EUROPEAN STANDARD NORME EUROPÉENNE
DRAFT prEN 13001-3-1
EUROPÄISCHE NORM July 2010 ICS 53.020.20
English Version
Cranes - General Design - Part 3-1: Limit States and proof competence of steel structure Appareils de levage à charge suspendue - Conception générale - Partie 3-1: Etats limites et vérification d'aptitude des structures en acier
Krane - Konstruktion allgemein - Teil 3-1: Grenzzustände und Sicherheitsnachweis von Stahltragwerken
This draft European Standard is submitted to CEN members for second enquiry. It has been drawn up by the Technical Committee CEN/TC 147. If this draft becomes a European Standard, CEN members are bound to comply with the CEN/CENELEC Internal Regulations which stipulate the conditions for giving this European Standard the status of a national standard without any alteration. This draft European Standard was established by CEN in three official versions (English, French, German). A version in any other language made by translation under the responsibility of a CEN member into its own language and notified to the CEN Management Centre has the same status as the official versions. CEN members are the national standards bodies of Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland and United Kingdom. Recipients of this draft are invited to submit, with their comments, notification of any relevant patent rights of which they are aware and to provide supporting documentation. Warning : This document is not a European Standard. It is distributed for review and comments. It is subject to change without notice and
shall not be referred to as a European Standard.
EUROPEAN COMMITTEE FOR STANDARDIZATION COMITÉ EUROPÉEN DE NORMALISATION EUROPÄISCHES KOMITEE FÜR NORMUNG
Management Centre: Avenue Marnix 17, B-1000 Brussels
© 2010 CEN
All rights of exploitation in any form and by any means reserved worldwide for CEN national Members.
Ref. No. prEN 13001-3-1:2010: E
prEN 13001-3-1:2010 (E)
Contents
Page
Foreword ..............................................................................................................................................................4 Introduction .........................................................................................................................................................5 1
Scope ......................................................................................................................................................5
2
Normative references ............................................................................................................................5
3
Terms and definitions ...........................................................................................................................7
4 4.1 4.2 4.2.1 4.2.2 4.3 4.3.1 4.3.2 4.3.3 4.3.4 4.3.5 4.4 4.5 4.6
General ................................................................................................................................................. 10 Documentation .................................................................................................................................... 10 Materials for structural members ...................................................................................................... 11 Grades and qualities .......................................................................................................................... 11 Impact toughness ............................................................................................................................... 13 Bolted connections............................................................................................................................. 14 Bolt materials ...................................................................................................................................... 14 General ................................................................................................................................................. 14 Shear and bearing connections ........................................................................................................ 15 Friction grip type (slip resistant) connections ................................................................................ 15 Connections loaded in tension ......................................................................................................... 15 Pinned connections ............................................................................................................................ 15 Welded connections ........................................................................................................................... 15 Proof of competence for structural members and connections .................................................... 16
5 5.1 5.2 5.2.1 5.2.2 5.2.3 5.2.4 5.2.5 5.3 5.3.1 5.3.2 5.3.3 5.3.4
Proof of............................................................................................. static strength .................................................................................................... .................. 16 General .................................................... 16 Limit design stresses and forces ...................................................................................................... 17 General ................................................................................................................................................. 17 Limit design stress in structural members ...................................................................................... 17 Limit design forces in bolted connections ...................................................................................... 18 Limit design forces in pinned connections ..................................................................................... 26 Limit design stresses in welded connections ................................................................................. 30 Execution of the proof ........................................................................................................................ 32 Proof for structural members ............................................................................................................ 32 Proof for bolted connections ............................................................................................................. 32 Proof for pinned connections ............................................................................................................ 33 Proof for welded connections ........................................................................................................... 33
6 6.1 6.2 6.2.1 6.2.2 6.2.3 6.3 6.3.1 6.3.2 6.3.3 6.3.4 6.4 6.5 6.5.1 6.5.2 6.5.3
Proof of fatigue strength .................................................................................................................... 34 General ................................................................................................................................................. 34 Limit design stresses ......................................................................................................................... 35 Characteristic fatigue strength .......................................................................................................... 35 Weld quality ......................................................................................................................................... 37 Requirements for fatigue testing ...................................................................................................... 38 Stress histories ................................................................................................................................... 38 General ................................................................................................................................................. 38 Frequency of occurence of stress cycles ........................................................................................ 39 Stress history parameter ................................................................................................................... 39 Stress history classes S .................................................................................................................... 40 Execution of the proof ........................................................................................................................ 41 Determination of the limit design stress range ............................................................................... 42 Applicable methods ............................................................................................................................ 42 Direct use of stress history parameter ............................................................................................. 42 Use of class S...................................................................................................................................... 42
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6.5.4
Independent concurrent normal and/or shear stresses .................................................................. 44
7
Proof of static strength of hollow section girder joints .................................................................. 44
8 8.1 8.2 8.2.1 8.2.2 8.3 8.3.1 8.3.2
Proof of elastic stability ...................................................................................................................... 44 General .................................................................................................................................................44 Lateral buckling of members loaded in compression ..................................................................... 45 Critical buckling load .......................................................................................................................... 45 Limit compressive design force ........................................................................................................ 46 Buckling of plate fields subjected to compressive and shear stresses ........................................ 48 General ................................................................................................................................................. 48 Limit design stress with respect to longitudinal stress σ x ............................................................49
8.3.3
Limit design stress with respect to transverse stress σ y .............................................................. 51
8.3.4 8.4 8.4.1 8.4.2
Limit design stress with respect to shear stress τ .........................................................................53 Execution of the proof ........................................................................................................................ 54 Members loaded in compression ...................................................................................................... 54 Plate fields ............................................................................................................................................54
Annex A (informative) Limit design shear force Fv,Rd per fit bolt and per shear plane for multiple shear plane connections ....................................................................................................................56 Annex B (informative) Preloaded bolts ........................................................................................................... 57 Annex C.1 C.2 C.3 C.4
C (normative) Design weld stress σW,Sd and τW,Sd............................................................................. 59 Butt joint ............................................................................................................................................... 59 Fillet weld ............................................................................................................................................. 60 T-joint with full and partial penetration .............................................................................................61 Effective distribution length under concentrated load ....................................................................61
Annex D (normative) Values of slope constant m and characteristic fatigue strength ∆σc, ∆τc .............. 63 Annex E (normative) Calculated values of limit design stress range ∆σ Rd................................................. 82 Annex F (informative) Evaluation of stress cycles ( example) .....................................................................84 Annex G (informative) Calculation of stiffnesses for connect ions loaded in tension ............................... 86 Annex H (informative) Hollow Sections ......................................................................................................... 89 Annex I (informative) Selection of a suitab le set of crane standards for a given application ............... 101 Annex ZA (informative) Relationship between this European Standard and the Essential Requirements of EU Directive 98/37/EC .......................................................................................... 102 Annex ZB (informative) Relationship between this European Standard and the Essential Requirements of EU Directive 2006/42/EC ...................................................................................... 103 Bibliography.................................................................................................................................................... 104 Selection of literatur e that contains infor mation about Hot Spot Stress M ethod: .................................. 104
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prEN 13001-3-1:2010 (E)
Foreword This document (prEN 13001-3-1:2010) has been prepared by Technical Committee CEN/TC 147 “Cranes Safety”, the secretariat of which is held by BSI. This document is currently submitted to the second CEN Enquiry. This document has been prepared under a mandate given to CEN by the European Commission and the European Free Trade Association, and supports essential requirements of EU Directive(s). For relationship with EU Directive(s), see informative Annex ZA and ZB, which is an integral part of this document. Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. CEN shall not be held responsible for identifying any or all such patent rights. This European Standard is one Part of EN 13001 Cranes – General Design. The other parts are as follows: Part 1:
General principles and requirements
Part 2:
Load actions
Part 3-2: Limit states and proof of competence of wire ropes in reeving systems Part 3-3: Limit states and proof of competence of wheel/rail contacts Part 3-4: Limit states and proof of competence of machinery Part 3-5: Limit states and proof of competence of forged hooks Annexes C, D and E are normative. Annexes A, B, F, G, H and I are informative.
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prEN 13001-3-1:2010 (E)
Introduction This European Standard has been prepared to be a harmonized standard to provide one means for the mechanical design and theoretical verification of cranes to conform with the essential health and safety requirements of the Machinery Directive, as amended. This standard also establishes interfaces between the user (purchaser) and the designer, as well as between the designer and the component manufacturer, in order to form a basis for selecting cranes and components. This European Standard is a type C standard as stated in EN ISO 12100-1. The machinery concerned and the extent to which hazards, hazardous situations and events are covered are indicated in the scope of this standard. When provisions of this type C standard are different from those which are stated in type A or B standards, the provisions of this type C standard take precedence over the provisions of the other standards, for machines that have been designed and built according to the provisions of this type C standard.
1
Scope
This European Standard is to be used together with EN 13001 – 1 and EN 13001 – 2 and as such they specify general conditions, requirements and methods to prevent mechanical hazards of cranes by design and theoretical verification. NOTE Specific requirements for particular types of crane are given in the appropriate European Standard for the particular crane type.
The following is a list of significant hazardous situations and hazardous events that could result in risks to persons during intended use and reasonably foreseeable misuse. Clauses 4 to 8 of this standard are necessary to reduce or eliminate risks associated with the following hazards: a) Exceeding the limits of strength (yield, ultimate, fatigue); b) Exceeding temperature limits of material or components; c) Elastic instability of the crane or its parts (buckling, bulging). This European Standard is not applicable to cranes which are manufactured before the date of its publication as EN and serves as reference base for the European Standards for particular crane types (see Annex I). NOTE
2
EN 13001-3-1 deals only with limit state method in accordance with EN 13001-1.
Normative references
The following referenced documents are indispensable for the application of this document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. EN 1990:2002, Eurocode — Basis of structural design EN 1993-1-8:2005, Eurocode 3: Design of steel structures – Part 1-8: Design of joints EN 10045-1:1989, Metallic materials; Charpy impact test — Part 1: Test method EN 10025-1:2004, Hot rolled products of structural steels — Part 1: General technical delivery conditions
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prEN 13001-3-1:2010 (E)
EN 10025-2:2004, Hot rolled products of structural steels — Part 2: Technical delivery conditions for non-alloy structural steels
EN 10025-3:2004, Hot rolled products of structural steels — Part 3: Technical delivery conditions for normalized/normalized rolled weldable fine grain structural steels
EN 10025-4:2004, Hot rolled products of structural steels — Part 4: Technical delivery conditions for thermomechanical rolled weldable fine grain structural steels
EN 10025-6:2004, Hot rolled products of structural steels — Part 6: Technical delivery conditions for flat products of high yield strength structural steels in the quenched and tempered condition
EN 10029:1991, Hot rolled steel plates 3 mm thick or above - Tolerances on dimensions, shape and mass EN 10149-1:1995, Hot-rolled flat products made of high yield strength steels for cold forming — Part 1: General delivery conditions
EN 10149-2:1995, Hot-rolled flat products made of high yield strength steels for cold forming — Part 2: Delivery conditions for thermomechanically rolled steels
EN 10149-3:1995, Hot-rolled flat products made of high yield strength steels for cold forming — Part 3: Delivery conditions for normalized or normalized rolled steels
EN 10163-1:2004, Delivery requirements for surface conditions of hot-rolles steel plates, wide flats and sections – Part 1: General requirements
EN 10163-2:2004, Delivery requirements for surface conditions of hot-rolles steel plates, wide flats and sections – Part 2: Plate and wide flats Delivery requirements for surface conditions of hot-rolles steel plates, wide flats and EN 10163-3:2004, sections – Part 3: Sections
EN 10164:2004, Steel products with improved deformation properties perpendicular to the surface of the product — Technical delivery conditions
EN 13001-1, Cranes — General Design — Part 1: General principles and requirements EN 13001-2, Cranes — General Design — Part 2: Load actions EN 20273:1991, Fasteners — Clearance holes for bolts and screws (ISO 273:1979) prEN ISO 898-1:2006, Mechanical properties of fasteners made of carbon steel and alloy steel — Part 1: Bolts, screws and studs (ISO/DIS 898-1:2006)
EN ISO 5817:2008, Welding — Fusion-welded joints in steel, nickel, titanium and their alloys (beam welding excluded) — Quality levels for imperfections (ISO 5817:2003, corrected version 2005, including Technical Corrigendum 1:2006))
EN ISO 9013:2002, Thermal cutting — Classification of thermal cuts — Geometrical specification and quality tolerances (ISO 9013:2002)
EN ISO 12100-1:2003, Safety of machinery — Basic concepts, general principles for design — Part 1: Basic terminology, methodology (ISO 12100-1:2003)
EN ISO 12100-2:2003, Safety of machinery — Basic concepts, general principles for design — Part 2: Technical principles (ISO 12100-2:2003)
EN ISO 17659:2004, Welding — Multilingual terms for welded joints with illustrations (ISO 17659:2002)
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prEN 13001-3-1:2010 (E)
ISO 286-2:1990, ISO system of limits and fits — Part 2: Tables of standard tolerance grades and limit deviations for holes and shafts
ISO 4306-1:2007, Cranes — Vocabulary — Part 1: General
3
Terms and definitions
3.1 Terms and definitions
For the purposes of this European Standard, the terms and definitions given in EN ISO 12100-1 and EN ISO 12100-2 and the basic list of definitions as provided in EN 1990-1 apply. For the definitions of loads, Clause 6 of ISO 4306-1:1990 applies. 3.2 Symbols and abbreviations
The symbols and abbreviations used in this Part of the EN 13001 are given in Table 1. Table 1 — Symbols and abbreviations Symbols, abbreviations
Description
A
cross section
An
net cross section
AS
stress area of a bolt
a
length of plate
ar
relevant weld thickness
b
width of plate
c
edge stress ratio factor (buckling)
Do, Di
outer, inner diameter of hollow pin
d
diameter (shank of bolt, pin)
do
diameter of hole
e1, e2
edge distances
Fb
tensile force in bolt
Fd
limit force
FK
characteristic value (force)
Fp
preloading force in bolt
FRd,σ
limit design force for normal stresses
FRd,τ
limit design force for shear stresses
Fe
external force (on bolted connection)
Fb, Rd Fb, Sd; Fbi, Sd
limit design bearing force design bearing force
Fcs, Rd
limit design tensile force
Fp, d
design preloading force
Fcr
reduction in compression force due to external tension
Fs, Rd
limit design slip force per bolt and friction interface
Ft, Rd
limit design tensile force in bolt
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prEN 13001-3-1:2010 (E)
Table 1 – (continued) Symbols, abbreviations
Description
Fv, Rd
limit design shear force per bolt/pin and shear plane
Fv, Sd
design shear force per bolt/pin and shear plane
Fσ,τ
acting normal/shear force
f
maximum imperfection
fd
limit stress
fK
characteristic value (stress)
fRd
limit design stress
fu
ultimate strength of material
fub
ultimate strength of bolts
fw, Rd
limit design weld stress
fy
yield stress of material
fyb
yield stress of bolts
fyk
yield stress (minimum value) of base material or member
fyp
yield stress of pins
Gt
mass of the moving crane parts during a representative working cycle
H
distance between weld and contact area of acting load
kσ, kτ
buckling factors
Kb
stiffness of bolt
Kc
stiffness of flanges
K*
specific spectrum ratio factor
km
stress spectrum factor based on m of the detail under consideration
K3
stress spectrum factor based on m = 3
lm
gauge length
lr
relevant weld length
lW
weld length
MRd
limit design bending moment
MSd
design bending moment
m
slope constant of log ∆σ/log N-curve
NC Nref
notch class reference number of cycles
min σ, max σ
extreme values of stresses
PS p1, p2
8
probability of survival distances between bolt centers
Q
mass of the maximum hoist load
q
impact toughness parameter
prEN 13001-3-1:2010 (E)
Table 1 – (continued) Symbols, abbreviations Rd r
Description
design resistance radius of wheel
Sd
design stresses or forces
s(m)
stress history parameter
T t Wel
Temperature Thickness elastic section modulus
α
side ratio (plate field buckling)
α
cross section parameter (lateral buckling)
αb
characteristic factor for bearing connection
αL
load introduction factor (buckling)
αw
characteristic factor for limit weld stress
γm
general resistance factor
γMf
fatigue strength specific resistance factor
γp
partial safety factor
γR
resulting resistance factor
γS γRb
specific resistance factor resulting resistance factor of bolt
γsb
specific resistance factor of bolt
γRm
resulting resistance factor of members
γsm
specific resistance factor of members
γRp
resulting resistance factor of pins
γsp
specific resistance factor of pins
γRs
resulting resistance factor of slip-resistance connection
γss
specific resistance factor of slip-resistance connection
γRc
resulting resistance factor for tension on section with holes
γst
specific resistance factor for tension on section with holes
γRw
resulting resistance factor of welding connection
γsw δp
specific resistance factor of welding connection elongation from preloading
φ2
dynamic factor
κ
dispersion angle (wheel pressure)
κ, κx, κy, κτ λ
reduction factors (buckling) width of contact area in weld direction
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prEN 13001-3-1:2010 (E)
Table 1 – (continued) Symbols, abbreviations λx, λy, λτ Ψ
4.1
non-dimensional plate slenderness (buckling) edge stress ratio (buckling)
∆Fb
additional force
∆δ
additional elongation
µ ν
slip factor relative total number of stress cycles (normalized)
νD
ratio of diameters
∆σc
characteristic value of stress range (normal stress)
∆τc
characteristic value of stress range (shear stress)
σe
reference stress (buckling)
σSd
design stress (normal)
τSd
design stress (shear)
σw, Sd
design weld stress (normal)
τw, Sd
design weld stress (shear)
∆σRd
permissible (limit) stress range (normal)
∆σRd,1
limit design stress range for k* = 1
∆τRd
permissible (limit) stress range (shear)
∆σSd
design stress range (normal) design stress range (shear)
∆τSd
4
Description
General Documentation
The documentation of the proof of competence shall include: design assumptions including calculation models, applicable loads and load combinations, material grades and qualities, weld quality classes, in accordance with EN ISO 5817, materials of connecting elements, relevant limit states results of the proof of competence calculation. and tests when applicable.
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4.2 Materials for structural members 4.2.1
Grades and qualities
European Standards specify materials and specific values. This standard gives a preferred selection. For structural members, steel according to following European Standards should be used: Non-alloy structural steels EN 10025-2. Weldable fine grain structural steels in conditions: normalized (N) EN 10025-3; thermomechanical (M) EN 10025-4. High yield strength structural steels in the quenched and tempered condition EN 10025-6. High yield strength steels for cold forming in conditions: thermomechanical (M) EN 10149-2; normalized (N)
EN 10149-3.
Table 2 shows specific values for the nominal value of strength fu, fy and limit design stress fRd (see 5.2). The values given are applicable for temperatures up to 150°C. For more information see the specific European Standard. Tolerance class A,inBthe or proof C of EN 10029 shall be specified for the plates the use nominal plate thicknesses calculations. Otherwise the minimum value to of allow thickness shallofbe used. values of Grades and qualities other than those mentioned in the above standards and in Table 2 may be used if the mechanical properties and the chemical composition are specified and conform to a relevant European Standard. If necessary, weldability shall be demonstrated. Table 2 — Specific values of steels for structural members Steel
Standard
Thickness t
mm
Nominal strength
fy yield
N/mm2
S235
EN 10025-2 S275
t ≤ 16 16 < t ≤ 40 40 < t ≤ 100 100 < t ≤ 150
235 225 215 195
t ≤ 16 16 < t ≤ 40 40 < t ≤ 63 63 < t ≤ 80 80 < t ≤ 100 100 < t ≤ 150
275 265 255 245 235 225
Limit design stress (γRm=1,1)
fu ultimate
fRdσ, normal
fRdτ, shear
340
214 205 195 177
123 118 113 102
430
250 241 232 223 214 205
144 139 134 129 123 118
N/mm2
N/mm2
N/mm2
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Table 2 – (continued) Steel
Standard
Thickness t
mm
Nominal strength
fy yield
2
N/mm
2
fRdσ, normal
fRdτ, shear
323 314 305 296
186 181 176 171
N/mm2
N/mm2
N/mm
t ≤ 16 16 < t ≤ 40 40 < t ≤ 63 63 < t ≤ 80
355 345 335 325
80 < t ≤ 100 100 < t ≤ 150 t < 16 16 < t ≤ 40 40 < t ≤ 63 63 < t ≤ 80 (N) 80 < t ≤ 100 (N) 100 < t ≤ 150 (N) t < 16 16 < t ≤ 40 40 < t ≤ 63 63 < t ≤ 80 (N) 80 < t ≤ 100 (N) 100 < t ≤ 150 (N) t < 16 16 < t ≤ 40 40 < t ≤ 63 63 < t ≤ 80 (N) 80 < t ≤ 100 (N)
315 295
287 268
166 155
355 345 335 325 315 295
450
323 314 305 295 286 268
186 181 176 171 165 155
500
382 364 355 336 327 309
220 210 205 194 189 178
418 400 391 373 364
241 231 226 215 210
S460
3 < t ≤ 50 50 < t ≤ 100
460 440
550
418 400
241 231
S500
3 < t ≤ 50 50 < t ≤ 100
500 480
590
455 436
262 252
S550
3 < t ≤ 50 50 < t ≤ 100
550 530
640
500 482
289 278
3 < t ≤ 50 50 < t ≤ 100
620 580
700
564 527
325 304
S690
3 < t ≤ 50 50 < t ≤ 100
690 650
770 760
627 591
362 341
S890
3 < t ≤ 50 50 < t ≤ 100
890 830
940 880
809 755
467 436
S960
3 < t ≤ 50
S355
S355
EN 10025-2
EN 10025-3 (N) EN 10025-4 (M)
S420
S460
S620
EN 10025-6
420 400 390 370 360 340 460 440 430 410 400
490
530
960
980
873
504
S315
315
390
286
165
S355
355
430
323
186
420
480
382
220
460
520
418
241
550
455
262
600
500
289
S420 S460 (M) S500 (M)
S550 (M)
12
Limit design stress (γRm=1,1)
fu ultimate
EN 10149–2 (M) all t
500 EN 10149-3 (N) 550
prEN 13001-3-1:2010 (E)
Table 2 – (continued) Steel
Thicknesst
Standard
mm
Nominal strength
fy yield
N/mm S600 (M) S650 (M)
EN 10149–2 (M)
S700 (M)
EN 10149-3 (N)
4.2.2
2
all t
600 650
t≤8
650
t>8
630
t≤8
700 680
t>8
Limit design stress (γRm=1,1)
fu ultimate
N/mm
fRdσ, normal
fRdτ, shear
N/mm2
2
545
N/mm2
315
700
750
591
341
573
331
636 618
367 357
Impact toughness
When selecting grade and quality of the steel for tensile members, the sum of impact toughness parameters q i shall be taken into account. Table 3 gives the impact toughness parameters qi for various influences. Table 4 gives the required steel quality and impact energy/test temperature in dependence of Σqi. Grades and qualities of steel other than mentioned in Table 4 may be used, if an impact energy/temperature is tested in accordance with EN 10045-1 and specified. Table 3 — Impact toughness parameters qi i
Influence
1
0
-10 ≤ T < 0
1
-20 ≤ T < -10
2
-30 ≤ T < -20
3
-40 ≤ T < -30
4
-50 ≤ T < -40
6
fy ≤ 300
0
300 < fy ≤ 460
1
460 < fy ≤ 700
2
700
3
1000
4
t ≤ 10
0
10 < t ≤ 20
1
20 < t ≤ 40
2
40 < t ≤ 60
3
60 < t ≤ 80 80 < t ≤ 100
4 5
b
100 < t ≤ 125
6
1,8
125 < t ≤ 150
7
Operating temperature T (°C)
2 Yield stress fy (N/mm2)
3
Material thickness t (mm) Equivalent thickness t for solid bars:
t=
d 1,8
for
b h
< 1,8 : t =
qi
0≤T
4 Stress concentration and notch class ∆σc (N/mm2) (see Annex D and Annex H)
∆σc > 125
0
80 < ∆σc ≤ 125
1
56< ∆σc ≤ 80
2
40≤ ∆σc ≤ 56
3
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Table 4 — Impact toughness requirement and corresponding steel quality for ∑qi ∑ qi ≤ 5
6 ≤ ∑ qi ≤ 8
9 ≤ ∑q11 i ≤
Impact energy/ test temperature requirement
27 J / +20°C
27 J / 0°C
27 J / -20°C
EN 10025-2
JR
J0
J2
EN 10025-3
N
N
N
EN 10025-4
M
M
M
ML
EN 10025-6
Q
Q
Q
QL
EN 10149-1
NC, MC
NC, MC
NC, MC
a)
4.3 4.3.1
12
≤ ∑qi ≤ 14 27 J / -40°C
a)
NL
a)
May be used if the impact toughness is at least 27 J at – 40 °C, tested in accordance with EN 10045-1 and specified ,
Bolted connections Bolt materials
For bolted connections bolts of the property classes (bolt grades) 4.6, 5.6, 8.8, 10.9 or 12.9 in accordance with prEN ISO 898-1 shall be used. Table 5 shows nominal values of the strengths: Table 5 — Property classes (bolt grades) Property class (Bolt grade)
4.6
5.6
8.8
10.9
12.9
f yb (N/mm2)
240
300
640
900
1 080
fub (N/mm2)
400
500
800
1 000
1 200
NOTE The designer should ask the bolt supplier to demonstrate compliance with the requirements regarding the protection against hydrogen brittleness, for the property classes (bolt grades) 10.9 and 12.9. Technical requirements can be found in EN ISO 15330, EN ISO 4042 and ISO 9587. 4.3.2
General
For the purpose of this standard bolted connections are connections between members and/or components utilizing bolts. In general bolted connections are tensioned wrench tight. Where slippage (e.g. caused by vibrations or fluctuations in loading) causes deleterious changes in geometry bolts shall be tightened to avoid slippage sufficiently or the joint surfaces shall be secured against rotation (e. g. by using multiple bolts);
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4.3.3
Shear and bearing connections
For the purpose of this standard shear and bearing connections are those connections where the loads act perpendicular to the bolt axis and cause shear and bearing stresses in the bolts and bearing stresses in the connected parts, and where clearance between bolt and hole shall conform to ISO 286-2 tolerances h13 and H11 or closer, when
bolts are exposed to load reversal or where slippage may cause deleterious changes in geometry; in other cases wider clearances in accordance with EN 20273 may be used; special surface treatment of the contact surfaces is not needed. 4.3.4
Friction grip type (slip resistant) connections
For the purpose of this standard friction grip connections are those connections where the loads are transmitted by friction between the joint surfaces, and where high strength bolts of property classes (bolt grades) 8.8, 10.9 or 12.9 shall be used; bolts shall be tightened by a controlled method to a specified preloading state; the surface condition of the contact surfaces shall be specified and taken into account accordingly; in addition to standard holes oversized and slotted holes may be used. 4.3.5
Connections loaded in tension
For the purpose of this standard connections loaded in tension are those connections where the loads act in the direction of the bolt axis and cause axial stresses in the bolts, high strength bolts of property classes (bolt grades) 8.8, 10.9 or 12.9 are used and tightened by a
controlled method to a specified preloading state; NOTE
4.4
Bolts in tension that are not preloaded are treated as structural members.
Pinned connections
For the purpose of this standard pinned connections are connections that do not constrain rotation between connected parts. Only round pins are considered. The requirements herein apply to pinned connections designed to carry loads, i. e., they do not apply to connections made only as a convenient means of attachment. Clearance between pin and hole shall be in accordance with ISO 286-2 tolerances h13 and H13 or closer. In case of loads with changing directions closer tolerances shall be applied. All pins shall be furnished with retaining means to prevent the pins from becoming displaced from the hole. In order to inhibit local out-of-plane distortion (dishing), consideration shall be given to the stiffness of the connected parts. 4.5
Welded connections
For the purposes of this standard welded connections are joints between members and/or components which utilize fusion welding processes, and where connected parts are 3 mm or larger in thickness.
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prEN 13001-3-1:2010 (E)
Quality levels of EN ISO 5817 shall be applied , and appropriate methods of non-destructive testing shall be used to verify compliance with quality level requirements. In general, load carrying welds shall be at least of quality level C.. Quality level D may be applied only in joints where local failure of the weld will not result in failure of the structure or falling of loads. Terms for welded joints are as given in EN ISO 17659. Although the distribution of stresses along the length of the weld may be non-uniform, such distributions can, in general, be considered uniform. Residual stresses and stresses not participating in the transfer of forces need not to be considered in the design of weld subjected to static actions. This applies specifically to the normal stress parallel to the axis of the weld which is accommodated by the base material. 4.6
Proof of competence for structural members and connections
The object of the proof of competence is to demonstrate that the design stresses or forces S d do not exceed the design resistances Rd :
Sd ≤ Rd
(1)
The design stresses or forces S d shall be determined by applying the relevant loads, load combinations and partial safety factors in accordance with EN 13001-2. In the following clauses, the design resistances Rd are represented as limit stresses f d or limit forces Fd . The following proofs for structural members and connections shall be demonstrated: proof of static strength in accordance with clause 5; proof of fatigue strength according to 6, proof of strength of hollow section girder joints in accordance with clause 7; proof of elastic stability in accordance with clause 8.
5 5.1
Proof of static strength General
A proof of static strength by calculation is intended to prevent excessive deformations due to yielding of the material, sliding of friction-grip connections, elastic instability (see 8) and fracture of structural members or connections. Dynamic factors given in EN 13001-2 are used to produce equivalent static loads to simulate dynamic effects. The use of the theory of plasticity for calculation of ultimate load bearing capacity is not considered acceptable within the terms of this standard. The proof shall be carried out for structural members and connections whilst taking into account the most unfavourable load effects from the load combinations A, B or C in accordance with EN 13001-2 and applying the resistances according to 5.2.
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This standard is based on nominal stresses, i. e. stresses calculated using traditional elastic strength of materials theory. When alternative methods of stress calculation are used, such as finite element analysis, using those stresses for the proof given in this standard may yield inordinately conservative results. 5.2
Limit design stresses and forces
5.2.1
General
The limit design stresses and forces shall be calculated from: Limit design stresses fRd = function ( fk , γ R ) or (2)
FRd = function ( Fk , γ R )
Limit design forces where
fk or Fk
are characteristic values (or nominal values)
γR
is the total resistance factor
γm
is the general resistance factor
γs
is the specific resistance factor applicable to specific structural components as given in the clauses below
γ R =γ m ×γ s γ m = 1,1 (see EN 13001-2)
fRd and FRd are equivalent to R / γ m in EN 13001-1.
NOTE 5.2.2
Limit design stress in structural members
The limit design stress fRd , used for the design of structural members, shall be calculated from:
f yk
fRdnormal for = stresses σ
γ Rm
f yk
for fRdshear stresses τ =
γ Rm 3
(3)
(4)
γ Rm = γ m ×γ sm
with where
f yk
γ sm
is the minimum value of the yield stress of the material (see Table 2, column fy ) is the specific resistance factor for material as follows: For non-rolled material
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γ sm = 1,0 For rolled materials (e. g. plates and profiles):
γ sm = 1,0 for stresses in the plane of rolling γ sm = 1,0 for compressive and shear stresses For tensile stresses perpendicular to the plane of rolling (see Figure 1): Material shall be suitable for carrying perpendicular loads and be free of lamellar defects.
γ sm = 1,0 for plate thicknesses less than 15mm or material in quality classes Z25 or Z35 in accordance with EN 10164 γ sm = 1,16 for material in quality class Z15 in accordance with EN 10164 γ sm = 1,50 without quality classification of through-thickness property
Key
Figure shows a tensile load perpendicular to plane of rolling where 1 is the direction of the plane of rolling 2 is the direction of stress/load Figure 1 — Tensile load perpendicular to plane of rolling 5.2.3
Limit design forces in bolted connections
5.2.3.1 5.2.3.1.1
Shear and bearing connections General
The resistance of a connection shall be taken as the least value of the limit forces of the individual connection elements. In addition to the bearing capacity of the connection elements other limit conditions at the most stressed sections shall be verified using the resistance factor of the base material. Only the unthreaded part of the shank is considered effective in the bearing calculations;
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5.2.3.1.2
Bolt shear
The limit design shear force Fv,Rd per bolt and for each shear plane shall be calculated from: f yb × A
Fv,Rd =
(5)
γ Rb × 3
γ Rb = γ m × γ sb
with where
f yb
is the yield stress (nominal value) of the bolt material (see Table 5)
A
is the cross-sectional area of the bolt shank at the shear plane
γ sb
is the specific resistance factor for bolted connections
γ sb = 1,0
for multiple shear plane connections
γ sb = 1,3
for single shear plane connections
See Annex A for limit design shear forces of selected bolt sizes. 5.2.3.1.3
Bearing on bolts and connected parts
The limit design bearing force Fb , Rd per bolt shall be calculated from:
Fb,Rd =
fy × d × t
γ Rb
(6)
γ Rb = γ m × γ sb
with
With the requirement e1 ≥ 1,5 × d 0
(7)
and with the following recommendations for the plate e2 ≥ 1,5 × d 0 p1 ≥ 3,0 × d 0 p2 ≥ 3,0 × d 0
where
fub
is the ultimate strength (nominal value) of the bolt (Table 5)
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fu
is the ultimate strength (nominal value) of the basic material (Table 2)
fy
is the minimum value of yield stresses of the basic materials and bolt (Table 2)
d
is the shank diameter of the bolt
d0
is the diameter of the hole
t
is the thickness of the connected part in contact with the unthreaded part of the bolt
γ sb
is the specific resistance factor for bolt connections
γ sb = 0,7 for multiple shear plane connections γ sb = 0,9 for single shear plane connections p1 p 2 e1 e 2
,
,
,
are distances (see Figure 2)
Key
p1 p 2 e1 e2 , , , are distances used in Equation (2) Arrow shows the direction of force Figure 2 — Illustration for Equation (7) 5.2.3.1.4
Tension in connected parts
Fcs,Rd , on the net cross-section The limit design tensile force per connected member with respect to yielding, shall be calculated from:
Fcs,Rd =
f y × An γ Rc
with
γ Rc = γ m × γ st where
20
(8)
prEN 13001-3-1:2010 (E)
An
is the net cross-sectional area at bolt or pin holes (see Figure 2)
γ st
is the specific resistance factor for tension on sections with holes γ st = 1,2
5.2.3.2
Friction grip type connections
The resistance of a connection shall be determined by summing the limit forces of the individual connecting elements. For friction grip type connections the limit design slip force Fs,Rd per bolt and per friction interface shall be calculated from: Fs,Rd =
µ × ( Fp, d − Fcr ) γ Rs
(9)
with γ Rs = γ m × γ ss where µ
is the friction coefficient
µ = 0,50
for surfaces blasted metallic bright with steel grit or sand, no unevenness
µ = 0,50
for surfaces blasted with steel grit or sand and aluminized
µ = 0,50 µ = 0,40
for surfaces blasted with steel grit or sand and metallized with a product based on zinc for surfaces blasted with steel grit or sand and alkali-zinc-silicate coating of 50 µm to 80 µm thickness
µ = 0,40
for surfaces hot dip galvanized and lightly blasted
µ = 0,30
for surfaces cleaned metallic bright by wire brushing
µ = 0,25
for surfaces cleaned and treated with etch primer
µ = 0,20
for surfaces cleaned of loose rust, oil and dirt (minimum requirement)
Fp,d
Fcr
is the design preloading force is the reduction in the compression force due to external tension on connection (for simplification
Fcr = Fe
may be used).
The applied preloading force shall be greater than or equal to the design preloading force.
γ ss
is the specific resistance factor for friction grip type connections (see Table 6)
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Table 6 — Specific resistance factor γss for friction grip connections Type of holes Effect of connection slippage
Standard a holes
b
Oversized and shortc slotted holes
Longslotte d holes
Longslotte d holes
c
d
a hazard is created
1,14
1,34
1,63
2,00
a hazard is not created
1,00
1,14
1,41
1,63
a
Holes with clearances in accordance with the medium series of EN 20273:1991.
b
Holes with clearances in accordance with the coarse series of EN 20273:1991.
c
Slotted holes with slots perpendicular to the direction of force.
d
Slotted holes with slots parallel to the direction of force.
Short slotted hole: length of hole is smaller than or equal to 1.25 times the diameter of the bolt. Long slotted hole: length of hole is larger than 1.25 times the diameter of the bolt. In order to reduce pressure under bolt or nut appropriate washers shall be used.
Table B.2 gives limit design slip forces using the specific resistance factor value γ ss = 1,14 and a design preloading force of Fp,d = 0,7 × f yb × As ,
where
f yb
is the yield stress (nominal value) of the bolt material (Table 5)
As
is the stress area of the bolt (Table B.2).
5.2.3.3
Connections loaded in tension
This clause specifies the limit state for a bolt in the connection. The connected parts and their welds shall be calculated with the general rules for structural members, where the preload in the bolt is considered as one loading component. The proof calculation shall be done for the bolt under maximum external force in a connection, with due consideration to the force distribution in a multi-bolt connection and the prying effects (i. e. leverage). Proof of competence calculations of a preloaded connection shall take into account the stiffness of the bolt and the connected parts, see Figure 3. In addition to that, the effect of different load paths of the external compression force, depending upon the joint construction, shall be taken into account, see Figure 4.
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Key
Fp
Preloading force in bolt Bolt elongation due to preloading Fe,t External tensile force Fe,c External compression force ∆δt Additional elongation, due to external tensile δp
force Fb Tensile force in bolt ∆Fb,t Additional force in bolt, due to external tensile force ∆Fb,cAdditional force in bolt, due to external compression force Kb Stiffness of bolt Kc Stiffness of connected parts
Figure 3 — Force-elongation-diagram
a)
External compression force does not interfere b) with the compression zone under the bolt
External compression force is transferred through the compression zone under the bolt
For simplicity, a symmetric loading with the bolt in the middle is assumed in the figure. Figure 4 — Load path alternatives for the external compression force
Two separate design limits shall be considered for the external tensile bolt force:
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1)
the resulting bolt force from the external force and the maximum design preload shall not exceed the bolt yield load, Equation (10)
2)
the connection shall not open (gap) under the resulting bolt force from the external force and the minimum design preload, Equation (11).
For connections loaded in tension it shall be proven that the external tensile design force in the bolt Fe,t , does not exceed either of the two limit design forces Ft1,Rd or Ft2,Rd , see also 5.3.2. The limit design tensile force per bolt for the bolt yield criteria is calculated from: Fy / γ Rb − Fp,max
Ft1,Rd =
(10)
Φ
with Φ =
Kb Kb + K c
and Rb = γ m × γ sb
and Fy = f yb × As
where is the bolt yield force,
Fy Fp,max
is the maximum value of the preload,
fyb
is the yield stress of the bolt material,
As
is the stress area of the threaded part of the bolt,
Φ
is the stiffness ratio factor of the connection, see also Annex G,
γ sb
is the specific resistance factor for connections loaded in tension,
γ sb = 0,91 NOTE:
A load introduction factor αL may be taken into account when calculating the factor Φ, see Annex G.
The limit design tensile force per bolt for the opening criteria of the connection is calculated from: Ft2,Rd
=
Fp,min
(11)
γ Rb ⋅ (1− Φ )
where is the minimum value of the preload.
Fp,min
The variation of preload due to scatter is taken into account by the maximum and minimum values of the preload as follows: and
Fp,max Fp,min
=
=
(1 + s ) × Fp,d
(1 − s ) × Fp,d
where Fp,d
24
is the nominal value of the design preload,
(12) (13)
prEN 13001-3-1:2010 (E)
Fp,max
is the maximum value of the preload,
Fp,min
is the minimum value of the preload, is the preload scatter,
s
s = 0,23
controlled tightening, rotation angle or tightening torque is measured
s = 0,09
controlled tightening, force in bolt or elongation is measured.
The nominal value of the design preloadFp,d value shall not exceed the values given in Table 7. Otherwise, any value for the preload may be chosen for a particular connection. Table 7 — Upper limits of preload levels according to method of preloading Type of preloading method
Upper limit of preload level
Methods, where the bolt is subjected to torque
0,7 Fy
Methods, where only direct tension is applied to the bolt
0,9 Fy
NOTE For direct tensioning method, the nominal preload is the residual preload achieved after a possible loss of the applied preload during the tensioning operation.
See Table B.1 for information on tightening torques. For the calculation of the additional force in bolt, the load path of the external compression force shall be considered, see Figure 4. In a general format the additional force in bolt is calculated as follows: ∆Fb = Φ × Fe, t + Fe,c
(14)
where ∆Fb
is the additional force in bolt
Φ
is the stiffness ratio factor
Fe, t
is the external tensile force
Fe,c
is the external compression force. This shall be omitted (i. e. Fe,c is set to zero in the equation) in cases, where the external compression force does not interfere with the compression zone under the bolt, case a) in Figure 4.
The additional force in bolt ∆Fb shall be used in the proof of fatigue strength of the bolt in accordance with clause 6. 5.2.3.4
Bearing type connections loaded in combined shear and tension
When bolts in a bearing type connection are subjected to both tensile and shear forces, the applied forces shall be limited as follows: 2
2
Ft,Sd F + v,Sd ≤ 1 Ft,Rd Fv,Rd
(15)
where Ft, Sd is the external tensile force per bolt
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Ft,Rd is the limit tensile force per bolt (see 5.2.3.3) Fv, Sd is the design shear force per bolt per shear plane Fv,Rd is the limit shear force per bolt per shear plane (see 5.2.3.1.2) 5.2.4
Limit design forces in pinned connections
5.2.4.1
Pins, limit design bending moment
The limit design bending moment is calculated from M Rd =
Wel × f yp γ Rp
(16)
with γ Rp = γ m × γ sp where Wel
is the elastic section modulus of the pin
f yp
is the yield stress (minimum value) of the pin material
γ sp
is the specific resistance factor for pinned connections bending moment γ sp = 1,0
5.2.4.2
Pins, limit design shear force
The limit design shear force per shear plane for pins is calculated from Fv,Rd =
1 u
×
A × f yp
(17)
3 × γ Rp
with γ Rp = γ m × γ sp where u
is the shape factor u=
4 3
for solid pins
4 1 + vD + vD 2 u = 3 × 1+ v 2 D where
26
νD =
for hollow pins
Di , DO
Di
is the inner diameter of pin
Do
is the outer diameter of pin
prEN 13001-3-1:2010 (E)
is the cross-sectional area of the pin
A
is the specific resistance factor for shear force in pinned connections
γ sp
γ sp = 1,0 for m ultiple shear plane connections γ sp = 1,3 for single shear plane connections 5.2.4.3
Pins and connected parts, limit design bearing force
The limit design bearing force is calculated from Fb,Rd =
αb × d × t × fy γ Rp
(18)
with γ Rp = γ m × γ sp where f yp
α b =Min
fy
1,0
fy
is the yield stress (minimum value) of the material of the connected parts
f yp is the yield stress (minimum value) of the pin material d
is the diameter of the pin
t
is the lesser value of the thicknesses of the connected parts, i. e. t1 + t 2 or t 3 in Figure 5
γ sp
is the specific resistance factor for the bearing force in pinned connections
γ sp = 0,6 when connected parts in multiple shear plane connections are held firmly together by retaining means such as external nuts on the pin ends γ sp = 0,9 for single shear plane connections or when connected parts in multiple shear plane connections are not held firmly together
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Figure 5 — Pinned connections
In case of significant movement between the pin and the bearing surface, consideration should be given to reducing the limit bearing force in order to reduce wear. In case of reversing load consideration should be given to the avoidance of plastic deformation. 5.2.4.4
Connected parts, limit design force with respect to shear
The limit design force in a failure mode, where a piece of material is torn out, shall be based upon shear stress in a critical section. In general, a uniform shear stress distribution throughout the section is assumed. The limit design shear force is calculated as follows: As × f y
Fv, Rd =
γm ⋅ 3
(19)
with As = (s1 + s2 ) × t in general and As = 2 × s × t
for a symmetric construction as in Figure 6 a) and c),
where
fy As
is the yield stress of the material of the structural member in question is the shear area of the tear-out section
s,s1,s2 are shear lengths of the tear-out section. For constructions in accordance with Figure 6 the tear-
out section is A-A and shear lengths are determined through a 40 degree rule as indicated.
t
28
is the thickness of the member.
prEN 13001-3-1:2010 (E)
Figure 6 — Connected parts 5.2.4.5
Connected parts, limit design force with respect to tensile stress
Design shall be based upon the maximum tensile stress at inner surface of the pin hole. Stress concentration due to geometry of the pin hole shall be considered. The limit design force for the construction in accordance with Figure 6 a) is determined as follows: Fv, Rd =
2×b×t × fy k × γ m × γ sp
(20)
with γ sp = 0,95
k
where
f y is the yield stress of the material of the structural member in question,
γ sp is the specific resistance factor for tension at pinned connections, k is the stress concentration factor, i.e. ratio between the maximum stress and the average stress in the section.For a construction with the geometric proportions as 1≤ c/b ≤2 and 0.5 ≤ b/d ≤1 (see Figure 6), the stress concentration factor k is taken from the Figure 7. The clearance between the hole and the pin are assumed to conform ISO 286-2 tolerances H11/h11 or closer. In case of a larger clearance, higher values of k shall be used.
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Figure 7 — Stress concentration factors for a specific type of pinned connection
NOTE Tensile loads or tensile parts of reversing loads only need to be considered within this clause. However, reversing load situations may require additional considerations where this may result in unacceptable plastic deformations or affect functionality of the connection (see 5.2.4.3). 5.2.5
Limit design stresses in welded connections
The limit design weld stress f w,Rd used for the design of a welded connection depends on: the base material to be welded and the weld material used; the type of the weld; the type of stress evaluated in accordance with Annex C; the weld quality.
Depending on the equation number given in Table 8, the limit design weld stressf w,Rd shall be calculated either by: f w,Rd =
α w × f yk γm
(21)
f w,Rd =
α w × f uw γm
(22)
or by
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where
αw
is a factor given in Table 8 in dependence on the type of weld, the type of stress and the material
f yk
is the minimum value of the yield strength of the connected member under consideration
fuw
is the ultimate tensile strength of the weld material (all weld metal) Table 8 — Factor for limit weld stress
Direction of stress
Type of weld
Type of stress
αw
Equation number f yk < 960
Stress normal to the weld direction
Stress parallel to the weld direction
The values of
f yk ≥ 960
N/mm²
N/mm²
Full penetration weld, matching weld Tension material Compression
21
1,0
0,93
21
1,0
0,93
Full penetration weld, undermatching weld materials
Tension
22
0,80
0,80
Compression
22
0,80
0,80
Partial penetration weld, matching weld materiala
Tension or 21 compression
0,70
0,65
Partial penetration weld, undermatching weld materiala
Tension or 22 compression
0,56
0,,56
All welds, matching weld material All welds, undermatching weld material
Shear Shear
0,70 0,54
0,65 0,54
All welds
Tension or 21 Compression
1,0
0,93
All welds, matching weld material
Shear
21
0,60
0,55
Full penetration welds, undermatching weld material
Shear
22
0,50
0,50
Partial penetration weld, undermatching weld material
Shear
22
0,50
0,50
21 22
α w are valid for welds in quality classes B and C of EN ISO 5817.
In case of connected members from different materials, the proof shall be made for each member separately. Undermatching weld material: weld material with strength properties less than those of connected members a
Note : An asymmetric weld is not recommended. However, if used connected members shall be supported so as to avoid the effect of load eccentricity on the weld.
The welds joining parts of built-up members, e.g. flange-to-web connections, may be designed without regard to normal stress parallel to the axis of the weld, provided the welds are proportioned to accommodate the shear forces developed between those parts.
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5.3
Execution of the proof
5.3.1
Proof for structural members
For the structural member to be designed it shall be proven that:
σ Sd ≤ fRdσ and τ Sd ≤ f Rd
(23)
τ
where
σ Sd,τ Sd
are the design stresses. The von Mises equivalent stress may be used as the design stress instead.
fRdσ , fRdτ
are the corresponding limit design stresses in accordance with clause 5.2.2. In case von Mises is used, fRdσ is the limit design stress.
In case of plane states of stresses when von Mises stresses are not used it shall additionally be proven that: σ Sd, x f Rdσ, x
2
σ + Sd, y f Rdσ, y
2
σ × σ Sd, y τ − Sd, x + Sd f × f Rd σ , x Rd , y σ f Rdτ
2
≤ 1
(24)
where indicate the orthogonal directions of stress components.
x, y
Spatial states of stresses may be reduced to the most unfavourable plane state of stress. 5.3.2
Proof for bolted connections
For each mode of failure of a connection it shall be proven for the most highly loaded member that: (25)
FSd ≤ FRd
where FSd
is the design force of the element, depending on the type of connection, e. g.
Fe,t FRd
NOTE
32
for connections loaded in tension (see 5.2.3.3)
is the limit design force in accordance with clause 5.2.3, depending on the type of the connection, i. e.
Fv,Rd
limit design shear force
Fb,Rd
limit design bearing force
Fs,Rd
limit design slip force
Ft,Rd
limit design tensile force
Care should be taken in apportioning the total load into individual components of the connection.
prEN 13001-3-1:2010 (E)
5.3.3
Proof for pinned connections
For pins, it shall be proven that:
M Sd ≤ M Rd Fv,Sd ≤ Fv,Rd
(26)
Fbi,Sd ≤ Fb,Rd where
M Sd
is the design value of the bending moment in the pin
M Rd
is the limit design bending moment in accordance with clause 5.2.4
Fv,Sd
is the design value of the shear force in the pin
Fv,Rd
is the limit design shear force in accordance with clause 5.2.4.2
Fbi,Sd
is the most unfavourable design value of the bearing force in the joining plate i of the pin connection
Fb,Rd
is the limit design bearing force in accordance with clause 5.2.4
NOTE In multi – pin connections care should be taken in apportioning the total load into individual components of the connection.
As a conservative assumption in the absence of a more detailed analysis the following equation may be used.
l
M Sd =
4
⋅ Fb3
(27)
where is the distance between
l
Fb3 5.3.4
is the sum of
Fb 1 and Fb2
Fb1 and Fb2 (see Figure 5)
Proof for welded connections
For the weld to be designed it shall be proven that:
σ w,sd and τ w,Sd ≤ f w,Rd
(28)
where
τ w,Sd, σ w,Sd f w,Rd
are the design weld stresses (see Annex C) is the corresponding limit design weld stress in accordance with clause 5.2.5
In case of plane states of stresses (with orthogonal stress components τ w,Sd , σ w,Sd,x , σ w,Sd, y ) in welded connections it shall additionally be proven that:
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σ w,Sd, x f w,Rd, x
2
σ + w,Sd, y f w,Rd, y
2
2
σ × σ w,Sd, y τ w, Sd − w,Sd, x ≤ 1,1 + f w,Rd, x × f w,Rd, y f w,Rd
(29)
where x, y
6 6.1
indicate the orthogonal directions of stress components.
Proof of fatigue strength General
A proof of fatigue strength is intended to prevent risk of failure due to formation and propagation of critical cracks in structural members or connections under cyclic loading. Where the design stress always is purely compressive in a uniaxial stress state, and hence crack propagation cannot occur, a proof of fatigue strength is not required. In general, the proof shall be executed by applying the load combinations A in accordance with EN 13001-2, multiplied by the dynamic factors φi , setting all partial safety factors γp = 1, and applying the resistances (i. e. limit design stresses) according to 6.2. In some applications a load from load combinations B (occasional loads) can occur frequently enough to require inclusion in the fatigue assessment. The stresses from these occasional loads shall be handled in the same way as those from the regular loads. The stresses are calculated in accordance with the nominal stress concept. This document deals only with the nominal stress method. A nominal stress is a stress in the base material adjacent to a potential crack location, calculated in accordance with simple elastic strength of materials theory, excluding local stress concentration effects. The constructional details in Annex D and Annex H contain the influences illustrated in the figures and thus the characteristic fatigue strength values include the effects of:
local stress concentrations due to the shape of the joint and the weld geometry;
size and shape of acceptable discontinuities; the stress direction; residual stresses; metallurgical conditions; in some cases, the welding process and post-weld improvement procedures.
The effect of other geometric stress concentrations than those listed above (global stress concentrations) shall be included in the nominal stress by means of relevant stress concentration factors. NOTE This standard does not use other methods like Hot Spot Stress Method. The bibliography gives information on literature about Hot Spot Stress Method.
For the execution of the proof of fatigue strength the cumulative damages caused by variable stress cycles shall be calculated. In this standard Palmgren-Miner's rule of cumulative damage is reflected by use of the stress history parameters (see Clause 6.3). Mean-stress influence, as presented in EN 13001-1, in structures in as-welded condition (without stress relieving) can be considered but is negligible. Therefore the stress history parameter s is independent of the mean-stress and the fatigue strength is based on the stress range only. In non-welded details or stress relieved welded details, the effective stress range to be used in the fatigue
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prEN 13001-3-1:2010 (E)
assessment may be determined by adding the tensile portion of the stress range and 60 % of the compressive portion of the stress range or by special investigation (see 6.5). The fatigue strength specific resistance factor γ mf (given in Table 9) is used to account for the uncertainty of fatigue strength values and the possible consequences of fatigue damage. Table 9 — Fatigue strength specific resistance factor gmf
γ mf Accessibility
Fail-safe components
Non fail-safe components without hazards persons
for
with hazards for persons
Accessible joint detail
1,0
1,10
1,20
Joint detail with poor accessibility
1,05
1,15
1,25
„Fail-safe“ structural components are those with reduced consequences of failure, such that the local failure of one component does not result in failure of the structure or falling of loads. Non „fail-safe“ structural components are those where local failure of one component leads rapidly to failure of the structure or falling of loads.
6.2 6.2.1
Limit design stresses Characteristic fatigue strength
The limit design stress of a constructional detail is characterized by the value of ∆σ c , the characteristic fatigue strength. ∆σ c represents the fatigue strength at 2 ×106 cycles under constant stress range loading and with a probability of survival equal to Ps = 97,7 % (mean value minus two standard deviations obtained by normal distribution and single sided test), see Figure 8.
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prEN 13001-3-1:2010 (E)
Key
a) principle b) simplification using one value for m (see EN 13001-1) 1 Constant stress range fatigue limit m is the slope constant of the fatigue strength curve. The curves have slopes of −1/ m in the log/log representation.
NOTE This standard is based on the use of stress history parameter s which requires the use of the one slope simplification of the log ∆σ − log N curve as shown in Figure 8 b).
Figure 8 — Illustration of ∆σ -N curve and ∆σc
In first column Annex E the values of ∆σ c are arranged in a sequence of notch classes (NC) and with thethe constant ratio ofof1,125 between the classes. For shear stresses ∆σ c is replaced by ∆τ c . The values of characteristic fatigue strength ∆σ c or ∆τ c and the related slope constants m of the log ∆σ − log N curve are given in Annex D (normative) and Annex H (informative) for: Table D.1:
36
Basic material of structural members;
prEN 13001-3-1:2010 (E)
Table D.2:
Elements of non-welded connections;
Table D.3:
Welded members;
Table H.1:
Values of slope constant m of the log ∆σ − log N -curve and limit design stress range ∆σ c for connections and joints of hollow section girders;
Table H.2:
Values of slope constant m of the log ∆σ − log N -curve and limit design stress range ∆σ c for lattice type connections of hollow section girders.
The apply one for the defined basic conditions. conditions appropriate notch class (NC)given shall values be selected or more notch classes aboveFor (+ 1deviating NC, + 2NC, ...) to an increase the resistance or below (- 1 NC, - 2 NC, ...) the basic notch class to decrease the resistance according to Annex D. The effects of several deviating conditions shall be added up. 6.2.2
Weld quality
∆σ c -values in Annex D and Annex H depend on the quality level of the weld. Quality classes B, C, D shall be in accordance with EN ISO 5817. In Annex H class C is assumed. Lower quality than level D shall not be used. For the purpose of this standard an additional quality level B* can be used. The requirements in addition to those of level B given hereafter define quality level B*.
Additional requirements for quality level B *: For the purpose of this standard 100 % NDT (non destructive testing) means inspection of the whole length of the weld with an appropriate method to ensure that the specified quality requirements are met. For butt welds: full penetration without initial (start and stop) points; both surfaces machined or flush ground down to plate surface; grinding in stress direction; the weld toe post-treated by grinding, remelting by TIG, plasma welding or by needle peening so that any
undercut and slag inclusions are removed; eccentricity of the joining plates less than 5 % of the greater thickness of the two plates; sum of lengths of concavities of weld less than 5 % of the total length of the weld; 100 % NDT.
For parallel and lap joints: transition angle of the weld to the plate surface shall not exceed 25°; the weld toe post-treated by grinding, remelting by TIG, plasma welding or by needle peening; 100 % NDT.
All other joints: full penetration; transition angle of the weld to the web surface shall not exceed 25°; the weld toe post-treated by grinding, remelting by TIG, plasma welding or by needle peening;
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prEN 13001-3-1:2010 (E)
100 % NDT; eccentricity less than 10 % of the greater thickness of the two plates.
If TIG dressing is used as a post treatment of the potential crack initialization zone of a welded joint in order to increase the fatigue strength, welds of quality class C for design purposes may be upgraded to quality class B for any joint configuration. 6.2.3
Requirements for fatigue testing
Details not given in Annex D and Annex H or consideration of mean stress influence require special investigation into ∆σ c and m by tests. Requirements for such tests are: test specimen in actual size (1:1); test specimen produced under workshop conditions; the stress cycles shall be completely in the tensile range; at least 7 tests per stress range level.
Requirements for determination of m and ∆σ c are:
∆σ c shall be determined from numbers of cycles based on mean value minus two standard deviations in a log–log presentation;
at least one stress range level that results in a mean number of stress cycles to failure of less than 2 x104
cycles shall be used;
at least one stress range level that results in a mean number of stress cycles to failure between 1,5 x10
6
and 2,5x106 cycles shall be used.
A simplified method for the determination of m and ∆σ c may be used:
m shall be set to m = 3; 5
a stress range level that results in a mean number of stress cycles to failure of less than 1 x10 cycles
shall be used. 6.3 6.3.1
Stress histories General
The stress history is a numerical presentation of all stress variations that are significant for fatigue. Using the established rules of metal fatigue the large number of variable magnitude stress cycles are condensed to one or two parameters. Stress histories shall be determined either through stress calculations or measurements, in both cases simulating the specified crane use. Stress histories shall be represented in terms of maximum stress amplitudes and frequencies of occurrence of stress amplitudes.
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prEN 13001-3-1:2010 (E)
6.3.2
Frequency of occurence of stress cycles
For the proof of fatigue strength, stress histories are expressed as single-parameter representations of frequencies of occurrence of stress ranges by using methods such as the hysteresis counting method (Rainflow or Reservoir method) with the influence of mean stress neglected. Each of the stress ranges is sufficiently described by its upper and lower extreme value. (30)
∆σ = σ u − σ b
where σ
is the upper extreme value of a stress range;
u
σ o is the lower extreme value of a stress range; ∆σ is the stress range. 6.3.3
Stress history parameter
Stress history parameter s is calculated as follows, based on a one-parameter presentation of stress histories during the design life of the crane: (31)
sm = ν × km
where km =
i
ν =
m
ni ∆σ i × N t ∆σˆ
∑
(32)
Nt
(33)
N ref
where ν
is the relative total number of occurrences of stress ranges;
km
is the stress spectrum factor dependant on m;
∆σ i
is the stress range;
∆σˆ
the maximum stress range; is the number of occurrences of stress range i ;
ni Nt =
∑i ni
is the total number of occurrences of stress ranges during the design life of the crane;
N ref = 2 × 10 6 is the reference number of cycles; m
is the slope constant of the
log ∆σ − log N -curve of the component under consideration.
Stress history parameter sm has a specific value for each structural detail. The value is related to crane duty and decisively depends on:
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prEN 13001-3-1:2010 (E)
the number of working cycles; the net load spectrum; crane configuration;
the effect of the crane motions on stress variations (traverse, slewing, luffing etc).
For thermally stress relieved or non-welded structural members the compressive portion of the stress range may be reduced to 60 %. Stress histories characterized by the same value of sm may be assumed to be equivalent in respect to the damage in similar materials, details or components. Proof of competence for fatigue may be omitted for structural members in cases, where the value of the stress history parameter is lower than 0,001 and the yield stress is 500 N/mm 2 or lower. NOTE 6.3.4
An example for the determination of stress histories by simulation is given in an Annex F. Stress history classes S
Members of crane structures may be arranged into classes S of the stress history parameter sm. The classification is based upon m = 3 and is specified in the Table 10 and illustrated in the Figure 9. Where a class S is referred to in the proof of fatigue strength of a member, the value of stress history parameter s3 shall be taken in accordance with the Table 11. Where a single stress history class S is used for the calculation of the whole structure, the most severe class occurring within the structure shall be used. Table 10 — Classes S of stress history parameter s3
NOTE
40
Class
Stress history parameter
S02
0,001 < s3 ≤ 0,002
S01
0,002 < s3 ≤ 0,004
S0
0,004 < s3 ≤ 0,008
S1
0,008 < s3 ≤ 0,016
S2
0,016 < s3 ≤ 0,032
S3
0,032 < s3 ≤ 0,063
S4
0,063 < s3 ≤ 0,125
S5
0,125 < s3 ≤ 0,250
S6 S7
0,250 < s3 ≤ 0,500 0,500 < s3 ≤ 1,000
S8
1,000 < s3 ≤ 2,000
S9
2,000 < s3 ≤ 4,000
The classes S01 and S02 do not exist in EN 13001-1 but may be used.
prEN 13001-3-1:2010 (E)
Key
1
fatigue assessment might not be required
ν
is the relative total number of occurrences of stress range
k 3 is the stress spectrum factor based on m = 3
Figure 9 — Illustration of the classification of stress history parameter s for
A given stress history falls into specific class S , independent of the slope constantm of the relevant log ∆σ / log N -curve. The diagonal lines for the class limits represent the k 3 to ν relationship for s = constant in a log/log scale diagram. 6.4
Execution of the proof
For the detail under consideration it shall be proven that: ∆σ Sd ≤ ∆σ Rd
(34)
∆σ Sd = max σ − min σ
(35)
where ∆σ Sd
maxσ, minσ ∆σ Rd
is the maximum range of design stresses, the same value that is used for ∆σˆ in 6.3.3. are the extreme values of design stresses (compression stresses with negative sign). is the limit design stress range
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Shear stresses τ are treated similarly. For each stress componentσ x , σ y and τ the proof shall be executed separately (where x,y indicate the orthogonal directions of stresses), In case of non welded details, if the normal and shear stresses induced by the same loading event vary simultaneously, or if the plane of the maximum principal stress does not change significantly in the course of a loading event, only the maximum principal stress range may be used. 6.5
Determination of the limit design stress range
6.5.1
Applicable methods
The limit design stress ranges ∆σ Rd for the detail under consideration shall be determined either by direct use of stress history parameter sm or by simplified method based on the use of classS . 6.5.2
Direct use of stress history parameter
The limit design stress range shall be calculated from: ∆σ Rd =
∆σ c γ mf × m sm
(36)
where is the limit design stress range
∆σ Rd
is the characteristic fatigue strength (see Annex D and Annex H)
∆σ c
is the slope constant of the
m
is the fatigue strength specific resistance factor (see Table 9)
γ mf
is the stress history parameter
sm 6.5.3
log ∆σ − log N curve (see Annex D and Annex H)
Use of class S Slope constant m
6.5.3.1
When the detail under consideration is related to a class S according to 6.3, the simplified determination of the limit design stress range is dependent on the (negative inverse) slope constant m of the log ∆σ –log N-curve. Slope constant m = 3
6.5.3.2
Values of stress history parameter s corresponding to individual stress history classes S are selected according to Table 11. Table 11 — Values of s 3 for stress history classes S Class
s3
NOTE
42
S02
S01
S0
S1
S2
S3
S4
S5
S6
S7
S8
S9
0,002 0,004 0,008 0,016 0,032 0,063 0,125 0,25 0,5 1,0 2,0 4,0 Values of stress history parameter s3 shown above are the upper limit values of ranges shown in Table 10.
prEN 13001-3-1:2010 (E)
The limit design stress range shall be calculated from: ∆σ Rd =
∆σ c γ mf × 3 s3
(37)
where ∆σ Rd
is the limit design stress range;
∆σ c
is the characteristic fatigue strength of details with m = 3 (see Annex D);
s3
is the classified stress history parameter (see Table 11);
γ mf
is the fatigue strength specific resistance factor (see Table 9).
For γ mf = 1,25 Annex E gives the values of ∆σ Rd in dependence on the classS and ∆σ c . 6.5.3.3
Slope constant m ≠ 3
If the slope constant m of the log ∆σ − log N curve is not equal to 3, the limit design stress range is dependent on the class S and the stress spectrum factor km (see 4.4.4 of EN 13001-1). The limit design stress range ∆σ Rd shall be calculated from: ∆σ Rd = ∆σ Rd,1 × k * ∆σ Rd,1 =
∆σ c γ mf × m s3
k k*=m 3 ≥ 1 km
(38) (39)
(40)
where ∆σ Rd
is the limit design stress range
σ Rd,1
is the limit design stress range for k* = 1
k*
is the specific spectrum ratio factor
∆σ c , m
are the characteristic values of stress range and the respective inverse slope of the log ∆σ - log N-curve (see Annex D and Annex H)
s3
is the classified stress history parameter (see Table 11)
γ mf
is the fatigue strength specific resistance factor (see Table 9)
k3 km
is the stress spectrum factor based on m = 3 is the stress spectrum factor based on m of the detail under consideration
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k 3 and km
shall be based on the same stress spectrum that is derived either from calculation or simulation
For γ mf = 1,25 and m = 5. Annex E gives the values of∆σ Rd,1 in dependence on the classS and ∆σ c . Simplified method for slope constants m ≠ 3
6.5.3.4
k* = 1 covers the most unfavourable stress spectra for cases with m > 3 and s m < 1, and ∆σ Rd,1 may then be used as limit design stress range. The value ofk* may be calculated fork3 and km from the stress spectrum
estimated by experience. 6.5.4
Independent concurrent normal and/or shear stresses
In addition to the separate proof for σ and τ (see 6.4), the action of independently varying ranges of normal and shear stresses shall be considered by: γ mf × ∆σ Sd, x ∆σ c, x
mx
γ mf × ∆σ Sd, y ∆σ c, y
× sm, x +
my
γ × ∆τ Sd × sm, y + mf ∆τ c
mτ
⋅ smτ ≤ 1,0
(41)
where ∆σ Sd , ∆τ Sd ∆σ c , ∆τ c
are the calculated maximum ranges of design stresses are the characteristic fatigue strengths is the fatigue strength specific resistance factor (see Table 9)
γ mf sm
is the stress history parameter
m
is the slope constant of
x,y
indicate the orthogonal directions of normal stresses indicates the respective shear stress
τ
7
log ∆σ − log N curve
Proof of static strength of hollow section girder joints
The proof shall be executed in accordance with Clause 7 of EN 1993-1-8:2005, if not otherwise given in Clause 8 of EN 13001-3.1.
8 8.1
Proof of elastic stability General
The proof of elastic stability is made to prove that ideally straight structural members or components will not lose their stability due to lateral deformation caused solely by compressive forces or compressive stresses. Deformations due to compressive forces or compressive stresses in combination with externally applied bending moments, or in combination with bending moments caused by initial geometric imperfections, shall be assessed by the theory of 2nd order as part of the proof of static strength. This chapter covers global buckling of members under compression and local buckling of plate fields subjected to compressive stresses.
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NOTE
8.2
Further information may be found in the bibliography.
Lateral buckling of members loaded in compression
8.2.1
Critical buckling load
The critical buckling load Nk is the smallest bifurcation load according to elastic theory. For members with constant cross section, Nk is given in Table 12 for a selection of boundary conditions, also known as Euler’s buckling cases. Table 12 — Critical buckling load Nk for Euler’s buckling cases.
Euler case no
1
2
3
4
5
π2 ×E×I
π2×E×I
2,05 × π 2 × E × I
4×π 2 × E × I
π2 × E×I
4 × L2
L2
L2
L2
L2
Boundary conditions
Nk
E I L
is the elastic modulus; is the moment of inertia of the member in the plane of the figure; is the length of the member.
For other boundary conditions or for members consisting of several parts i, with different cross sections, Nk may be computed from the differential equation, or system of differential equations, of the elastic deflection curve in its deformed state, which has the general solution: y = Ai × cos(ki × x ) + Bi × sin(ki × x ) + Ci × x + Di ,
ki =
N E × Ii
(42)
where: x
is the longitudinal coordinate;
y
is the lateral coordinate in the weakest direction of the member;
E
is the elastic modulus;
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prEN 13001-3-1:2010 (E)
is the moment of inertia of part i in the weakest direction of the member;
Ii
is the compressive force;
N Ai, Bi, Ci, Di
are constants to be found by applying appropriate boundary conditions;
The critical buckling load Nk is found as the smallest positive value N that satisfies Equation (42), or system of Equations (42), when solved with the appropriate boundary conditions applied. 8.2.2
Limit compressive design force
The limit compressive design force NRd for the member or its considered part is computed from the critical buckling load Nk by: N Rd =
κ × f yk × A
(43)
γm
where: κ
is a reduction factor;
fyk
is the compressive yield stress;
A
is the cross section area of the member.
The reduction factor κ is computed from the slenderness λ, which is given by: f yk × A
λ=
(44)
Nk
where: Nk
is the critical buckling load according to 8.2.1.
Depending on the value ofλ and the cross section parameter α, the reduction factor κ is given by: λ ≤ 0,2:
κ = 1,0
0,2 < λ ≤ 3,0:
κ=
λ > 3,0:
κ =
1 ξ + ξ 2 − λ2
[
ξ = 0,5 × 1 + α × (λ − 0,2) + λ2
1 λ × (λ + α )
Depending of the type of cross section, the parameter α is given in Table 13.
46
]
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Table 13 — Parameter α and acceptable bow imperfections for various cross sections. Buckling about axis
Type of cross section
1
Hollow sections
Hot rolled
Cold formed
2
hy t y < 30 hz t z < 30
3
Rolled sections
h b > 1,2; t ≤ 40 mm
t > 80 mm
4
Welded I sections ti ≤ 40 mm
ti > 40 mm
5
Acceptable maximum bow imperfectio n
mm
α
Acceptable maximum bow imperfectio n
0,2 1
y−y
0,3 4
L 250
0,3 4
L / 250
0,3 4
L 250
0,3 4
L / 250
0,4 9
L 200
0,4 9
L 200
z−z
y−y z−z
y−y z−z
h b > 1,2;
40 mm < t ≤ 80 mm h b ≤ 1,2; t ≤ 80 mm
α
f y ≥ 460 N 2
y−y
z−z
Thick welds and
mm
z−z
y−y
Welded box sections
f y < 460 N 2
y−y z−z y−y z−z y−y z−z y−y z−z
L 300
L 350
3
0,2 1 0,3 4 0,3 4 0,4 9 0,7 6 0,3 4 0,4 9 0,4 9 0,7 6
0,1
0,1 L 300 L 250
L 250 L 200
L 150 L 250 L 200
L 200 L 150
3 0,1 3 0,2 1 0,2 1 0.4 9 0,3 4 0,4 9 0,4 9 0,7 6
L 350 L 350
L 300 L 300
L 200 l 250 l 200
L 200 L 150
Channels, L, T and solid sections y−y z−z
0,4 9
L 200
0,4 9
L 200
NOTE : L is the length of the member
In case of a member with varying cross section, the equations in 8.2.2 shall be applied to all parts of the member. The smallest resulting value of NRd shall be used, and i n addition it shall be conform to the following:
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prEN 13001-3-1:2010 (E)
N Rd ≤
Nk
(46)
1,2 × γ m
NOTE Special consideration should be given to members with thin-walled cross sections which are susceptible to local buckling and possible reduction in their limit compressive design force NRd
8.3
Buckling of plate fields subjected to compressive and shear stresses
8.3.1
General
Plate fields are unstiffened plates that are supported only along their edges or plate panels between stiffeners. It is assumed that: geometric imperfections of the plate are less than the maximum values shown in Table 14, stiffeners are designed with sufficient stiffness and strength to allow the required buckling resistance of the plate to be developed (i.e. buckling strength of stiffeners is greater than that of the plate field), the plate field is supported along its edges as shown in Table 15. there is no instability resulting from the interaction between the local buckling of the plate field and the
global buckling of the member containing it, such case is not covered by this standard. Table 14 — Maximum allowable imperfection f for plates and stiffeners
1
2
4
3 f =
1
General
l m = a, where a ≤ 2b l m = 2b, where a > 2b
Unstiffened plates
2
lm
250
Subject to transverse compression
f =
lm
250
lm = b, where b ≤ 2a lm = 2a, where b > 2a
3
Longitudinal stiffeners in plates with longitudinal stiffening
48
f =
a
400
prEN 13001-3-1:2010 (E)
Table 14 - (continued)
4
f
f =
Transverse stiffeners in plates with longitudinal and transverse stiffening
f =
a
400 b
400
shall be measured in the perpendicular plane.
lm is the gauge length.
Figure 10 shows a plate field with dimensions a and b (side ratioα = a/b). It is subjected to longitudinal stress varying between σ x (maximum compressive stress) and ψ .σ x along its end edges, coexistent shear stress τ and with coexistent transverse stress σ y ,(e.g. from wheel load, see Annex C.4) applied on one side only.
Figure 10 — Stresses applied to plate field Limit design stress with respect to longitudinal stress σ x
8.3.2
The limit design compressive stress fb,Rd,x is calculated from: f b,Rd, x =
κ x × f yk γm
(47)
where: κx
is a reduction factor according to Equation (48);
fyk
is the minimum yield stress of the plate material.
The reduction factor κ is given by:
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1 0,22 κx = c × − 1,0
with c = 1,25 − 0,12 ×ψ
,
673 λ x > 0,
673
(48)
λ x ≤ 0,
c ≤ 1,25
where: λx
is a non-dimensional plate slenderness according to Equation (49);
ψ
is the edge stress ratio of the plate, relative to the maximum compressive stress.
The non-dimensional plate slendernessλx is given by: λx =
f yk
(49)
kσ × σ e
where: σe
is a reference stress according to Equation (50);
kσ
is a buckling factor given in Table 14.
The reference stress σe is given by: σe =
π2 ×E
t × 12 × (1 − υ ) b
2
2
(50)
where: Ε
is the elastic modulus of the plate;
ν
is the Poisson’s ratio of the plate;
t b
is the plate thickness; is the width of the plate field.
The buckling factor kσ depends on the edge stress ratioψ, the side ratio α and the edge support conditions of the plate field. Table 15 gives values for the buckling factor kσ for plate fields supported along both transverse and longitudinal edges (Case 1) and plate fields supported along both transverse edges but only along one longitudinal edge (Case 2).
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Table 15 — Buckling factor kσ
Case 1
Case 2
Supported along all four edges Supported along both loaded (end) edges and along only one longitudinal edge.
Type of support
1
Stress
2
distribution 3
ψ =1
4
1>ψ > 0
5
4
0,43
8,2
0,578
ψ + 1,05
ψ + 0,34
ψ =0
7,81
1,70
0,57
6
0 > ψ > −1
7,81 − 6,29ψ + 9,78ψ 2
1,70 − 5ψ + 17,1ψ 2
0,57 − 0,21ψ + 0,07ψ 2
7
ψ = −1
23,9
23,8
0,85
23,8
0,57 − 0,21ψ + 0,07ψ 2
ψ < −1
8 NOTE
5.98 x (1-ψ)
2
0,57 − 0,21ψ + 0,07ψ 2
For Case 1 the values and equations for buckling factors kσ given in Table 14 for plate fields supported along
all four edges can give overly conservative results for plate fields with α < 1,0 for rows 3 to 6 and α < 0,66 for row 7. For Case 2 the results can be overly conservative for plate fields with α < 2,0 . Further information regarding alternative values for short plate fields can be found in additional references, see bibliography. 8.3.3
Limit design stress with respect to transverse stress σ y
The limit design transversal normal stress shall be calculated from: κ y . f yk f b, Rd , y =
γm
(51)
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κy
is a reduction factor according to Equation (52);
f yk
is the minimum yield stress of the plate material.
The reduction factor κ y is given by: 1 0,22 κ y = 1,13 × − for λy λ2y κ y = 1,0 for
831 831
λ y > 0,
(52)
λ y ≤ 0,
The non-dimensional plate slendernessλ y is given by:
λy =
f yk kσ × σ e ×
a c
(53)
where:
52
σe
is a reference stress according to Equation (50);
kσ
is a buckling factor determined using figure 10;
a
is the plate field length
c
is the width over which the transverse load is distributed c( = 0 , corresponds to a point load)
prEN 13001-3-1:2010 (E)
Figure 11 — Buckling factor kσ 8.3.4
Limit design stress with respect to shear stress
The limit design buckling shear stress is calculated from: κτ . f yk f b, Rd ,τ =
3 .γ m
τ
(54)
where κτ is a reduction factor given by: κτ =
0,84
or
λτ
84
f
λτ ≥ 0,
(55)
κτ = 1 f or λτ < 0,84
where λτ =
f yk kτ .σ e . 3
(56)
f yk is the minimum yield strength of the plate material
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kτ is a buckling factor calculated (for a plate field supported along all four edges) using equations given in table 16. Table 16 — Buckling factor
kτ kτ
α
4
α>1
kτ = 5,34 +
α≤1
kτ = 4 + 2 α
α2
5,34
8.4
Execution of the proof
8.4.1
Members loaded in compression
For the member under consideration, it shall be proven that: (57)
N Sd ≤ N Rd
where: NSd
is the design value of the compressive force;
NRd
is the limit design compressive force according to 8.2.2.
8.4.2
Plate fields
8.4.2.1
Plate fields subjected to longitudinal or transverse compressive stress
For the plate field under consideration, it shall be proven that: σ Sd, x ≤ f b,Rd, x
and σ Sd,y ≤ f b,Rd, y
(58)
where: σSd,x , σSd,y
are the design values of the compressive stresses σ x or σ y ;
fb,Rd,x , fb,Rd,y
are the limit design compressive stresses in accordance with 8.3.2 and 8.3.3
8.4.2.2 Plate fields subjected to shear stress
For the plate field under consideration, it shall be proven that: τ Sd ≤ f b,Rd,τ
where: τ Sd
is the design value of the shear stress;
f b,Rd,τ is the limit design shear stress in accordance with 8.3.4.
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(59)
prEN 13001-3-1:2010 (E)
8.4.2.3 Plate fields subjected to coexistent normal and shear stresses
For the plate field subjected to coexistent normal (longitudinal and/or transverse) and shear stresses, apart from a separate proof carried out for each stress component in accordance with 8.4.2.1 and 8.4.2.2, it shall be additionally proven that: σ Sd, x f b, Rd , x
e1
σ Sd, y f b, Rd , y
+
e2
σ Sd, x .σ Sd, y f b, Rd , x . f b, Rd , y
− V ×
τ + Sd f b, Rd ,τ
e3
≤1
(60)
where e1 = 1 + κ x4
(61)
e2 = 1 + κ y4
(62)
e3 = 1 + κ x × κ y × κτ2
(63)
and with κ x calculated in accordance with 8.3.2, κ y in accordance with 8.3.3 and κτ in accordance with 8.3.4. 6
V = (κ x × κ y ) V = −1
for for
0 σ Sd , x × σ Sd , y > 0
(64)
σ Sd , x × σ Sd , y <
55
prEN 13001-3-1:2010 (E)
Annex A
(informative) Limit design shear force Fv,Rd per fit bolt and per shear plane for multiple shear plane connections
Table A.1 — Limit design shear force Fv,Rd per fit bolt and per shear plane for multiple shear plane connections
Fv,Rd Fit bolt
Shank diameter
kN
mm
Fit bolt material for γRb = 1,1 4.6
5.6
M12
13
16,7
20,9
M16
17
28,6
M20
21
43,5
M22
23
M24 M27 M30
8.8
10.9
12.9
44,6
62,8
75,4
35,7
76,2
107,2
128,6
54,4
116,2
163,2
196,1
52,2
65,3
139,4
196,0
235,2
25
61,8
77,3
164,9
231,9
278,3
28
77,6
97,0
206,9
291,0
349,2
31
95,1
111,8
253,6
356,6
428,0
Table A.2 — Limit design shear force Fv,Rd in the shank per standard bolt and per shear plane for multiple shear plane connections
Fv,Rd kN Bolt
Shank diameter
Bolt material for γ Rb = 1,1
mm
56
4.6
5.6
8.8
10.9
12.9
M12
12
14,2
17,8
37,9
53,4
64,1
M16 M20
16 20
25,3 39,5
31,6 49,4
67,5 105,5
94,9 148,4
113,9 178,0
M22
22
47,8
59,8
127,6
179,5
215,4
M24
24
56,9
71,2
151,9
213,6
256,4
M27
27
72,1
90,1
192,3
270,4
324,5
M30
30
89,0
111,3
237,4
333,9
400,6
prEN 13001-3-1:2010 (E)
Annex B
(informative) Preloaded bolts
Table B.1 — Tightening torques in Nm to achieve the maximum allowable preload level 0,7 × Fy Bolt size
Bolt material
8.8
10.9
12.9
M12
86
122
145
M14
136
190
230
M16
210
300
360
M18
290
410
495
M20
410
590
710
M22
560
790
950
M24
710
1 000
1 200
M27
1 040
1 460
1 750
M30
1 410
2 000
2 400
M33
1 910
2 700
3 250
M36
2 460
3 500
4 200
Note A friction coefficient µ = 0,14 is assumed in the calculations of the preceding tightening torques.
57
prEN 13001-3-1:2010 (E)
Table B.2 — Limit design slip force FS,Rd per bolt and per friction interface using a design preloading force Fp,d = 0,7 × f yb × As Bolt
stress area
Design preloading force Fp,d in kN
AS
Bolt material
Limit design slip force Fs,Rd in kN
γm = 1.1, γss = 1.14
mm 2 Bolt material
58
8.8
10.9
12.9
Slip factor :
Slip factor :
Slip factor :
8.8
10.9
12.9
0.50
0.40
0.30
0.20
0.50
0.40
0.30
0.20
0.50
0.40
0.30
0.20
M12
84,3
37,8
53,1
63,7
15,1
12,0
9,0
6,0
21,2
16,9
12,7
8,5
25,4
20,3
15,2
10,2
M14
115
51,5
72,5
86,9
20,5
16,4
12,3
8,2
28,9
23,1
17,3
11,6
34,7
27,7
20,8
13,9
M16
157
70,3
98,9
119
28,0
22,4
16,8
11,2
39,4
31,6
23,7
15,8
47,3
37,9
28,4
18,9
M18
192
86,0
121
145
34,3
27,4
20,6
13,7
48,2
38,6
28,9
19,3
57,9
46,3
34,7
23,2
M20
245
110
154
185
43,8
35,0
26,3
17,5
61,5
49,2
36,9
24,6
73,9
59,1
44,3
29,5
M22
303
136
191
229
54,1
43,3
32,5
21,6
76,1
60,9
45,7
30,4
91,3
73,1
54,8
36,5
M24
353
158
222
267
63,1
50,4
37,8
25,2
88,7
70,9
53,2
35,5
106
85,1
63,8
42,6
M27
459
206
289
347
82,0
65,6
49,2
32,8
115
92,2
69,2
46,1
138
111
83,0
55,3
M30
561
251
353
424
100
80,2
60,1
40,1
141
113
84,6
56,4
169
135
101
67,6
M33
694
311
437
525
124
99,2
74,4
49,6
174
139
105
69,7
209
167
126
83,7
M36
817
366
515
618
146
117
87,6
58,4
205
164
123
82,1
246
197
148
98,5
prEN 13001-3-1:2010 (E)
Annex C
(normative) Design weld stress σW,Sd and τW,Sd C.1 Butt joint Normal weld design stress σ W ,Sd and shear weld design stress τ W ,Sd are calculated from: σ W,Sd =
Fσ ar × lr
; τ W,Sd =
Fτ
(C.1)
ar × lr
where Fσ
is the acting normal force (see Figure C.1);
Fτ
is the acting shear force (see Figure C.1);
ar
is the effective weld thickness;
lr
is the effective weld length.
Figure C.1 — Butt weld
The effective weld thickness a r is calculated from: a r ≤ min(t1,t 2 )
for full penetration welds
a r = 2 × ai
for double sided symmetrical partial penetration welds
where ai NOTE
is the thickness of either welds Single sided partial penetration butt welds with transverse loads are not covered by this standard.
In general, the effective weld length lr is given by: l r = lW − 2 × ar
(for continuous welds)
unless measures are taken to ensure that the whole weld length is effective, in which case lr = l W 59
prEN 13001-3-1:2010 (E)
where is the weld length (see Figure C.1);
lW ar
is the effective weld thickness.
t1 , t2
thicknesses of the plates.
C.2 Fillet weld Normal weld design stress σ W, Sd and shear weld design stress τ W, Sd are calculated from: σ W,Sd =
Fσ ar1 × lr1 + ar2 × lr2
F
τ , τ W,Sd = ar1 × lr1 + ar2 × lr2
(C.2)
where Fσ
is the acting normal force (see Figure C.2);
Fτ
is the acting shear force (see Figure C.2);
ari
are the effective weld thicknesses (see Figure C.2); with ari = ai
lri
are the effective weld lengths.
Figure C.2 — Joint dimensions
The effective weld thickness ar is limited to: ar ≤ 0,7 × min( t1, t 2 ) .
For the effective weld lengths see C.1. Single sided welds may be used loaded with forces as shown in Figure C.2. For single sided welds, σ W ,Sd and τ W ,Sd are calculated in an analogous manner using the relevant weld parameters. 60
prEN 13001-3-1:2010 (E)
C.3 T-joint with full and partial penetration Normal weld design stress σ W, Sd and shear weld design stress τ W, Sd are calculated from: σ W, Sd =
Fσ ar1 × lr1 + ar2 × lr2
, τ W,Sd =
Fτ ar1 × lr1 + ar2 × lr2
(C.3)
where F
is the acting normal force (see Figure C.3);
σ
Fτ
is the acting shear force (see Figure C.3);
ari
are the effective weld thicknesses (see Figure C.3); with ari = ai + ahi
lri
are the effective weld lengths.
Figure C.3 — Joint dimensions
The effective weld thickness ar is limited to: ar ≤ 0,7 ⋅ min( t1, t 2 ) .
For the effective weld lengths see C.1. Single sided welds may be used loaded with forces as shown in Figure C.3. For single sided welds, σ W, Sd and τ W, Sd are calculated in an analogous manner using the relevant weld parameters.
C.4 Effective distribution length under concentrated load For simplification the normal design stresses in the weld and parent material under concentrated load may be calculated using the effective distribution length as follows l r = 2 × hd × tan κ + λ
(C.4) 61
prEN 13001-3-1:2010 (E)
where lr hd
λ
is the effective distribution length ; is the distance between the section under consideration and contact level of acting load ; is the length of the contact area. For wheels λ may be set to: λ = 0,with 2× r
λmax mm = 50
where
r
is the radius of wheel;
κ
is the dispersion angle.
shall be set to κ ≤ 45° .
Figure C.4 — Concentrated load
Other calculations for the determination of the design stresses may be used, however the values for ∆σ c and ∆τ c in Annex D are based on the calculation presented herein.
62
prEN 13001-3-1:2010 (E)
Annex D
(normative) Values of slope constant m and characteristic fatigue strength ∆σc, ∆τc
Notch classes (NC) refer to the first column of Annex E (see 6.2.1). Table D.1 — Basic material of structural members Detail No.
∆σ c ∆τc
Constructional detail
N/mm2
Requirements
General requirements: Rolled surfaces No geometrical notch
effects (e.g. cut outs) m=5
Surface roughness
values before surface treatment such as shot blasting Plates, flat bars, rolled profiles under normal stresses -
1.1
140
Independent of fy
140
180 ≤
fy
160
220 <
fy
≤
320
180
320 <
fy
≤
500
≤
220
-
-
200
500 <
-
fy
-
180
180 ≤
fy
200
220 <
225
320 <
fy fy
250
500 <
280 315
≤
220
≤
320
≤
500
fy
≤
650
650 <
fy
≤
900
900 <
fy
-
-
Surface condition in accordance with EN10163 classes A1 or C1 (repair welding allowed) Surface condition in accordance with EN10163 classes A3 or C3 Surface roughness Rz ≤ 100µm Edges rolled or machined or no free edges Any burrs and flashes removed from rolled edges Surface roughness Rz ≤ 60 µm +1 NC Surface condition in accordance with EN10163 classes A3 or D3 Surface roughness Rz ≤ 20µm Edges machined or no free edges
63
prEN 13001-3-1:2010 (E)
Table D.1 - Continued Detail No.
1.2
∆σ c ∆τ c
Constructional detail
N/mm2
Requirements -
General requirements: Rolled surfaces Thermal cut edges No geometrical notch effects (e. g. cutouts)
-
Surface roughness valuessuch before surface treatment as shot blasting
-
Surface condition in accordance with EN10163 classes A1 or C1 (repair welding allowed) Edge quality in accordance with Table 5 Range 3 of EN ISO 9013 Edge quality in accordance with Table 5 Range 3 of EN ISO 9013 Surface condition in accordance with EN10163 classes A3 or C3 Surface roughness
m=5
Edges in plates, flat bars, rolled profiles under normal stresses
140
Independent of f y -
-
140
180 ≤
fy
≤
220 -
160
220 <
fy
≤
500
-
180
500 <
fy
160
180 ≤
fy
≤
220
180
220 <
fy
≤
320
200
320 <
fy
≤
500
225
500 <
fy
≤
650
-
250
650 <
fy
≤
900
-
280
900 <
fy
-
-
-
64
Rz ≤ 100µm Mill scale removed before cutting Machine controlled cutting Plate surface roughness Rz ≤60µm and edge quality in accordance with Table 5 Range 2 of EN ISO 9013 +1NC Edge quality in accordance with Table 5 Range 1 of EN ISO 9013 Surface condition in accordance with EN10163 classes A3 or C3 Plate surface roughness Rz ≤20µm Mill scale removed before cutting Machine controlled cutting
prEN 13001-3-1:2010 (E)
Table D.1 - Continued Detail No.
∆σ c ∆τ c
Constructional detail
N/mm2
Requirements
General requirements: Nominal stress calculated for the net cross-section - Holes not flame cut, Bolts may be present as long as these are stressed to no more than 20 % of their strength in shear/ bearing connections or to no more than 100 % of their strength in slipresistant connections
m=5
Hole edges in a plate under normal stresses
1.3 80
Independent of fy
100
180 <
fy
≤
220
112
220 <
fy
≤
320
125
320 <
fy
≤
500
140
500 <
fy
≤
650
160
650 <
fy
-
-
-
Holes may be punched Holes machines or thermal cut to a quality in accordance with Table 5 Range 3 of EN ISO 9013 Holes not punched Burr on hole edges removed Rolled surface condition in accordance with EN 10163 classes A3 or C3 Plate surface roughness Rz ≤100µm
65
prEN 13001-3-1:2010 (E)
Table D.1 - Concluded Detail No.
∆σ c ∆τ c
Constructional detail
N/mm2
Requirements
General requirements: Rolled surfaces No geometrical notch effects (e.g. cut outs) - Surface roughness values before -
m=5
surface blasting treatment such as shot
Plates, flat bars, rolled profiles under shear stress -
90
Independent of fy
90
180 ≤
fy
≤
220
-
100
220 <
fy
≤
320
-
112
320 <
fy
≤
500
-
125
500 <
fy
1.4
-
125
fy 220 < fy
140
320 <
160
≤
220
-
≤
320
-
fy
≤
500
500 <
fy
≤
650
180
650 <
fy
≤
900
200
900 <
fy
112
66
180 ≤
-
Surface condition in accordance with EN10163 classes A1 or C1 (repair welding allowed) Surface condition in accordance with EN10163 classes A3 or C3 Surface roughness Rz ≤ 100µm Edges rolled or machined or no free edges Any burrs and flashes removed from rolled edges Surface roughness Rz ≤ 60 µm +1 NC
Surface condition in accordance with EN10163 classes A3 or D3 Surface roughness Rz ≤ 20µm Edges machined or no free edges -
prEN 13001-3-1:2010 (E)
Table D.2 —Elements of non-welded connections Detail No.
∆σ c ∆τ c
Constructional detail
N/mm2
Requirements
Double shear
Supported single-shear (example)
The proof of fatigue
strength is not required for bolts of friction grip type bolted connections
m=5 2.1
Nominal stress
Single-shear
calculated for the net cross-section Perforated parts in slip-resistant bolted connections under normal stresses
2.2
160
f y ≤ 275
180
275 < f y
m=5 180
2.3
m=5 125 m=5
2.4
2.6
NOTE
Nominal stress
calculated for the net cross-section
double-shear and supported single-shear Normal stress Perforated parts in shear/bearing connections under normal stresses
Nominal stress
calculated for the net cross-section
single-shear joints, not supported Normal stress Fit bolts in double-shear or supported single-shear joints
125
Shear stress (∆τc)
355
Bearing stress (∆σc)
m=5 2.5
Perforated parts in shear/bearing connections under normal stresses
Fit bolts in single-shear joints, not supported
100
Shear stress (∆τc)
250
Bearing stress (∆σc)
m=3 50
Threaded bolts loaded in tension (bolt grade 8.8 or better) Machined thread
63
Rolled thread above M30
71
Rolled thread for M30 or smaller
Uniform distribution
of stresses is assumed Uniform distribution
of stresses is assumed
∆σ calculated for the
stress-area of the bolt, using ∆Fb (see 5.2.3.3)
Pinned connections are considered in the proof of fatigue strength as structural members.
67
prEN 13001-3-1:2010 (E)
Table D.3 — Welded members Detail No.
∆σ c ∆τ c
N/mm2
Constructional detail
Requirements
Basic conditions: symmetric plate arrangement fully penetrated weld
Components with usual residual stresses
Angular misalignment < 1° t1 = t2
or m=3
slope <1:3
Symmetric butt joint, normal stress across the weld 3.1
Special conditions:
Components with considerable residual stresses (e. g. joint of components with restraint of shrinkage) -1 NC
140
Butt weld, quality level B*
-2 NC
125
Butt weld, quality level B
-4 NC
112
Butt weld, quality level C
- 4 NC Basic conditions: symmetric plate arrangement fully penetrated weld
3.2
m=3
Components with usual residual stresses
Angular misalignment < 1°
Special conditions: Symmetric butt joint, normal stress across the weld 80
68
Butt weld on remaining backing, quality level C
Components with considerable residual stresses (e. g. joint of components with restraint of shrinkage) -1 NC
prEN 13001-3-1:2010 (E)
Table D.3 - Continued Detail No.
∆σc ∆τ c
N/mm2
Constructional detail
Requirements
Basic conditions: fully penetrated weld
Supported parallel to butt weld: e < 2⋅t2 + 10mm
Supported vertical to butt weld:
e < 12⋅t2 Components with usual residual stresses
slope ≤ 1:3
m=3
t2 - t1 ≤ 4 mm
3.3 Unsymmetrical supported butt joint, normal stress across the butt weld
Special conditions:
Components with considerable residual stresses (e. g. joint of components with restraint of shrinkage) -1 NC
Influence of slope and thickness t 2-t1: thickness t 2
125
Butt weld, quality level B*
112
Butt weld, quality level B
100
Butt weld, quality level C
slope ≤4 – ≤1:3 ≤1:2 -1NC ≤1:1 -1NC >1:1 - -2NC
≤ 10
-1NC -1NC -2NC -2NC
− t1 ≤50 -1NC -2NC -2NC -3NC
> 50 -2NC -2NC -3NC -3NC
Basic conditions: fully penetrated weld
supported parallel to butt weld:
supported vertical to butt weld:
e < 2⋅t2 + 10mm
e < 12⋅t2
3.4
m=3
components with usual residual stresses
Unsymmetrical supported butt joint, normal stress across the butt weld
t2 - t1 ≤ 10 mm
Special conditions:
components with considerable residual stresses (e. g. joint of components with restraint of shrinkage) -1 NC
t2 - t1 > 10 mm
-1 NC
69
prEN 13001-3-1:2010 (E)
Table D.3 - Continued Detail No.
∆σc ∆τ c
Constructional detail
80
Butt weld on remaining backing, quality level C
N/mm2
Requirements
Basic conditions: fully penetrated weld
components with usual residual stresses slope ≤ 1:1 slope in weld or base material
t1/t2 > 0,84
m=3
Special conditions:
3.5
components with considerable residual stresses (e. g. joint of components with restraint of shrinkage)
Unsymmetrical unsupported butt joint, stress across the butt weld -1 NC
-2 NC 100
Butt weld, quality level B*
t1/> t2 0,74
-1 NC
90
Butt weld, quality level B
t1/> t2 0,63
-2 NC
t1/> t2 0,50
-3 NC
t1/> t2 0,40
-4 NC
80
Butt weld quality level C
Basic conditions: components with usual residual stresses
m=3 3.6 Butt joint with crossing welds, stress across the butt weld
70
125
Butt weld, quality level B*
100
Butt weld, quality level B
90
Butt weld, quality level C
prEN 13001-3-1:2010 (E)
Table D.3 - Continued Detail No.
∆σ c ∆τ c
N/mm2
Constructional detail
Requirements
Special conditions: no irregularities from start-
stop-points in quality level C + 1 NC
m=3
3.7 Normal stress in weld direction 180
welding with restraint of shrinkage - 1 NC
Continuous weld, quality level B
140
Continuous weld, quality level C
80
Intermittent weld, quality level C Basic conditions: continuous weld
Special conditions: automatic welding, no initial
m=3
points NC
+1
welding with restraint of
3.8 Cross or T-Joint, groove weld, normal stress across the weld 112
K-weld, quality level B*
100
K-weld, quality level B
80
K-weld, quality level C
71
V-weld with full penetration and backing, quality level C
shrinkage - 1 NC
Basic conditions: continuous weld
Special conditions: 3.9
automatic welding, no initial
m=3
points NC
+1
welding with restraint of
shrinkage NC
-1
Cross or T-Joint, symmetric double fillet weld
71
prEN 13001-3-1:2010 (E)
Table D.3 - Continued Detail No.
∆σc ∆τ c
Constructional detail
N/mm2 45
Stress in weld throat
71
Quality level B
63
Quality level C
Requirements
σ w = F /( 2 × a × l ) see Annex C Stress in the loaded plate at weld toe
m=3
3.10 T-Joint, stresses from bending Stress calculated with the applied bending moment and weld joint geometry taken into account
45
Stress in weld throat
80
Stresses in plate at weld toe, Quality level B
71
Stresses in plate at weld toe, Quality level C
m=3 3.11
Full penetration weld (double sided) with transverse compressive load (e. g. wheel)
72
112
Quality level B
100
Quality level C
prEN 13001-3-1:2010 (E)
Table D.3 - Continued Detail No.
3.12
∆σc ∆τ c
Constructional detail
N/mm2
Requirements
m=3
Full penetration weld (with backing) with transverse compressive load (e. g. wheel) 80
3.13
Quality level C
0,5 ⋅ t ≤ a ≤ 0,7 ⋅ t
m=3
Double fillet weld with transverse compressive load, (e. g. wheel), stress calculated in the plate 71
Quality level C
0,5 ⋅ t ≤ a ≤ 0,7 ⋅ t with a according to Annex C 3.14
m=3
p=1mm for t≤6mm t p≥ 4
for t>6mm
Partial penetration weld with transverse compressive load (e. g. wheel), stress calculated in the plate 71
Quality level C
73
prEN 13001-3-1:2010 (E)
Table D.3 - Continued Detail No.
∆σ c ∆τ c
Constructional detail
N/mm2
Requirements
0,5 × t ≤ a ≤ 0,7 × t
with a according to Annex C 3.15
m=3
p=1mm for t ≤ 6mm
p≥
t 4
for t > 6mm
Partial penetration weld with transverse load (e. g. underslung crab), stress calculated in the plate 63
Quality level C Basic conditions: quality level C continuous weld distance c between the
weld toe and rim of continuous component greater than 10 mm Special conditions:
m=3
quality level B
*
+2
NC
3.16
quality level B
Continuous component with a welded cover plate
+1
NC quality level D
-1
NC
c < 10 mm
NC
74
80
l ≤ 50 mm
71
50 mm < l ≤ 100 mm
63
l > 100 mm
-1
prEN 13001-3-1:2010 (E)
Table D.3 - Continued Detail No.
∆σc ∆τ c
N/mm2
Constructional detail
Requirements
Basic conditions: m=3
continuous fillet or
groove weld 3.17
Continuous component with load carrying flange plate, stress in continuous component at end of connection 112
Flange plate with end chamfer ≤ 1:3; edge weld and end of flank weld in weld quality level B*
100
Flange plate with end chamfer ≤ 1:2; edge weld and end of flank weld in weld quality level B*
Basic conditions: 3.18
continuous fillet or
m=3
groove weld
to ≤ 1,5 tu
Continuous component with load carrying flange plate, stress in continuous component at end of connection 80
Edge weld and end of flank weld in weld quality level B*
75
prEN 13001-3-1:2010 (E)
Table D.3 - Continued Detail No.
∆σ c ∆τc
Constructional detail
N/mm2
Requirements
Basic conditions: continuous fillet or groove weld
m=3 3.19
Continuous component with load carrying flange plate, stress in continuous component at end of connection 63
Quality level B
56
Quality level C Basic conditions: stressed area to be
calculated from: m=3
As = t × lr lr = min( bm , bL + l )
3.20
see also detail 3.32 Overlapped welded joint, main plate 80
Quality level B*
71
Quality level B
63
Quality level C
m=3 Basic conditions: stressed area to be
3.21
calculated from:
As = bL × (tL1 + tL 2 ) 50 Overlapped welded joint, lap plates
76
prEN 13001-3-1:2010 (E)
Table D.3 - Continued Detail No.
∆σ c ∆τc
Constructional detail
N/mm2
Requirements
Basic conditions:
R ≥ 50 mm; α ≤ 60° for
quality levels B or C
R ≥ 150 mm; α ≤ 45°
for quality level B*
groove weld or allround
m=3
fillet weld Special conditions:
3.22 Continuous component with longitudinally mounted parts, Parts rounded or chamfered 90
Quality level B*
80
Quality level B
71
Quality level C
end welds in a zone of at least 5 t fully penetrated +1 NC
Basis conditions: allround fillet weld quality level B, C
m=3
Special conditions: single fillet weld -1 NC
3.23
Continuous component with parts ending perpendicularly 80
l ≤ 50 mm
71
50 mm < l ≤ 100 mm
63
100 mm < l ≤ 300 mm
56
l > 300 mm
weld quality level D -1 NC
Basic conditions:
R ≥ 50 mm or α ≤ 60°
t2 ≤ t1
butt weld or all-round
fillet weld Special conditions: 3.24
m=3
R ≥ 150 mm or α ≤ 45°
R < 50mm or α > 60°
end welds in a zone of at least 5 t2 fully penetrated with quality level B* +1 NC
+1 NC -2 NC Continuous component with longitudinally mounted parts, welded to edge
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prEN 13001-3-1:2010 (E)
Table D.3 - Continued Detail No.
∆σ c ∆τ c
Constructional detail
N/mm2 80
Quality level B
71
Quality level C
Requirements
Basic conditions
c ≥ 10 mm
quality level C
m=3
Special conditions: 3.25
Continuous component with overlapping parts
b ≤ 50 mm and quality level B +1 NC
80
b ≤ 50 mm
quality level D
71
50 mm < b ≤ 100 mm
63
b > 100 mm
c< 10 mm
-1 NC -1 NC
Basic conditions: plate thickness t ≤ 12 mm
c ≥ 10 mm
quality level D not
m=3
allowed for K-weld Special conditions: plate thickness t > 12 mm
3.26
(Double fillet welds only) 1 NC
Continuous component to which parts are welded transversally 112
Double fillet weld, quality level B*
100
Double fillet weld, quality level B
90
Double fillet weld, quality level C
71
Single fillet weld, quality level B, C
71
Partial penetration V-weld on remaining backing, quality level B, C
c< 10 mm
-1 NC
K-weld instead of double
fillet weld NC
+1
quality level D instead of C-1 NC
Basic conditions: plate thickness t ≤ 12 mm
c ≥ 10 mm
Special conditions: plate thickness t > 12 mm
3.27
(double fillets only)
m=3
Continuous component to which stiffeners are welded transversally
78
-1 NC
c< 10 mm
-1 NC K-weld instead of double fillet weld +1 NC quality level D instead of C -1 NC
prEN 13001-3-1:2010 (E)
Table D.3 - Continued Detail No.
∆σ c ∆τ c
Constructional detail
N/mm2 112
Double fillet weld, quality level B*
100
Double fillet weld, quality level B
90
Double fillet weld, quality level C
71
Single fillet weld, quality level B, C
71
Partial penetration V-weld on remaining backing, quality level B, C
Requirements
m=3 3.28 Continuous component to which transverse parts or stiffeners are welded intermittently 63
Quality level C
50
Quality level D
For parts rounded or chamfered: Basic conditions:
3.29
R ≥ 50 mm, α ≤ 60°
Special conditions:
m=3
R ≥ 100 mm, α ≤ 45°
end welds in the zone of at least 5 t fully penetrated +2 NC
+1 NC
Continuous component with longitudinally mounted parts, parts through hole 80
Parts rounded or chamfered
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prEN 13001-3-1:2010 (E)
Table D.3 - Continued Detail No.
∆σc ∆τ c
Constructional detail
N/mm2 56
Requirements
Parts ending perpendicularly
Basic conditions: quality level C groove weld fully
penetrated m=3
fillet weld thickness a >
0,7 tube thickness flange thickness greater
3.30
than two times tube thickness (for middle figure)
Tubes under axial and bending loads, normal stresses calculated in the tube
Special conditions:
80
Butt weld, cylindrical tube (case a)
quality B
63
Groove weld, cylindrical tube (case b)
56
Groove weld, rectangular tube (case b)
45
Double fillet weld, cylindrical tube (case c)
40
Double fillet weld, rectangular tube (case c)
+1 NC
quality B* +2 NC
Basic conditions: quality level C components with usual
residual stresses m=5
Special conditions:
3.31
components with
considerable residual stresses (e. g. joint of components with restraint of shrinkage) -1 NC
Continuous groove weld, single or double fillet weld under uniform shear flow
80
112
With full penetration
90
Partial penetration
no initial points +1 NC
prEN 13001-3-1:2010 (E)
Table D.3 - Continued Detail No.
∆σc ∆τ c
Constructional detail
N/mm2
Requirements
Basic conditions: 3.32
m=5
load is assumed to be transferred by longitudinal welds only
Weld in lap joint, shear with stress concentration 71
Quality level B
63
Quality level C
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prEN 13001-3-1:2010 (E)
Annex E
(normative) Calculated values of limit design stress range ∆σRd
One row is representing a notch class (NC) for basic conditions. +1 NC is one line above, -1 NC is one line below. Table E.1 — Details with m = 3 and NC, ∆σc
γ mf = 1,25
∆σRd
2
2
N/mm
N/mm S02
S01
S0
S1
S2
S3
S4
S5
S6
S7
S8
S9
355
2254,1
1789,1
1420,0
1127,1
894,5
713,7
568,0
450,8
357,8
284,0
225,4
178,9
315
2000,1
1587,5
1260,0
1000,1
793,8
633,3
504,0
400,0
317,5
252,0
200,0
158,8
280
1777,9
1411,1
1120,0
888,9
705,6
562,9
448,0
355,6
282,2
224,0
177,8
141,1
250
1587,4
1259,9
1000,0
793,7
630,0
502,6
400,0
317,5
252,0
200,0
158,7
126,0
225
1428,7
1133,9
900,0
714,3
567,0
452,4
360,0
285,7
226,8
180,0
142,9
113,4
200
1269,9
1007,9
800,0
635,0
504,0
402,1
320,0
254,0
201,6
160,0
127,0
100,8
180
1142,9
907,1
720,0
571,5
453,6
361,9
288,0
228,6
181,4
144,0
114,3
90,7
160 140
1015,9 888,9
806,3 705,6
640,0 560,0
508,0 444,5
403,2 352,8
321,7 281,5
256,0 224,0
203,2 177,8
161,3 141,1
128,0 112,0
101,6 88,9
80,6 70,6
125
793,7
630,0
500,0
396,9
315,0
251,3
200,0
158,7
126,0
100,0
79,4
63,0
112
711,2
564,4
448,0
355,6
282,2
225,2
179,2
142,2
112,9
89,6
71,1
56,4
100
635,0
504,0
400,0
317,5
252,0
201,1
160,0
127,0
100,8
80,0
63,5
50,4
90
571,5
453,6
360,0
285,7
226,8
180,9
144,0
114,3
90,7
72,0
57,1
45,4
80
508,0
403,2
320,0
254,0
201,6
160,8
128,0
101,6
80,6
64,0
50,8
40,3
71
450,8
357,8
284,0
225,4
178,9
142,7
113,6
90,2
71,6
56,8
45,1
35,8
63
400,0
317,5
252,0
200,0
158,8
126,7
100,8
80,0
63,5
50,4
40,0
31,8
56
355,6
282,2
224,0
177,8
141,1
112,6
89,6
71,1
56,4
44,8
35,6
28,2
50
317,5
252,0
200,0
158,7
126,0
100,5
80,0
63,5
50,4
40,0
31,7
25,2
45
285,7
226,8
180,0
142,9
113,4
90,5
72,0
57,1
45,4
36,0
28,6
22,7
40
254,0
201,6
160,0
127,0
100,8
80,4
64,0
50,8
40,3
32,0
25,4
20,2
36
228,6
181,4
144,0
114,3
90,7
72,4
57,6
45,7
36,3
28,8
22,9
18,1
32
203,2
161,3
128,0
101,6
80,6
64,3
51,2
40,6
32,3
25,6
20,3
16,1
28
177,8
141,1
112,0
88,9
70,6
56,3
44,8
35,6
28,2
22,4
17,8
14,1
25
158,7
126,0
100,0
79,4
63,0
50,3
40,0
31,7
25,2
20,0
15,9
12,6
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prEN 13001-3-1:2010 (E)
Table E.2 — Details with m = 5 and NC, ∆σc
γ mf = 1,25
∆σRd,1
2
2
N/mm
N/mm S02
S01
S0
S1
S2
S3
S4
S5
S6
S7
S8
S9
355
984,3
856,9
745,9
649,4
565,3
493,7
430,5
374,7
326,2
284,0
247,2
215,2
315
873,4
760,3
661,9
576,2
501,6
438,1
382,0
332,5
289,5
252,0
219,4
191,0
280
776,3
675,8
588,3
512,2
445,9
389,4
339,5
295,6
257,3
224,0
195,0
169,8
250
693,1
603,4
525,3
457,3
398,1
347,7
303,1
263,9
229,7
200,0
174,1
151,6
225
623,8
543,1
472,8
411,6
358,3
312,9
272,8
237,5
206,8
180,0
156,7
136,4
200
554,5
482,7
420,2
365,8
318,5
278,1
242,5
211,1
183,8
160,0
139,3
121,3
180
499,1
434,5
378,2
329,3
286,6
250,3
218,3
190,0
165,4
144,0
125,4
109,1
160
443,6
386,2
336,2
292,7
254,8
222,5
194,0
168,9
147,0
128,0
111,4
97,0
140
388,2
337,9
294,2
256,1
222,9
194,7
169,8
147,8
128,7
112,0
97,5
84,9
125
346,6
301,7
262,7
228,7
199,1
173,8
151,6
132,0
114,9
100,0
87,1
75,8
112
310,5
270,3
235,3
204,9
178,4
155,8
135,8
118,2
102,9
89,6
78,0
67,9
100
277,3
241,4
210,1
182,9
159,2
139,1
121,3
105,6
91,9
80,0
69,6
60,6
90
249,5
217,2
189,1
164,6
143,3
125,2
109,1
95,0
82,7
72,0
62,7
54,6
80
221,8
193,1
168,1
146,3
127,4
111,3
97,0
84,4
73,5
64,0
55,7
48,5
71
196,9
171,4
149,2
129,9
113,1
98,7
86,1
74,9
65,2
56,8
49,4
43,0
63 56
174,7 155,3
152,1 135,2
132,4 117,7
115,2 102,4
100,3 89,2
87,6 77,9
76,4 67,9
66,5 59,1
57,9 51,5
50,4 44,8
43,9 39,0
38,2 34,0
50
138,6
120,7
105,1
91,5
79,6
69,5
60,6
52,8
45,9
40,0
34,8
30,3
45
124,8
108,6
94,6
82,3
71,7
62,6
54,6
47,5
41,4
36,0
31,3
27,3
40
110,9
96,5
84,0
73,2
63,7
55,6
48,5
42,2
36,8
32,0
27,9
24,3
36
99,8
86,9
75,6
65,9
57,3
50,1
43,7
38,0
33,1
28,8
25,1
21,8
32
88,7
77,2
67,2
58,5
51,0
44,5
38,8
33,8
29,4
25,6
22,3
19,4
28
77,6
67,6
58,8
51,2
44,6
38,9
34,0
29,6
25,7
22,4
19,5
17,0
25
69,3
60,3
52,5
45,7
39,8
34,8
30,3
26,4
23,0
20,0
17,4
15,2
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prEN 13001-3-1:2010 (E)
Annex F
(informative) Evaluation of stress cycles (example)
The stress histories at a selected point of the structure depend on the loads, their direction and position during the use of the crane, as well as on the crane configuration. The total number of working cycles of a crane during its useful life can be divided into several typical tasks with the numbers of working cycles corresponding to them. A task can be characterized by a specific combinations of crane configuration and sequence of intended movements. Before the sequence of stress peaks occurring during the performance of any task can be evaluated, the corresponding series of loadings has to be determined first, i.e. the magnitude, position and direction of all loads.
Key
A B
System Influence lines for bending at selected point j
C D
Influence lines for shear at selected point j Sequences of movements
E
Extreme values of bending Mj and shear Qj (φ 2= 1) during sequences of movements Figure F.1 — Example of load and moment variations due to load movements for tasks on a ship unloader
The unloader handles bulk material from ship to hopper or stockpile, the ranges of points to be served are given by the arrangement of the ship (points 12, 1 and 11), hopper (point 2) and stockpile (points 31 and 32).
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prEN 13001-3-1:2010 (E)
Figure F.1 shows the different sequences of movements of an unloader for two tasks considered, moving load from ship (point 11) to hopper (point 2) and moving load from stockpile (point 31) to hopper (point 2). In the encoded description of each task, the point labels are:
linked by the sign “+” for working movements (with load) and “-“ for dead movements (without load);
underlined when the grab (load lifting attachment) is grounded.
The influence lines (representing the influences of loading and its position) for bending moment Mj and shear force Qj at the selected point j are shown for different loads (T for trolley, P for payload, A for lifting attachment, i.e. grab). The description of salient points of the bending moment and shear load variations can be found in Table F.1. Table F.1 – Description of salient points in bending moment and shear load variations Point
Trolley position
Grab position
Acting loads
a
11
Grounded
T
b
11
Lifted
T,A,P
c
2
Lifted
T,A,P and T,A when load dropped
d
11
Lifted
T,A
e
11
Grounded
T
f
31
Grounded
T
g
31
Lifted
h
2
Lifted
T,A,P T,A,P and T,A when load dropped
i
31
Lifted
T,A
j
31
Grounded
T
The sequences of stresses arising from the bending moment Mj ( σ (t ) = global bending stress) and the shear force Qj ( τ (t ) = global shear stress) can be determined directly from the influence lines. Stress cycles can be identified from the resulting sequences of stress peaks using one of the established stress cycle counting methods, such as the Rainflow counting method or the Reservoir method. The complete stress history is obtained by summating the individual stress histories taken from the sequences of movements of all different tasks.
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prEN 13001-3-1:2010 (E)
Annex G
(informative) Calculation of stiffnesses for connections loaded in tension
The determination of stiffnesses of elements for the calculation of bolt joints in tension presented in this annex applies in the ideal cases shown in Figure G.1 assuming no more than 5 contact surfaces in practical joints. Adjacent and/or theshould way of of actual external forces into the system have great influence on the additionalbolts bolt force and beintroduction considered in design.
Figure G.1 — Types of connections loaded in tension
The stiffnesses for connections in tension can be calculated as follows: The stiffness of the connected parts is calculated from E
Kc =
× Aeq
lK
where Kc
is the stiffness (slope) of flanges
E
is the modulus of elasticity
lK
is the effective clamped length (including all clamped components) with lK = l1 + l2
86
(G.1)
prEN 13001-3-1:2010 (E)
Aeq is the equivalent area for calculation
The calculation of Aeq is in dependence of DA (see Figure G.1): for DA < d W : Aeq =
π
4
× ( DA2 − d h2 )
(G.2)
for d W ≤ DA ≤ d W + lK : Aeq =
π
4
2 × (d W − d h2 ) +
2
l ×d W + 1 − 1 × d W × ( DA − d W ) × 3 K 2 8 D A
π
(G.3)
for d W + lK < DA Aeq =
π
4
2 × (d W − d h2 ) +
π
8
2 lK × d W + 1 − 1 (l + d )2 K W
× lK × d W × 3
(G.4)
where DA is the diameter of the available cylinder of clamped material
dw
is the diameter of the contact area under the bolt head
Aeq is the equivalent area for calculation dh
is the diameter of the hole
lK
is the effective clamped length
The stiffness of the bolt is calculated from 1 Kb
=
1 4 × (l1 + 2 × 0,4 × d ) l2 + 0,5 × d × + Ar π × d2
E
(G.5)
where Kb
is the stiffness (slope) of bolt
E
is the modulus of elasticity
l1
is the effective length for tension without thread
l2
is the effective length for tension with thread
d
is the shank diameter
Ar
is the root area of the bolt
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prEN 13001-3-1:2010 (E)
According to the shape of the connected parts, the external load is introduced to the bolt near its end (Figure G.2, case a), between the bolt end and the connection plane (case b) or close to the connection plane (case c). This may be considered in calculation of the stiffness ratio factor as follows: Φ = αL ×
Kb Kb + K c
(G.6)
where Φ
is the stiffness ratio factor
Kb is the stiffness of bolt Kc is the stiffness of connected parts
αL is the load introduction factor, see Figure G.2.
a) = 0,9α...1 L
b)
α=L 0,6
c)
αL = 0,3
Figure G.2 — Values for the load introduction factor αL as a function of the connection shape
Case a) is typical for bolted connections in cranes. More precise values can be found in the literature. In cases where load introduction cannot be reliably specified, a conservative assumption αL = 1 should be used. In cases where the stiffness ratio factor Φ is determined by finite element analysis of the complete joint, the load introduction factor αL will become an in-built part of the analysis and the value αL = 1 shall be used with the Equation G.6.
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prEN 13001-3-1:2010 (E)
Annex H
(informative) Hollow Sections
Table H.1 — Values of inverse slope of ∆σ –N-curve m and limit design stress range ∆σc for connections and joints of hollow sections girders, m = 5
For site welding the given values of ∆σc should be multiplied by the factor 0,9. No.
∆σc N/mm
1
90
2
Dimensions mm
2 < t0 ≤ 25
Constructional detail
Butt joint with I- or V-weld with weld backing
90
8 < t0 ≤ 25
71
2 < t0 ≤ 8
80
2 < t0 ≤ 25
Requirements
The admissible mismatch of the sections due to a change of the plate thickness is ≤ t0/3, but not more than max. 2 mm. In case of a higher mismatch, especially for a transverse plate butt of rectangular hollow section girders of different dimensions, ∆σc is reduced to 80 % of the given values.
without backing weld 2
Butt joint with I- or V-weld with weld backing
80
8 < t0 ≤ 25
63
2 < t0 ≤ 8
Requirements analogous to No. 1
without weld backing
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prEN 13001-3-1:2010 (E)
Table H.1 — Continued
No.
∆ σc N/mm
2
Dimensions mm
Constructional detail
Requirements
Transverse plate butt with semi V-welds ( tp ≥ 2 to ) 63
2 < t0 ≤ 25
63
8 < t0 ≤ 25
with weld backing
Requirements analogous to No. 1
3
56
2 < t0 ≤ 8
without weld backing 56
2 < t0 ≤ 25
56
8 < t0 ≤ 25
Transverse plate butt with semi V-welds ( tp ≥ 2 to ) with weld backing
Requirements analogous to No. 1
4
50
2 < t0 ≤ 8
without weld backing Transverse plate butt with semi V-welds ( tp ≥ 2 to )
5
90
45
2 < t0 ≤ 8
Requirements analogous to No. 1
prEN 13001-3-1:2010 (E)
Table H.1 — Continued
No.
∆σc N/mm
2
Dimensions mm
Constructional detail
Requirements
Transverse plate butt with semi V-welds ( tp ≥ 2 to )
6
7
40
2 < t0 ≤ 8
80
l ≤ 50
71
50 < l ≤ 100
56
l > 100
100
t≤6
Fillet weld thickness a = t0
Longitudinally welded outer fin not bearing transverse loading in y-direction (2 < t0 ≤ 25)
Fillet weld thickness a: for 2 < t0 ≤ 3:a = 2 for 3 ≤ t0 ≤ 25:a = 0,7⋅t0
Transversally welded outer fin with projection, not bearing transverse loading in y-direction (2 < to ≤ 25), (b > b0)
Fillet weld thickness a: for
8
90
2 < t0 ≤ 3:a = 2 for
6 < t ≤ 12
3 ≤ t0 ≤ 25:a ≤ 0,7⋅t0, 80
12 < t ≤ 25
80
t≤6
71
6 < t ≤ 12
but not more than a = 10 Transversally welded outer fin with projection, not bearing transverse loading in y-direction (2 < t0 ≤ 25), (b > b0)
Fillet weld thickness a: for
9
2 < t0 ≤ 3:a = 2 for 3 ≤ t0 ≤ 25:a ≤ 0,7⋅t0,
63
12 < t ≤ 25
but not more than a = 10
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prEN 13001-3-1:2010 (E)
Table H.1 — Continued
No.
∆ σc N/mm
80
2
Dimensions mm
t≤6
Constructional detail
Transversally welded outer fin without projection, not bearing transverse loading in y-direction (2 < t0 ≤ 25), (b ≤ 0,8 d0)
Requirements
Fillet weld thickness a: for 2 < t0 ≤ 3:a = 2
10
71
6 < t ≤ 12
63
12 < t ≤ 25
100
t≤6
for 3 ≤ t0 ≤ 25:a ≤ 0,7⋅t0, but not more than a = 10
Transversally welded outer fin without projections, not bearing transverse loading in y-direction (2 < t0 ≤ 25), (b ≤ 0,8 b0)
Fillet weld thickness a: for 2 < t0 ≤ 3:a = 2
11
90
6 < t ≤ 12
for 3 ≤ t0 ≤ 25:a ≤ 0,7⋅t0,
80
but not more than a = 10
6 < t ≤ 12
Welded-on hollow section girder, not bearing transverse loading in y-direction (b,d ≤ b0,d0)
12
92
63
2 < t0 ≤ 8
Fillet weld thickness a = t0
prEN 13001-3-1:2010 (E)
Table H.1 — Continued
No.
∆σc N/mm
10
36 13 16
50
6
32
2
Dimensions mm t0/t = 1
(b,d)/d0 = 0,6
Constructional detail
Welded-on hollow section girder, bearing transverse loading F in y-direction (b,d ≤ d0), (2 < t0 ≤ 8)
t0/t = 1
Fillet weld thickness
(b,d)/d0 = 1 t0/t ≥ 1
a = t0
(b,d)/d0 = 0,6 t0/t ≥ 1
(b,d)/d0 = 0,6 t0/t = 1
Welded-on hollow section girder, bearing transverse loading F in y-direction (b,d ≤ b0), (2 < t0 ≤ 8)
(b,d)/b0 = 0,6 t0/t = 1
(b,d)/b0 = 1
Fillet weld thickness
14 12,5
40
Requirements
t0/t ≥ 1
a = t0
(b,d)/b0 = 0,6
t0/t ≥ 1
(b,d)/b0 = 0,6 Single butt strap at chamfered end of tube ( d0/t0 < 25)
15
80
Pinched end of tube
2 < t0 ≤ 8
a = 2 t0
Welded double butt strap ((b0,d0)/t0 < 25)
16
80
2 < t0 ≤ 8
Hot-bended strap, rounded slot milled at end of tube Fillet weld thickness a = t0
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Table H.1 — Continued
No.
∆ σc N/mm
2
Dimensions mm
Constructional detail
Requirements
Inserted dovetail strap ((b0,d0)/t0 < 25)
17
71
Fillet weld thickness
2 < t0 ≤ 8
a = t0
End face strap (d0/t0 < 25), (tP ≥ 2.5 t0)
18
56
Fillet weld thickness for the hollow section girder: a = t0
2 < t0 ≤ 8
for the strap: a = 0,7✕tL
End face strap (b0/t0 < 25), (tP ≥ 2,5 t0)
19
45
2 < t0 ≤ 8
Fillet weld thickness for the hollow section girder: a = t0
for the strap: a = 0,7✕tL
Inserted rectangular strap [(b0,d0)/t0 < 25]
20
94
45
2 < t0 ≤ 8
Fillet weld thickness a = t0
prEN 13001-3-1:2010 (E)
Table H.1 — Continued
No.
∆σc N/mm
56
2
Dimensions mm
8 < t0 ≤ 25
Constructional detail
Requirements
Mitre joint with I- or V-weld without weld backing, stressed by bending (d0/t0 < 25), (ϕ ≥ 90°)
Requirements analogous to No. 1
21 50
2 < t0 ≤ 8
Mitre joint with I- or V- weld without weld backing, stressed by bending (b0/t0 < 25), (ϕ ≥ 90°) 50
8 < t0 ≤ 25 Requirements analogous to No. 1
22 45
2 < t0 ≤ 8
50
Weld thickness a:
Mitre joint with transverse plate and fillet welds, stressed by bending (d0/t0 < 25), (ϕ ≥ 90°), (tP ≥ 2,5 t0)
2
23
45
8 < a ≤ 14
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Table H.1 — Continued
No.
∆ σc N/mm
45
2
Dimensions mm
Weld thickness a:
Constructional detail
Requirements
Mitre joint with transverse plate and fillet welds, stressed by bending (b0/t0 < 25), (ϕ ≥ 90°), (tP ≥ 2,5 t0)
2
24
40
8 < a ≤ 14
45
Weld thickness a:
Joint of column and transverse girder with fillet welds, stressed by bending (b0/t0 < 25), (b0 ≤ b + 3 r)
2
where t0 is the existing minimum plate thickness 40
96
8 < a ≤ 14
prEN 13001-3-1:2010 (E)
Table H.2 — Values of inverse slope of ∆σ –N-curve m and limit design stress range ∆σc for lattice type connections of hollow section girders, m = 5 Basic symbols for all items
with overlapping (e < 0)
with gap (e ≥ 0)
Basic requirements for all items
Bending in individual members should be included in the calculated nominal stress
b0, d 0 ≤ 120 mm. For b0, d 0 > 120 mm, the given values of ∆σ c should be multiplied by the factor f a = 4 120 /(bo , d o )
t 0 ≤ 12,5 mm
Weld thickness a = min t Incline of the diagonal members:
35° ≤ Θi ≤ 50°
(b0, d 0 ) / t 0 < 25 ; t 0 , / t i ≥ 1; 0,6 ≤ (bi, d i ) /(b0, d 0 ) ≤1
Eccentricity
in the plane of the lattice work: − 0,5 ≤ e /( h0, d 0 ) ≤ 0,25
perpendicular to the plane of the lattice work: ≤ 0,02 (b0, d 0 ) Welding under shop conditions. For site welding the given values of
∆σ c should be multiplied by the
factor 0,9.
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Table H.2 (continued) No .
2
Requirements
∆σc (N/mm ) Intermediate values by straight-line interpolation!
K-gussett with direct strut joint
a) with gap:
t0 / ti = 1
t0 / ti ≥ 2
36
80
45
90
t0 / ti = 1
t0 / ti ≥ 2
d i / d 0 = 0,6
50
80
d i / d0 = 1
56
90
d i / d 0 = 0,6 d i / d0 = 1
g ≤ 0,3 d 0 g ≤ 2 / 3 di
1 0,3 ≤ q / p ≤1
a. with overlapping K-T-gusset with direct strut joint
2
t0 / ti = 1
t0 / ti ≥ 2
d i / d 0 = 0,6
36
71
d i / d0 = 1
35
80
0,3 ≤ q / p ≤1
N-gusset with direct strut joint
b) with gap:
t0 / ti = 1
t0 / ti ≥ 2
g ≤ 0,3 d 0
d i / d 0 = 0,6
18
56
g ≤ 2 / 3 di
d i / d0 = 1
25
63
t0 / ti = 1
t0 / ti ≥ 2
45 50
80 90
3 0,3 ≤ q / p ≤ 1
d i / d 0 = 0,6 d i / d0 = 1
b. with overlapping
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Table H.2 (continued) 2
No.
∆σc (N/mm ) Intermediate values by straight-line interpolation!
Requirements T- and X-gusset with direct strut joint
4
t0 / ti = 1
t0 / ti ≥ 2
di / d 0 = 0,6
10
16
d i / d0 = 1
36
50
60° ≤ Θ ≤ 90°
Bending of boom member should be considered! K-gusset with direct strut joint
c) with gap:
g ≤ 0,3 b0 t0 / ti = 1
t0 / ti ≥ 2
bi / b0 = 0,6
32
63
bi / b0 = 1
36
71
5
g ≤ 2 / 3bi
0,3 ≤ q / p ≤ 1
with overlapping K-T-gusset with direct strut joint
6
t0 / ti = 1
t0 / ti ≥ 2
bi / b0 = 0,6
32
56
bi / b0 = 1
36
63
0,3 ≤ q / p ≤ 1
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Table H.2 (continued) 2
No.
∆σc (N/mm ) Intermediate values by straight-line interpolation!
Requirements N-gusset with direct strut joint
d) with gap:
g ≤ 0,3 b0
7
t0 / ti = 1
t0 / ti ≥ 2
bi / b0 = 0,6
29
50
bi / b0 = 1
36
56
g ≤ 2 / 3bi
0,3 ≤ q / p ≤ 1
c. with overlapping T- and X-gusset with direct strut joint
8
t0 / ti = 1
t0 / ti ≥ 2
bi / b0 = 0,6
6
12,5
bi / b0 = 1
32
40
60° ≤ Θ ≤ 90°
Bending of boom member should be considered!
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Annex I
(informative) Selection of a suitable set of crane standards for a given application Is there a product standard in the following list that suits the application?
EN 13000
Cranes — Mobile cranes
EN 14439
Cranes — Tower cranes
EN 14985
Cranes — Slewing jib cranes
prEN 15011
Cranes — Bridge and gantry cranes
EN 13852-1
Cranes — Offshore cranes — Part 1: General purpose offshore cranes
EN 13852-2
Cranes — Offshore cranes — Part 2: Floating cranes
EN 14492-1
Cranes — Power driven winches and hoists — Part 1: Power driven winches
EN 14492-2
Cranes — Power driven winches and hoists — Part 2: Power driven hoists
EN 12999
Cranes — Loader cranes
EN 13157
Cranes — Safety — Hand powered lifting equipment
EN 13155
Cranes — Non-fixed load lifting attachments
EN 14238
Cranes — Manually controlled load manipulating devices
EN 15056
Cranes — Requirements for container handling spreaders YES
NO
Use it directly, plus the standards that are referred to
Use the following:
EN 13001-1
Cranes — General design — Part 1: General principles and requirements
EN 13001-2
Cranes — General design — Part 2: Load actions
prEN 13001-3.1
Cranes — General design — Part 3.1: Limit states and proof of competence of steel structures
CEN/TS 13001-3.2
Cranes — General design — Part 3.2: Limit states and proof of competence of wire ropes
CEN/TS 13001-3.3
Cranes — General design — Part 3.3: Limit states and proof of competence of wheel / rail contacts
CEN/TS 13001-3.5
Cranes — General design — Part 3.5: Limit states and proof of competence of forged hooks
EN 13135-1
Cranes — Equipment — Part 1: Electrotechnical equipment
EN 13135-2
Cranes — Equipment — Part 2: Non-electrotechnical equipment
EN 13557
Cranes — Controls and control stations
EN 12077-2
Cranes safety — Requirements for health and safety — Part 2: Limiting and indicating devices
EN 13586
Cranes — Access
EN 14502-1
Cranes — Equipment for the lifting of persons — Part 1: Suspended baskets
EN 14502-2
Cranes — Equipment for the lifting of persons — Part 2: Moveable cabins
EN 12644-1
Cranes — Information for use and testing — Part 1: Instructions
EN 12644-2
Cranes — Information for use and testing — Part 1: Marking
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prEN 13001-3-1:2010 (E)
Annex ZA
(informative) Relationship between this European Standard and the Essential Requirements of EU Directive 98/37/EC
This European Standard has been prepared under a mandate given to CEN by the European Commission and the European Free Trade Association to provide a means of conforming to Essential Requirements of the New Approach Directive Machinery 98/37/EC, amended by 98/79/EC. Once this standard is cited in the Official Journal of the European Union under that Directive and has been implemented as a national standard in at least one Member State, compliance with the normative clauses of this standard confers, within the limits of the scope of this standard, a presumption of conformity with the relevant Essential Requirements of that Directive and associated EFTA regulations. WARNING — Other requirements and other EU Directives may be applicable to the product(s) falling within
the scope of this standard.
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Annex ZB
(informative) Relationship between this European Standard and the Essential Requirements of EU Directive 2006/42/EC
This European Standard has been prepared under a mandate given to CEN by the European Commission and the European Free Trade Association to provide a means of conforming to Essential Requirements of the New Approach Directive Machinery 2006/42/EC. Once this standard is cited in the Official Journal of the European Union under that Directive and has been implemented as a national standard in at least one Member State, compliance with the normative clauses of this standard confers, within the limits of the scope of this standard, a presumption of conformity with the relevant Essential Requirements of that Directive and associated EFTA regulations. WARNING — Other requirements and other EU Directives may be applicable to the product(s) falling within
the scope of this standard.
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Bibliography
Selection of literature that contains information about Hot Spot Stress Method: [1] EN 1993-1-1:2005, Eurocode 3: Design of steel structures — Part 1-1: General rules and rules for buildings
[2] prEN 1993-1-9: Eurocode 3: Design of steel structures — Part 1-9: Fatigue strength of steel structures [3] EN 22553:1994, Welded, brazed and soldered joints — Symbolic representation on drawings (ISO 2553:1992)
[4] EN ISO 4042:1999, Fasteners — Electroplated coatings (ISO 4042:1999) [5] EN ISO 17659:2004 Welding - Multilingual terms for welded joints with illustrations (ISO 17659:2002); Trilingual version
[6] EN ISO 15330:1999, Fasteners — Preloading test for the detection of hydrogen embrittlement — Parallel bearing surface method (ISO 15330:1999) [7] ISO 9587:2007, Metallic and other inorganic coatings — Pre-treatment of iron or steel to reduce the risk of hydrogen embrittlement
[8] IIW International Institute of Welding. Subcommission XV-E-92-244: Recommended Fatigue Design Procedure for Welded Hollow Section Joints, 2nd edition, June 1999 [9] IIW – XV-E: Recommended Fatigue Design Procedure for Welded Hollow Section Joints Part 1: Recommendations. 1999; Document XIII-1804-99 Part 2: Commentary, 1999, Document XV-1035-99
[10] I. HUTHER, H-P. LIEURADE, L. VELLUET, Contraintes admissibles dans les assemblages soudés, 1A4085/1A4087, rapport CETIM, avril 2000 [11] E. Niemi, W. Fricke, S.J. Maddox, Fatigue analysis if welded components; Designer's guide to the structural hot-spot stress approach, September 2006 [12] American Petroleum Institute – API RP 2A-WSD: Recommended practice for planning, designing and constructing fixed offshore platforms – Working Stress Design, December 1,2000 [13] Romeijn, A., Stress and strain concentration factors of welded multiplanar tubular joints, Delft University Press, Delft, 1994, ISBN 90-407-1057-0
Selection of literature that contains information about hollow sections: [14] Zhao, X-L., Herion, S. Packer, J. A., Puthli, R. S., Sedlacek, G. Wardenier, J. Weymand, K., Wingerde, A. M., van, and Yeomans, N. F.: Design Guide for circular and rectangular hollow section welded joints under fatigue loading, CIDECT and Verlag TÜV Rheinland, Cologne, 2000, ISBN 3-8249-0565-5 [15] Wardenier, J., Dutta, D., Yeomans, N., Packer, J. A., and Bucak, O.: Design Guide for structural hollow sections in mechanical applications, CIDECT and Verlag TÜV Rheinland, Cologne, 1995, ISBN 3-82490302-4 [16] Zirn, R.: Schwingfestigkeitsverhalten geschweißter Rohrknotenpunkte und Rohrlaschenverbindungen, Techni. Wiss. Bericht MPA Stuttgart, 1975, Heft 75-01 104
prEN 13001-3-1:2010 (E)
Selection of literature that contains information about elastic stability: [17] DIN 18800-2, Stahlbauten — Stabilitätsfälle — Knicken von Stäben und Stabwerken [18] “Eurocode 3 – Design of steel structures”, Part 1.5 : general rules : supplementary rules for planar plated structures without transverse loading (EN 1993-1-5:2007) [19] Klöppel, K. and Scheer, J., “Beulwerte ausgesteifter Rechteckplatten“, W. Ernst und Sohn [20] Klöppel, K. and Möller, K., “Beulwerte ausgesteifter Rechteckplatten, Band II“, W. Ernst und Sohn [21] Protte, W. : Zum Scheiben und Beulproblem lângsversteifter Stegblechfelder bei örtlicher Lasteinleitung und bei Belastung aus Haupttragwirkung.Stahlbau 45 (1976), pages 251-252
105
