MC MEMORIA DE CALCULO EJEMPLO AMETANK

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SUBDIRECCIÓN DE ALMACENAMIENTO Y DESPACHO GERENCIA DE ADMINISTRACIÓN DE GUARDA Y MANEJO ®

CONTRATO: P5ANO93013 “Desarrollo de Ingeniería de Detalle, Procura, Construcción, Pruebas y Puesta en Operación de la Nueva infraestructura para la incorporación de Etanol Anhidro en la Matriz Energética de Pemex Refinación”

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MC-H-001

MEMORIA MEMORIA DE CÁL CULO MECÁNICA. TANQUE DE ALMACEN AL MACENAMIENTO AMIENTO DE ETANOL ANHIDRO TV-368 / TV-369.

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MC-H-001

MEMORIA DE CÁLCULO MECÁNICA. TANQUE DE ALMACENAMIENTO DE ETANOL ANHIDRO TV-368 / TV-369.

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ÍNDICE ___________________________________ ____________________________________ ____________________________________ ____________________ __3 1.0 OBJETIVO _________________ 2.0 ALCANCE AL CANCE _________________ ___________________________________ ____________________________________ ____________________________________ ____________________ __ 3 3.0 DATOS DEL SITIO __________________ ___________________________________ ___________________________________ ________________________________ ______________3 4.0 DATOS DE PROCESO _________________ ___________________________________ ___________________________________ ____________________________ ___________3 5.0 ANÁLISIS ANÁ LISIS SÍSMICO _________________ __________________________________ ___________________________________ ________________________________ ______________3 6.0 ANÁLISIS ANÁ LISIS POR VIENTO ________________ __________________________________ ___________________________________ ____________________________ ___________7 7.0 METODOLOGÍA METODOLOGÍA DE CÁLCUL O ________________ __________________________________ ___________________________________ ______________________ _____ 7 7.1 SUMMARY OF DESIGN DESIGN DATA AND A ND REMARKS ________________ _________________________________ ___________________________ __________7 7.2 TANK NAMEPLATE N AMEPLATE INFORMATION __________________ ____________________________________ __________________________________ ________________7 7.3 SUMMARY OF SHELL SHELL RESULTS _________________ ___________________________________ ____________________________________ ___________________ _8 7.4 SELF SUPPORTED CONICAL ROOF _________________ ___________________________________ __________________________________ ________________9 7.5 SUMMARY OF ROOF RESULTS __________________ ____________________________________ ___________________________________ __________________ _ 16 7.6 SHELL SHELL COURSE COURSE DESIG DESIGN N (Bott om c our se is #1)_________________ #1)___________________________________ ________________________ ______17 7.7 SUMMARY OF SHELL SHELL RESULTS _________________ ___________________________________ ____________________________________ __________________22 7.8 INTERMEDIATE INTERMEDIATE STIFFENER STIFFENER CALCUL ATIONS PER API-650 Sectio n 5.9.7 _________________ ___________________ __22 7.9 FLAT BOTTOM: B OTTOM: NON NON ANNULAR PL ATE DESIGN DESIGN _________________ __________________________________ _______________________ ______23 7.10 SUMMARY OF BOTTOM RESULTS________________ RESULTS __________________________________ ____________________________________ __________________24 7.11 WIND MOMENT (Per API-650 SECTION 5.11) ________________ __________________________________ ___________________________ _________24 7.12 RESISTANCE TO OVERTURNING (per API-650 5.11.2) _________________ ___________________________________ __________________26 7.13 RESISTANCE TO SLIDING (per API-650 5.11.4) _________________ ___________________________________ ________________________ ______27 7.14 SITE GROUND GROUND MOTION CALCUL ATIONS ________________ __________________________________ ______________________________ ____________28 7.15 SEISMIC SEISMIC CAL CULATIONS _________________ __________________________________ ___________________________________ _________________________ _______29 7.16 ANCHOR 7.16 ___________________________________ ___________________________________ _________________________ _______35 ANCHOR BOLT B OLT DESIGN __________________ 7.17 ANCHOR 7.17 ANCHOR BOLT B OLT SUMMARY SUMMA RY ________________ __________________________________ ___________________________________ ________________________ _______38 7.18 NORMAL AND EMERGENCY VENTING (API-2000 6th EDITION)_________________ EDITION) ____________________________ ___________41 7.19 FLOATING ROOF DESIGN _________________ ___________________________________ ___________________________________ ________________________ _______43 7.20 PLAN VIEW APPURTENANCE_________________ APPURTENANCE ___________________________________ ___________________________________ _____________________ ____47 7.21 ELEVATION VIEW APPURTENANCE _________________ ___________________________________ _________________________________ _______________47 7.22 CAPACITIES and WEIGHTS ________________ _________________________________ ___________________________________ _________________________ _______61 7.23 MAWP & MAWV SUMMARY ________________ _________________________________ ___________________________________ _________________________ _______62 7.24 MAXIMUM CALCULAT ED INTERNAL PRESSURE ________________ _________________________________ _______________________ ______62 7.25 MAXIMUM CALCULATED EXTERNAL PRESSURE________________ PRESSURE _________________________________ _______________________ ______62 8.0 CONCLUSIONES _______________ _________________________________ ____________________________________ __________________________________ ________________63 9.0 NORMATIVIDAD APLICABLE _________________ ___________________________________ ___________________________________ _____________________ ____ 6633 __________________________________ ___________________________________ _________________________ _______64 10.0 GEOMETRIA DEL DISEÑO _________________

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1.0 OBJETIVO El presente documento tiene como objetivo el Diseño Mecánico de un Tanque de Almacenamiento de Etanol Anhidro, TV-368 / TV-369. 2.0 ALCANCE El presente documento tiene como alcance general el dimensionamiento de los siguientes componentes: • • • • • • • • •

Placas del cuerpo y corroboración de espesores. Placas del techo cónico y corroboración de espesores. Placas de fondo y corroboración de espesores. Membrana interna flotante y su configuración. Sumidero para drenaje y difusor de boquilla de entrada. Escalera helicodal. Barandal Perimetral. Entradas Hombre en techo y cuerpo. Boquillas de operación.

3.0 DATOS DEL SITIO

•

•

LOCALIZACIÓN: Terminal de Almacenamiento y Reparto (TAR) de Perote, Veracruz. o COORD. GEOGRAFICAS: a 19° 34' 34' 15" de latitud norte norte y 97° 15' 15' 6" de longitud oeste. oeste. o

4.0 DATOS DE PROCESO •

De acuerdo a Hoja de Datos 1501-677-HDD-CTC-REF-V-001.

5.0 ANÁL ISIS SÍSMICO SÍSMICO Para el presente Tanque de Almacenamiento se tiene la siguiente Clasificación de la Instalación Según el Manual de Diseño de Obras Civiles Civi les (MDOC) de la CFE 2008: Según su destino: B o Según su Estructuración: Tipo 5 o •

•

El presente Tanque de Almacenamiento se analizará para las siguientes características: Estado límite: Colapso o Tipo de Suelo: Suelo Medio. o

De acuerdo a Estudio de Mecánica de Suelos. 677-EA-ESP-F-028 , se tienen los siguientes datos de las Propiedades y Estratificación del Suelo. •

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PEMEX LOGÍSTICA

SUBDIRECCIÓN DE ALMACENAMIENTO Y DESPACHO GERENCIA DE ADMINISTRACIÓN DE GUARDA Y MANEJO CONTRATO: P5ANO93013

®

“Desarrollo de Ingeniería de Detalle, Procura, Construcción, Pruebas y Puesta en Operación de la Nueva infraestructura para la incorporación de Etanol Anhidro en la Matriz Energética de Pemex Refinación”

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Fecha: 19-01-2016

MC-H-001

MEMORIA DE CÁL CULO MECÁNICA. TANQUE DE ALMACENAMIENTO DE ETANOL ANHIDRO TV-368 / TV-369.

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Tabla 1.

Propiedades y Estratif icaci ón del Suelo.

Estrato 1 2 3 4 5 6 7 8 9 10

Profundidad

Espesor

-

2.70 1.80 2.25 1.35 1.40 3.60 2.25 0.90 1.80 2.09

0 2.7 4.5 6.75 8.1 9.5 13.1 15.4 16.3 18.1

Total

2.7 4.5 6.75 8.1 9.5 13.1 15.4 16.3 18.1 20.1

20.14

Clasificación S.U.C.S SM SM SM GP-SM SM SM SM ML GM SM

Número de Golpes 8 13 50 10 30 32 50 44 50 11 35 30 50 16 21 50 50

Promedio

32.35

βn (m/s )

ρ (kg/m³)

180 180 180 180 180 180 180 180 180 180

1600 1670 1630 1700 1670 1630 1650 1620 1700 1680

180.00

1655.00

Estos valores, se introdujeron al programa PRODISIS de CFE 2008, para obtener el resumen de coeficientes para la obtención de la gráfica del espectro sísmico.

Figura 1.

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Estado límite y caracterizaci ón del terreno en PRODISIS CFE 2008.

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DATOS DEL ESPECTRO S SMICO DATOS DE ESPECTRO CALCULADOS EN "PR DISIS" Resumen Respuesta Dinámica Vs = m/s 182.17 Ts = s 0.46 Te = s 1.04 Fact terreno rocos o a0r = g 0.118 Fd = 0.289

Figura 2.

Fact co mp lineal p = 0.25 Fs = 1.565 Fr = 3.557 Fact comp no lineal

Fnl = Fv =

0.947 0.96

Espectro de Diseño a0 = g 0.174 c = g 0.62 Ta = s 0.168 Tb = s 0.6 ζe = % 5 k = 1.5 β = 1

Gráfica del Espectro sísmi co.

a) Aceleración Espectral Impulsiva (Sai ) De acuerdo al Estudio de Mecánica de Suelos INFORME EGG1508660, la aceleración máxima en la superficie del suelo (PGA), para el diseño del proyecto es de 0.3 g.

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b) Para la Obtención de la Aceleración Espectral Convectiva tenemos;   . ≤ 4  .,

 =

  . > 4 .,

 =

1.5 1 

≤



6 1 

2

Donde de acuerdo al API 650: T conv

=

1.8 K s

D

Para determinar el periodo natural convectivo se requiere calcular K s y sustituirlo en la ecuación.

K s

=

0.57 8

 3.68 H     D 

=

0.580

Tanh

Donde; H = Altura del nivel de liquido d e diseño, en m. D = Diametro nominal del tanq ue, en m. Ks = Coeficiente del primer modo de onda. Por lo tant o; Tconv =

2.880

s

8. Sac =

0.255

RESUMEN DE DATOS A INGRESAR A AMETank PARA EL M TODO “API 650- S ite Specific"; 1. Seismic Use Group (SUG): 2. Seismic S ite Classificatión: 3. Q (Factor de Escala): 4. Rwi (Impulsiva): 5. Rwc (Convectiva): 6. Importance Factor:

7 . 8.

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Sai : Sac :

I D 0.66 4 2

1 0.3 0.255

DATO POR EL CLIENTE

g g

DATO POR EL CLIENTE

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6.0 ANÁL ISIS POR VIENTO De acuerdo a Bases de Usuario, se introdujeron los siguientes datos.

Figura 3.

Datos de viento para el software AMETank.

7.0 METODOLOGÍA DE CÁLCUL O 7.1 SUMMARY OF DESIGN DATA AND REMARKS Job : DCPA-SO-SCAR-SAR-GOMT-E-15-14 Date of Calcs. : 18-ENE-16 Mfg. or Insp. Date : Plant : PURCHASER DESCRIPTION CITY AND STATE Plant Location : TAR PEROTE 677 Site : PEROTE, VERACRUZ Design Basis : API-650 12th Edition, March 2013

7.2 TANK NAMEPLATE INFORMATION Pressure Combination Factor 0.4 Design Standard API-650 12th Edition, March 2013 Appendices Used E, F Roof A283M-C : 11.1 mm Shell (1) A283M-C : 7.9 mm Shell (2) A283M-C : 6.35 mm Shell (3) A283M-C : 6.35 mm Shell (4) A283M-C : 6.35 mm Bottom A283M-C : 9.5 mm

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Design Internal Pressure = 0.4 KPa or 40.7924 mmh2o Design External Pressure = -0 KPa or -0 mmh2o MAWP = 7.936 KPa or 809.3269 mmh2o MAWV = -0.6361 KPa or -64.8714 mmh2o D of Tank = 7.62 m OD of Tank = 7.6358 m ID of Tank = 7.62 m CL of Tank = 7.6279 m Shell Height = 7.3152 m S.G of Contents = 0.789 Max Liq. Level = 6.035 m Min Liq. Level = 0.609 m Design Temperature = 93 ºC Tank Joint Efficiency = 0.85 Ground Snow Load = 0 KPa Roof Live Load = 1 KPa Additional Roof Dead Load = 0 KPa Basic Wind Velocity = 180 kph Wind Importance Factor = 1 Using Seismic Method: API-650 - Site Specific DESIGNER REMARKS TANQUE DE ALMACENAMIENTO DE ETANOL ANHIDRO. TV-368 / TV-369 7.3 SUMMARY OF SHELL RESULTS tMin min ttCA Tensile Sd St Weigh t-min t-min Shel Width Materia Yield Weigh t-Des t-Test Ext- min Actua Statu (mm JE Strengt (MPa (MPa t CA Erectio Seismi l # (mm) l Strengt h (MPa) l s ) ) ) t (N) (N) n (mm) (mm) (mm) c (mm) Pe (mm h (MPa) (mm ) (mm) ) 1828. A283M0.8 4.433 1.390 1 205 380 137 154 26,569 15,813 6 6 7.9 OK 8 C 3.2 5 2 5 3.8732 NA 1828. A283M0.8 0.947 2 3.2 205 380 137 154 21,360 10,600 5 4.04 3.5853 NA 5 6.35 OK 8 C 5 1 1828. A283M0.8 3.646 0.503 3 3.2 205 380 137 154 21,360 10,600 5 3.4073 NA 5 6.35 OK 8 C 5 7 7 1816. A283M0.8 3.253 0.060 4 3.2 205 380 137 154 21,220 10,531 5 3.2347 NA 5 6.35 OK 8 C 5 5 3

Total Weight of Shell = 90,511.2095 N

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CONE ROOF Plates Material = A283M-C t.required = 10.5143 mm t.actual = 11.1 mm Roof corrosion allowance = 1.6 mm Roof Joint Efficiency = 0.85 Plates Overlap Weight = 1,242.0931 N Plates Weight = 39,897.4639 N Bottom Type : Pie Plates Bottom Material = A283M-C t.required = 9.2 mm t.actual = 9.5 mm Bottom corrosion allowance = 3.2 mm Bottom Joint Efficiency = 0.85 Total Weight of Bottom = 34,342.2733 N ANCHOR B OLT : (8) M64 mm UNC Bol ts, A36M TOP END STIFFENER : Detail B Size = l50x50x8 Material = A36M Weight = 1,375.0141 N 7.4 SELF SUPPORTED CONICAL ROOF A = Actual Part. Area of Roof-to-shell Juncture per API-650 (cm^2) A-min = Minimum participating area (cm^2) per API-650 5.10.5.2 a-min-A = Minimum participating area due to full design pressure per API-650 F.5.1 (cm^2) a-min-Roof = Minimum participating area per API-650 App. F.5.2 (cm^2) Add-DL = Added Dead load (kPa) Alpha = 1/2 the included apex angle of cone (degrees) Ap = Projected Area of Roof for wind moment (m^2) Ap-Vert = Vertical Projected Area of Roof (m^2) Aroof = Contributing Area due to roof plates (cm^2) Ashell = Contributing Area due to shell plates (cm^2) CA = Roof corrosion allowance (mm) D = Tank Nominal Diameter per API-650 5.6.1.1 Note 1 (m) density = Density of roof (kg/mm3) DL = Dead load (kPa) e.1b = Gravity Roof Load (1) - Balanced (kPa) e.1u = Gravity Roof Load (1) - Unbalanced (kPa) e.2b = Gravity Roof Load (2) - Balanced (kPa) e.2u = Gravity Roof Load (2) - Unbalanced (kPa) Fp = Pressure Combination Factor Fy = smallest of the yield strength (MPa) Powered by EBPC

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Fy-roof = Minimum yield strength for shell material (Table 5-2a) (MPa) Fy-shell = Minimum yield strength for shell material (Table 5-2a) (MPa) Fy-stiff = Minimum yield strength for stiffener material (Table 5-2a) (MPa) hr = Roof height (m) ID = Tank Inner Diameter (m) Insulation = Roof Insulation (m) JEr = Roof joint efficiency JEs = Top shell course joint efficiency JEst = Roof comp. ring joint efficiency Lr = Entered Roof Live Load (kPa) Lr-1 = Computed Roof Live Load, including External Pressure Max-f = Intermediate variable for calculating max roof load due to roof actual thickness Max-p = Max Roof Load due to participating Area (kPa) Max-T1 = Max roof load due to roof actual thickness (kPa) ME = per API 650 App. M.5.1 Net-Uplift = Uplift due to internal pressure minus nominal weight of shell, roof and attached framing (N), per API-650 F.1.2 P-ext-1 = Max external pressure due to roof actual thickness (kPa) P-ext-2 = Max external pressure due to roof shell joint area (kPa) P-F41 = Max design pressure limited by the roof-to-shell joint (kPa) P-F42 = Max design pressure due to Uplift per API-650 F.4.2 (kPa) P-F51 = Max design pressure reversing a-min-A calculation (kPa) P-max-ext = Total max external pressure due to roof actual thickness (kPa) P-max-ext-T = Total max external pressure due to roof actual thickness and roof participating area (kPa) P-max-internal = Maximum design pressure and test procedure per API-650 F.4, F.5. (kPa) P-Std = Max pressure pressure allowed per API-650 App. F.1 & F.7 (kPa) P-weight = Dead load of roof plate (kPa) Pe = External Pressure (kPa) Pr = Total design external pressure (kPa) pt = Roof cone pitch (mm) rise per 12 (mm) R = Roof horizontal radius (m) R2 = Length of the normal to the roof, measured from the vertical centerline of the tank (mm) Ra = Roof surface area (cm^2) Rc = Inside Radius of tank shell (mm) Roof Plates Weight = Weight of roof plates (N) Roof-wc = Weight corroded of roof plates (N) S = Ground Snow Load per ASCE 7-05 Fig 7-1 (kPa) Sb = Balanced Design Snow Load per API-650 Section 5.2.1.h.1 (kPa) Shell-wc = Weight corroded of shell (N) Su = Unbalanced Design Snow Load per API-650 Section 5.2.1.h.2 (kPa) T = Balanced Roof Design Load per API-650 Appendix R (kPa) t-actual = Actual roof thickness (mm) t-calc = Minimum nominal roof plates thickness per API-650 Section 5.10.5.1 (mm) Theta = Angle of cone to the horizontal (degrees) U = Unbalanced Roof Design Load per API-650 Appendix R (kPa) Wc = Maximum width of participating shell per API-650 Fig. F-2 (mm) Wh = Maximum width of participating roof per API-650 Fig. F-2 (mm) Xw = Moment Arm of UPLIFT wind force on roof (m) Note: Tank Pressure Combi natio n Factor Fp = 0.4 Powered by EBPC

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D = 7.62 m ID = 7.62 m CA = 1.6 mm hr = 0.6385 m R = 3.8309 m Fp = 0.4 JEr = 0.85 JEs = 0.85 JEst = 0.85 Insulation = 0 m Add-DL = 0 kPa Lr = 1 kPa S = 0 kPa Sb = 0 kPa Su = 0 kPa density = 0.000007841 kg/mm3 P-weight = 0.8749 KPa Pe = 0 kPa pt = 2 mm rise per 12 mm t-actual = 11.1 mm ME = 1 Fy-roof = 205 MPa Fy-shell = 205 MPa Fy-stiff = 250 MPa DL = Insulation + P-weight + Add-DL DL = 0 + 0.8749 + 0 DL = 0.8749 kPa Roof Loads per API-650 5.2.2 e.1b = DL + MAX(Sb , Lr) + (0.4 * Pe) e.1b = 0.8749 + MAX(0 , 1) + (0.4 * 0) e.1b = 1.8749 kPa e.2b = DL + Pe + (0.4 * MAX(Sb , Lr)) e.2b = 0.8749 + 0 + (0.4 * MAX(0 , 1)) e.2b = 1.2749 kPa T = MAX(e.1b , e.2b) T = MAX(1.8749 , 1.2749) T = 1.8749 kPa e.1u = DL + MAX(Su , Lr) + (0.4 * Pe) e.1u = 0.8749 + MAX(0 , 1) + (0.4 * 0) e.1u = 1.8749 kPa e.2u = DL + Pe + (0.4 * MAX(Su , Lr)) e.2u = 0.8749 + 0 + (0.4 * MAX(0 , 1)) e.2u = 1.2749 kPa Powered by EBPC

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U = MAX(e.1u , e.2u) U = MAX(1.8749 , 1.2749) U = 1.8749 kPa Lr-1 = MAX(T , U) Lr-1 = MAX(1.8749 , 1.8749) Lr-1 = 1.8749 kPa Theta = TAN^-1 (pt/12) Theta = TAN^-1 (2/12) Theta = 9.4623 degrees Alpha = 90 - Theta Alpha = 90 - 9.4623 Alpha = 80.5377 degrees Rc = ID/2 Rc = 7620/2 Rc = 3810 mm R2 = Rc/SIN(Theta) R2 = 3810/SIN(9.4623) R2 = 23,175.3252 mm Weight, Surface Area, and Proj ect Areas of Roof Ap-Vert = D^2 * TAN(Theta)/4 Ap-Vert = 7.62^2 * TAN(9.4623)/4 Ap-Vert = 2.4193 m^2 Horizon tal Proj ected Area of Roof p er API-650 5.2.1.f Xw = D * 0.5 Xw = 7.62 * 0.5 Xw = 3.81 m Ap = PI * (D/2)^2 Ap = PI * (7.62/2)^2 Ap = 45.6036 m^2 Ra = PI * R * SQRT(R^2 + hr^2) Ra = PI * 3.8309 * SQRT(3.8309^2 + 0.6385^2) Ra = 467,401.1522 cm^2 or 46.7401 m^2 Roof Plates Weight = density * Ra * t-actual Roof Plates Weight = 0.000007841 * 467,401.1522 * 11.1 Roof plates Weight = 39,897.4639 N Minimum Thickness of Roof Plate Section 5.10.5.1 Powered by EBPC

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t-calc = MAX((D/(4.8 * SIN(Theta)) * SQRT(T/2.2)) + CA , (D/(* 5.5 SIN(Theta))) * SQRT(U/2.2) * CA , 5) t-calc = MAX(7.62/(4.8 * SIN(9.4623)) * SQRT(1.8749/2.2)) + 1.6 , (7.62/(* 5.5 SIN(9.4623))) * SQRT(1.8749/2.2) * 1.6) , 5 t-calc = 10.5143 mm Max-f = 4.8 * SIN(Theta) * (t-actual - CA)/ME/D Max-f = 4.8 * SIN(9.4623) * (11.1 - 1.6)/1/7.62 Max-f = 0.9838 Max-T1 = Max-f^2 * 45 Max-T1 = 0.9838^2 * 45 Max-T1 = 2.1293 kPa P-ext-1 = -(Max-T1 - DL - MAX(S , Lr)) / Fp P-ext-1 = -(2.1293 - 0.8749 - MAX(0 , 1)) / 0.4 P-ext-1 = -0.6361 kPa P-max-ext = -0.6361 kPa TOP MEMBER DESIGN CA_roof (Thickness of roof plate) = 1.6 mm CA_shell (Thickness of shell plate) = 3.2 mm D (Shell nominal diameter) = 7.6279 m ID (Shell inside diameter) = 7.62 m Theta angle (Angle between the roof and a horizontal plane at the roof-to-shell junction) = 9.4623 deg tc (Thickness of shell plate) = 6.35 mm th (Thickness of roof plate) = 11.1 mm Shell ins ide radius Rc = ID / 2 = 7620.0 / 2 = 3810.0 mm Shell nominal diameter (D) = 7.6279 m Length of normal to roof R2 = Rc / SIN(Theta angle) = 3810.0 / SIN(9.4623) = 23175.3252 mm Thickness of corroded roof pl ate th_corroded = th - CA_roof = 11.1 - 1.6 = 9.5 mm Thickness of corroded shell plate tc_corroded = tc - CA_shell = 6.35 - 3.2 = 3.15 mm CA_stiff > 0 Note: The calculation does not take into account the stiffener corrosion allowance, make sure to pick a stiffener size that make up the difference in the thicknesses (corroded vs nominal). Maximum width of participating roof API-650 Figure F-2 Wh = MIN((0.3 * SQRT((R2 * th_corroded))) , 300) = MIN((0.3 * SQRT((23175.3252 * 9.5))) , 300) Powered by EBPC

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= 140.7654 mm Maximum wid th of participating shell API-650 Figure F-2 Wc = 0.6 * SQRT((Rc * tc_corroded)) = 0.6 * SQRT((3810.0 * 3.15)) = 65.7308 mm Nominal weight of shell pl ates and framing DLS = Ws + W_framing = 90511.2095 + 1337.0416 = 91848.2511 N Nominal weight of r oof plates and attached stru ctural DLR = Wr + W_structural = 39897.464 + 16864.7513 = 56762.2153 N Compression Ring Detail b Properties ID (Shell inside diameter) = 7.62 m Size (Compression ring size) = l50x50x8 Wc (Length of contributing shell) = 65.7308 mm Wh (Length of contributing roof) = 140.7654 mm h (Top angle to top shell distance) = 3.15 mm tc (Thickness of shell plate) = 3.15 mm th (Thickness of roof plate) = 9.5 mm Angle vertical leg size (l_vert) = 50 mm Angle horizontal leg size (l_horz) = 50 mm Angle thickness (t_angle) = 8.0 mm Angle area (A_angle) = 741.0 mm^2 Angle centroid (c_angle) = 15.2 mm Angle moment of inertia (I_angle) = 163000.0 mm^4 Length of contributing shell reduced wc_reduced = Wc - h = 65.7308 - 3.15 = 62.5808 mm Contributing shell moment of inertia I_shell = (wc_reduced * (tc_corroded^3)) / 12 = (62.5808 * (3.15^3)) / 12 = 163.0015 mm^4 Contributi ng shell area A_shell = wc_reduced * tc_corroded = 62.5808 * 3.15 = 197.1296 mm^2 Contributing roof area A_roof = Wh * th_corroded = 140.7654 * 9.5 = 1337.2715 mm^2 Detail total area A_detail = A_shell + A_roof + A_angle = 197.1296 + 1337.2715 + 741.0 = 2275.401 mm^2 Find combined moment of inertia about shell inside axis with negative value toward center

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Description Shell centroid Stiffener centroid moment of inertia of first body moment of inertia of second body Total area Sum of moments of inertia's Combined centroid Combined moment of inertia Distance from neutral axis to edge 1 (inside) Distance from neutral axis to edge 2 (outside) Combined stiffener shell section modulus

Variable d_shell d_stiff

Equation tc_corroded / 2 c_angle + tc_corroded

Value 1.5750 18.3500

I_1

I_angle + (A_angle * (d_stiff^2))

412511.3725 mm^4

I_2

I_shell + (A_shell * (d_shell^2))

652.0060

A_sum I_sum

Unit mm mm

mm^4

A_angle + A_shell I_1 + I_2 ((d_stiff * A_angle) + (d_shell * c_combined A_shell)) / (A_angle + A_shell)

938.1296 mm^2 413163.3785 mm^4

I_combined I_sum - (A_sum * (c_combined^2))

206978.9491 mm^4

e1

c_combined

14.8251

mm

e2

(tc_corroded + l_horz) - e1

38.3249

mm

S

I_combined / MAX(e1 , e2)

5400.6336

mm^3

14.8251

mm

Roof Design Requirements Least allow able tensile stress for t he materials in t he roof-to-shell joint Fa = 0.6 * Fy = 0.6 * 205 = 123.0 MPa Compression region required area for self suppo rted cone roof API-650 5.10.5.2 A_roof = (p * (D^2)) / (8 * Fa * TAN(Theta angle)) = (1874.8739 * (7.6279^2)) / (8 * 123.0 * TAN(9.4623)) = 665.1785 mm^2 A_actual >= A_roof ==> Compression region actual cross sectional area is sufficient. Maximum allowable load for th e actual resisti ng area API-650 5.10.5.2 Max-p = (A_actual / (D^2)) * 8 * Fa * TAN(Theta angle) = (2275.401 / (7.6279^2)) * 8 * 123.0 * TAN(9.4623) = 6413.4516 Pa Appendi x F Requi rements A_actual (Area resisting compressive force) = 2275.401 mm^2 D (Tank nominal diameter) = 7.6279 m DLR (Nominal weight of roof plates and attached structural) = 56762.2153 N DLS (Nominal weight of shell plates and framing) = 91848.2511 N Fy (Minimum specified yield-strength of the materials in the roof-to-shell junction) = 205 MPa ID (Tank inside diameter) = 7.62 m Powered by EBPC

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Mw (Wind moment) = 381923.2178 N.m P (Design pressure) = 0.4 kPa Theta angle (Angle between the roof and a horizontal plane at the roof-to-shell junction) = 9.4623 deg W_framing (Weight of framing supported by the shell and roof) = 1337.0416 N W_structural (Weight of roof attached structural) = 16864.7513 N Wr (Roof plates weight) = 39897.464 N Ws (Shell plates weight) = 90511.2095 N Uplift due to internal pressure API-650 F.1.2 P_uplift = P * pi * ((ID^2) / 4) = 400.0 * pi * ((7.62^2) / 4) = 18241.4692 N Tank design does not have to meet App. F requirements. Maximum allowable internal pressure for th e actual resisting area API 650 F.5.1 P_F51 = ((Fy * TAN(Theta angle) * A_actual) / (200 * (D^2))) + ((0.00127 * DLR) / (D^2)) = ((205 * TAN(9.4623) * 2275.401) / (200 * (7.6279^2))) + ((0.00127 * 56762.2153) / (7.6279^2)) = 7.9196 kPa Maximum allowable internal pressure P_max_internal = MIN(P_std , P_F51) = MIN(18 , 7.9196) = 7.9196 kPa Maximum allowable external pressur e P-ext-2a = -(Max-p - DL - MAX(S , Lr)) / Fp P-ext-2a = -(6.4135 - 0.8749 - MAX(0 , 1)) / 0.4 P-ext-2a = -11.3464 kPa P-ext-2b = -(Max-p - DL - Fp * MAX(S , Lr)) P-ext-2b = -(6.4135 - 0.8749 - 0.4 * MAX(0 , 1)) P-ext-2b = -5.1386 kPa P-ext-2 = MAX (P-ext-2a , P-ext-2b) P-ext-2 = MAX (-11.3464 ,-5.1386) P-ext-2 = -5.1386 kPa P-max-ext-T = MAX(P-ext-1 , P-ext-2) P-max-ext-T = MAX(-0.6361 , -5.1386) P-max-ext-T = -0.6361 kPa 7.5 SUMMARY OF ROOF RESULTS Material = A283M-C t-actual = 11.1 mm t-cone = 10.5143 mm P-Max-Internal = 7.9196 kPa P-Max-External = -0.6361 kPa Roof Plates Weight = 39,897.4639 N Powered by EBPC

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7.6 SHELL COURSE DESIGN (BOTTOM COURSE IS #1) API-650 ONE FOOT METHOD D = Tank Nominal diameter (m) per API-650 5.6.1.1 Note 1 H = Max liquid level (m) I-p = Design internal pressure (kPa) L = Factor I-p = 0.4 kPa D = 7.62 m H = 6.035 m L = (500 * D (t-1 - Ca-1))^0.5 L = (500 * 7.62 (7.9 - 3.2))^0.5 = 133.817 Course # 1 Ca-1 = Corrosion allowance per API-650 5.3.2 (mm) G = Design specific gravity of the liquid to be stored H' = Effective liquid head at design pressure (m) hmax-1 = Max liquid level based on shell thickness (m) JE = Joint efficiency pmax-1 = Max pressure at design (kPa) pmax-int-shell-1 = Max internal pressure at design (kPa) Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa) St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa) t-1 = Shell actual thickness (mm) t-calc-1 = Shell thickness design condition td (mm) t-seismic-1 = See E.6.2.4 table in SEISMIC calculations. t-test-1 = Shell thickness hydrostatic test condition (mm) Material = A283M-C Width = 1.8288 m Ca-1 = 3.2 mm JE = 0.85 t-1 = 7.9 mm Sd = 137 MPa St = 154 MPa Design Con dition G = 0.789 (per API-650) H' = H H' = 6.035 H' = 6.035 m t-calc-1 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-1 (per API-650 5.6.3.2) t-calc-1 = (4.9 * 7.62 * (6.035 - 0.3) * 0.789)/137 + 3.2 t-calc-1 = 4.4332 mm hmax-1 = Sd * (t-1 - CA-1)/(2.6 * D * G) + 1 hmax-1 = 137 * (7.9 - 3.2)/(2.6 * 7.62 * 0.789) + 1 Powered by EBPC

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hmax-1 = 22.1568 m pmax-1 = (hmax-1 - H) * 9.8 * G pmax-1 = (22.1568 - 6.035) * 9.8 * 0.789 pmax-1 = 124.6566 kPa pmax-int-shell-1 = pmax-1 pmax-int-shell-1 = 124.6566 kPa Hydrostatic Test Conditio n G = 1 H' = H H' = 6.035 H' = 6.035 m t-test-1 = (* 4.9 D (H' - 0.3))/St t-test-1 = (* 4.9 7.62 (6.035 - 0.3))/154 t-test-1 = 1.3905 mm Course # 2 Ca-2 = Corrosion allowance per API-650 5.3.2 (mm) G = Design specific gravity of the liquid to be stored H' = Effective liquid head at design pressure (m) hmax-2 = Max liquid level based on shell thickness (m) JE = Joint efficiency pmax-2 = Max pressure at design (kPa) pmax-int-shell-2 = Max internal pressure at design (kPa) Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa) St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa) t-2 = Shell actual thickness (mm) t-calc-2 = Shell thickness design condition td (mm) t-seismic-2 = See E.6.2.4 table in SEISMIC calculations. t-test-2 = Shell thickness hydrostatic test condition (mm) Material = A283M-C Width = 1.8288 m Ca-2 = 3.2 mm JE = 0.85 t-2 = 6.35 mm Sd = 137 MPa St = 154 MPa Design Con dit ion G = 0.789 (per API-650) H' = H H' = 4.2062 H' = 4.2062 m t-calc-2 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-2 (per API-650 5.6.3.2) Powered by EBPC

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t-calc-2 = (4.9 * 7.62 * (4.2062 - 0.3) * 0.789)/137 + 3.2 t-calc-2 = 4.04 mm hmax-2 = Sd * (t-2 - CA-2)/(2.6 * D * G) + 1 hmax-2 = 137 * (6.35 - 3.2)/(2.6 * 7.62 * 0.789) + 1 hmax-2 = 14.9503 m pmax-2 = (hmax-2 - H) * 9.8 * G pmax-2 = (14.9503 - 4.2062) * 9.8 * 0.789 pmax-2 = 83.0752 kPa pmax-int-shell-2 = MIN(pmax-int-shell-1 pmax-2) pmax-int-shell-2 = MIN(124.6566 83.0752) pmax-int-shell-2 = 83.0752 kPa Hydrostatic Test Conditio n G = 1 H' = H H' = 4.2062 H' = 4.2062 m t-test-2 = (* 4.9 D (H' - 0.3))/St t-test-2 = (* 4.9 7.62 (4.2062 - 0.3))/154 t-test-2 = 0.9471 mm Course # 3 Ca-3 = Corrosion allowance per API-650 5.3.2 (mm) G = Design specific gravity of the liquid to be stored H' = Effective liquid head at design pressure (m) hmax-3 = Max liquid level based on shell thickness (m) JE = Joint efficiency pmax-3 = Max pressure at design (kPa) pmax-int-shell-3 = Max internal pressure at design (kPa) Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa) St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa) t-3 = Shell actual thickness (mm) t-calc-3 = Shell thickness design condition td (mm) t-seismic-3 = See E.6.2.4 table in SEISMIC calculations. t-test-3 = Shell thickness hydrostatic test condition (mm) Material = A283M-C Width = 1.8288 m Ca-3 = 3.2 mm JE = 0.85 t-3 = 6.35 mm Sd = 137 MPa St = 154 MPa Design Co ndition G = 0.789 (per API-650) Powered by EBPC

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H' = H H' = 2.3774 H' = 2.3774 m t-calc-3 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-3 (per API-650 5.6.3.2) t-calc-3 = (4.9 * 7.62 * (2.3774 - 0.3) * 0.789)/137 + 3.2 t-calc-3 = 3.6467 mm hmax-3 = Sd * (t-3 - CA-3)/(2.6 * D * G) + 1 hmax-3 = 137 * (6.35 - 3.2)/(2.6 * 7.62 * 0.789) + 1 hmax-3 = 14.9503 m pmax-3 = (hmax-3 - H) * 9.8 * G pmax-3 = (14.9503 - 2.3774) * 9.8 * 0.789 pmax-3 = 97.2159 kPa pmax-int-shell-3 = MIN(pmax-int-shell-2 pmax-3) pmax-int-shell-3 = MIN(83.0752 97.2159) pmax-int-shell-3 = 83.0752 kPa Hydrostatic Test Conditio n G = 1 H' = H H' = 2.3774 H' = 2.3774 m t-test-3 = (* 4.9 D (H' - 0.3))/St t-test-3 = (* 4.9 7.62 (2.3774 - 0.3))/154 t-test-3 = 0.5037 mm Course # 4 Ca-4 = Corrosion allowance per API-650 5.3.2 (mm) G = Design specific gravity of the liquid to be stored H' = Effective liquid head at design pressure (m) hmax-4 = Max liquid level based on shell thickness (m) JE = Joint efficiency pmax-4 = Max pressure at design (kPa) pmax-int-shell-4 = Max internal pressure at design (kPa) Sd = Allowable design stress for the design condition per API-650 Table 5-2b (MPa) St = Allowable stress for the hydrostatic test condition per API-650 5.6.2.2 (MPa) t-4 = Shell actual thickness (mm) t-calc-4 = Shell thickness design condition td (mm) t-seismic-4 = See E.6.2.4 table in SEISMIC calculations. t-test-4 = Shell thickness hydrostatic test condition (mm) Material = A283M-C Width = 1.8168 m Ca-4 = 3.2 mm JE = 0.85 t-4 = 6.35 mm Powered by EBPC

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Sd = 137 MPa St = 154 MPa Design Condi tion G = 0.789 (per API-650) H' = H H' = 0.5486 H' = 0.5486 m t-calc-4 = (4.9 * D * (H' - 0.3) * G)/Sd + Ca-4 (per API-650 5.6.3.2) t-calc-4 = (4.9 * 7.62 * (0.5486 - 0.3) * 0.789)/137 + 3.2 t-calc-4 = 3.2535 mm hmax-4 = Sd * (t-4 - CA-4)/(2.6 * D * G) + 1 hmax-4 = 137 * (6.35 - 3.2)/(2.6 * 7.62 * 0.789) + 1 hmax-4 = 14.9503 m pmax-4 = (hmax-4 - H) * 9.8 * G pmax-4 = (14.9503 - 0.5486) * 9.8 * 0.789 pmax-4 = 111.3565 kPa pmax-int-shell-4 = MIN(pmax-int-shell-3 pmax-4) pmax-int-shell-4 = MIN(83.0752 111.3565) pmax-int-shell-4 = 83.0752 kPa Hydrostatic Test Conditio n G = 1 H' = H H' = 0.5486 H' = 0.5486 m t-test-4 = (* 4.9 D (H' - 0.3))/St t-test-4 = (* 4.9 7.62 (0.5486 - 0.3))/154 t-test-4 = 0.0603 mm

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7.7 SUMMARY OF SHELL RESULTS t-min-Seismic = See API-650 E.6.1.4, table in SEISMIC calculations. Shell API-650 Summary (Bottom is 1) tMin min ttCA Tensile Sd St Weigh t-min t-min Shel Width Materia Yield Weigh t-Des t-Test Ext- min Actua Statu (mm JE Strengt (MPa (MPa t CA Erectio Seismi l # (mm) l Strengt h (MPa) l s ) ) ) t (N) (N) n (mm) (mm) (mm) c (mm) Pe (mm h (MPa) (mm ) (mm) ) 1828. A283M0.8 4.433 1.390 1 3.2 205 380 137 154 26,569 15,813 6 3.8732 NA 6 7.9 OK 8 C 5 2 5 2 1828. A283M- 3.2 0.8 205 380 137 154 21,360 10,600 5 4.04 0.947 3.5853 NA 5 6.35 OK 8 C 5 1 1828. A283M0.8 3.646 0.503 3 3.2 205 380 137 154 21,360 10,600 5 3.4073 NA 5 6.35 OK 8 C 5 7 7 1816. A283M0.8 3.253 0.060 4 3.2 205 380 137 154 21,220 10,531 5 3.2347 NA 5 6.35 OK 8 C 5 5 3

Total Weight = 90,511.2095 N

7.8 INTERMEDIATE STIFFENER CALCULATIONS PER API-650 SECTION 5.9.7 D = Nominal diameter of the tank shell (m) Hu = Vertical Distance Between the Intermediate Stiffener (Per API-650 5.9.7) (m) L_act = Actual Transform Height Spacing between Stiffeners (m) L_0 = Uniform Maximum Transform Height Spacing between Stiffineres (m) V = Design wind speed (km/h) Wtr = Transposed width of each shell course (m) Zi = Required Intermediate Stiffener Section Modulus (per API-650 5.9.6.1) (cm^3) Zi-actual = Actual Top Comp Ring Section Modulus (cm^3) D = 7.62 m V = 180 km/h ME = 1 Hu = ME * 9.47 * tsmin * (SQRT (tsmin / D)^3) * (190 / V)^2 Hu = 1 * 9.47 * 6.35 * (SQRT (6.35 / 7.62)^3) * (190 / 180)^2 Hu = 50.9699 m (Maximum Height of Unstiffened Shell) Transforming c ourses (1) to (4) Wtr = Course-width * (SQRT (t-uniform / t-course)^5) Wtr-1 = 1.8288 * (SQRT (6.35 / 7.9)^5) = 1.0593 m Wtr-2 = 1.8288 * (SQRT (6.35 / 6.35)^5) = 1.8288 m Powered by EBPC

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Wtr-3 = 1.8288 * (SQRT (6.35 / 6.35)^5) = 1.8288 m Wtr-4 = 1.8168 * (SQRT (6.35 / 6.35)^5) = 1.8168 m Wtr = SUM(Wtr-n) Wtr = 6.5337 m For uniforml y spaced stiffeners L_0 = Hts/# of Stiffeners + 1 L_0 = 6.5337/(0 + 1) L_0 = 6.5337 m L_act = Wrt L_act = 6.5337 m Number of Intermediate Stiffeners Sufficient Since Hu >= L_act SUMMARY OF SHELL STIFFENING RESULTS Number of Intermediate stiffeners req'd (NS) = 0 7.9 FLAT BOTTOM: NON ANNULAR PL ATE DESIGN Ba = Area of bottom (cm^2) Bottom-OD = Bottom diameter (m) c = Factor ca-1 = Bottom (1st) shell course corrosion allowance (mm) Ca-bottom = Bottom corrosion allowance (mm) D-bottom = Density of bottom (kg/mm3) G = Design specific gravity of the liquid to be stored H = Max liquid level (m) H' = Effective liquid head at design pressure (m) JE = Bottom joint efficiency S = Maximum Stress in first shell course per API 650 Table 5.1.a S1 = Product stress in the first shell course per API 650 Table 5.1.a S2 = Hydrostatic test stress in the first shell course per API 650 Table 5.1.a t-1 = Bottom (1st) shell course thickness (mm) t-actual = Actual bottom thickness (mm) t-calc = Minimum nominal bottom plates thickness per API-650 5.4.1 (mm) t-min = Minimum nominal bottom plates thickness per API-650 5.4.1 (mm) t-test-1 = Bottom (1st) shell course test thickness (mm) t-vac = Vacuum calculations per ASME section VIII Div. 1 (mm) td-1 = Bottom (1st) shell course design thickness (mm) Material = A283M-C t-actual = 9.5 mm t-min = 6.0 + Ca-bottom t-min = 6.0 + 3.2 t-min = 9.2 mm Powered by EBPC

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t-calc = t-min t-calc = 9.2 mm Calculation of Hydrostatic Test Stress & Product Stress (per API-650 Section 5.5.1) Bottom-OD = 7.7364 m JE = 0.85 D-bottom = 0.00000784 kg/mm3 t-1 = 7.9 mm ca-1 = 3.2 mm G = 0.789 H = 6.035 m H' = 6.035 m St = 154 MPa Sd = 137 MPa Ca-bottom = 3.2 mm Product stress stress in first shell course S1 = ((td-1 - ca-1) / (t-1 - ca-1)) ca -1)) * Sd S1 = ((4.4332 - 3.2) / (7.9 - 3.2)) * 137 S1 = 35.947 MPa Hydrostatic test stress in first shell course S2 = (t-test-1 / t-1) * St S2 = (1.3905 / 7.9) * 154 S2 = 27.1054 MPa S = Max (S1, S2) S = Max (35.947 , 27.1054) S = 35.947 MPa ABS(E-p) < P-btm Then there is no uplift 7.10 SUMMARY OF BOTTOM B OTTOM RESULTS Material = A283M-C t-actual = 9.5 mm t-req = 9.2 mm NET UPLIFT DUE TO INTERNAL PRESSURE Net-Uplift = 0 N, (See roof r oof report for calculations)

7.11 WIND MOMENT (PER API-650 SECTION 5.11) Powered by EBPC


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A = Area resisting the compressive force, as illustrated in Figure F.1 P-F41 = Design pressure determined in F.4.1 P-v = Internal pressure Wind Velocity Specified By Purchaser (3-sec gust based on a 2 % annual probability of being exceeded [50-year mean recurrence interval]) V_entered = 180 kph Vs (Wind Velocity) = V_entered = 180 kph Vf = (Vs / 190)^2 Vf = (180 / 190)^2 Vf (Velocity Factor) = 0.8975 PWS = 0.86 * Vf PWS = 0.7718 kPa PWR = 1.44 * Vf PWR = 1.2924 kPa API-650 5.2.1.k Up li ft Chec k P-F41 = (A * Fy * TAN(Theta))/(200 * D^2) + (0.00127 * DLR)/D^2 P-F41 = (2275.4 * 205 * TAN(9.4623))/(200 T AN(9.4623))/(200 * 7.62^2) + ((0.00127 * 56762) / 7.62^2) P-F41 = 7.9361 kPa Wind-Uplift = MIN(PWR , (1.6 * P-F41 - Pv)) Wind-Uplift = MIN(1.2924 , 12.2977) Wind-Uplift = 1.2924 kPa Ap-Vert (Vertical Projected Area of Roof) = 2.4193 m^2 Horizon tal Proj ected Ar ea of Roo f (Per API-650 API-650 5.2.1 5.2.1.f) .f) Xw (Moment Arm of UPLIFT wind force on roof) = 3.81 m Ap (Projected Area of roof for wind moment) = 45.6037 m^2 M-roof (Moment Due to Wind Force on Roof) = Wind-Uplift * Ap * Xw M-roof = (1,292.41 * 45.6037 * 3.81) M-roof = 224,556 N-m Xs (Height from bottom to the Shell's center of gravity) = Shell Height/2 Xs = (7.3152/2) Xs = 3.6576 m As (Projected Area of Shell) = Shell Height * (D + 2 * t-ins) As = 7.3152 * (7.62 + 2 * 0) As = 55.7418 m^2 M-Shell (Moment Due to Wind Force on Shell) = (PWS * As * (Shell Height / 2)) Powered by EBPC


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M-Shell = (0.7718 * 55.7418 * (7.3152 / 2)) M-Shell = 157,367 N-m Mw (Wind moment) = M-roof + M-shell Mw = 224,556 + 157,367 Mw = 381,923.2178 N-m 7.12 RESISTANCE TO OVERTURNING (PER API-650 5.11.2) DLR = Nominal weight of roof plate plus weight of roof plates overlap plus any attached structural. DLS = Nominal weight of the shell and any an y framing (but not roof plates) support by the shell and roof. F-friction = Maximum of 40% of weight of tank MDL = Moment about the shell-to-bottom joint from the nominal weight of the shell MDLR = Moment about the shell-to-bottom joint from the nominal weight of the roof plate plus any attached structural. MF = Stabilizing moment due to bottom plate and liquid liqui d weight MPi = Destabilizing moment about the shell-to-bottom joint from design pressure Mw = Destabilizing wind moment tb = Bottom plate thickness less C.A. wl = Circumferential loading of contents along shell-to-bottom joint An un anc ho red tan k mus m us t meet m eet thes t hes e th ree cri c riter teria: ia: Mw = 381,923 m-N DLS = 91,848.2511 N DLR = 56,762.2153 N MPi = P * (Pi * D^2 / 4) * (D / 2) MPi = 0.4 * (3.1416 * 7.62^2 / 4) * (7.62 / 2) MPi = 69.5 m-N MDL = DLS * (D/2) MDL = 91,848.2511 * 7.62/2 MDL = 349,942 N-m MDLR = DLR * (D/2) MDLR = 56,762.2153 * 7.62/2 MDLR = 216,264 N-m tb = 6.3 mm wl-min-liq = 59 * tb * SQRT(fy-btm * H-min-liq) wl-min-liq = 59 * 6.3 * SQRT(205 * 0.609) wl-min-liq = 4,153.155 N/m wl = (min [59 * tb * SQRT(fy-btm * H-liq)] [140.8 * H-liq * D]) wl = (min [59 * 6.3 * SQRT(205 * 6.035)] [140.8 * 6.035 * 7.62]) wl = 6,474.9273 N/m MF = (D/2) * wl * Pi * D Powered by EBPC


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MF = 3.81 * 6,474.9273 * 3.1416 * 7.62 MF = 590,561 m-N MF-min-liq = (D/2) * wl-min-liq * Pi * D MF-min-liq = 3.81 * 4,153.155 * 3.1416 * 7.62 MF-min-liq = 378,798 m-N Criteria 1 0.6 * Mw + MPi < (MDL + MF-min-liq) / 1.5 + MDLR 0.6 * 381,923 + 69.5 < (349,942 + 378,798) / 1.5 + 216,264 Since 229,223 < 702,091, Tank is stable Criteria 2 Mw + Fp * MPi < (MDL + MF) / 2 + MDLR 381,923 + 0.4 * 69.5 < (349,942 + 590,561) / 2 + 216,264 Since 381,951 < 686,516, Tank is stable Criteria 3 M-shell + Fp * Mpi < MDL /1.5 + MDLR 157,366.9921 + 0.4 * 69.5 < 349,942 / 1.5 + 216,264 Since 157,395 < 449,559, Tank is stable 7.13 RESISTANCE TO SLIDING (PER API-650 5.11.4) F-wind = Vf * 18 * As F-wind = 0.8975 * 18 * 55.7418 F-wind = 41,734 N F-friction = 0.4 * [(W-roof-corroded * g) + (W-shell-corroded * g) + (W-btm-corroded * g) + (W-roof-struct * g) + (W-min-liquid * g)] F-friction = 0.4 * [(3,481.9717 * 9.8) + (4,848.3676 * 9.8) + (2,322.3374 * 9.8) + (0 * 9.8) + (21,913 * 9.8)] F-friction = 127,743 N No anchorage needed to resist sliding since F-friction > F-wind Anchorage Requi rement Tank does not require anchorage

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7.14 SITE GROUND MOTION CAL CULATIONS Af (Acceleration Coefficient for Sloshing Wave Height) = 0.099 Anchorage_System (Anchorage System) = mechanically anchored Av (Vertical Ground Acceleration Coefficient) = 0.0924 D (Nominal Tank Diameter) = 7.62 m H (Maximum Design Product Level) = 6.035 m I (Importance Factor) = 1.0 K (Spectral Acceleration Adjustment Coefficient) = 1.5 Q (MCE to Design Level Scale Factor) = 0.66 Rwc (Convective Force Reduction Factor) = 2 Rwi (Impulsive Force Reduction Factor) = 4 Sac (Convective Design Spectral Response Acceleration Parameter at Any Period) = 0.255 Sai (Impulsive Design Spectral Response Acceleration Parameter at Any Period) = 0.3 Seismic_Site_Class (Seismic Site Class) = seismic site class d Seismic_Use_Group (Seismic Use Group) = seismic use group i TL (Regional Dependent Transistion Period for Longer Period Ground Motion) = 12 sec Sloshing Coefficient API 650 Section E.4.5.2 Ks = 0.578 / SQRT(TANH(((3.68 * Liq_max) / D))) = 0.578 / SQRT(TANH(((3.68 * 6.035) / 7.62))) = 0.5797 Convective Natural Period API 650 Section E.4.5.2 Tc = 1.8 * Ks * SQRT(D) = 1.8 * 0.5797 * SQRT(7.62) = 2.8804 sec Impulsive Design Response Spectrum Acceleration Coefficient API 650 Sections E.4.6.2 Ai = Q * (I / Rwi) * Sai = 0.66 * (1.0 / 4) * 0.3 = 0.0495 Convective Design Response Spectrum Acceleration Coefficient API 650 Sections E.4.6.2 Ac = Q * K * (I / Rwc) * Sac = 0.66 * 1.5 * (1.0 / 2) * 0.255 = 0.1262 Ac = MIN(Ac , Ai) = MIN(0.1262 , 0.0495) = 0.0495 Design Spectral Response Acceleration at Short Period API 650 Sections E.4.6.1 SDS = Ai * (Rwi / I) = 0.0495 * (4 / 1.0) = 0.198 Design Spectral Response Acc eleration at a Period of 1 Second API 650 Sections E.4.6.1 SD1 = (Ac / K) * Tc * (Rwc / I) = (0.0495 / 1.5) * 2.8804 * (2 / 1.0) = 0.1901 Vertical Ground Acceleration Coefficient API 650 Section E.6.1.3 and E.2.2 Av = (2 / 3) * 0.7 * SDS = (2 / 3) * 0.7 * 0.198 = 0.0924 Vertical Ground Acceleration Coefficient Specified by user (Av) = 0.0924

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7.15 SEISMIC CALCULATIONS < Mapped ASCE7 Method > Ac = Convective spectral acceleration parameter Ai = Impulsive spectral acceleration parameter Av = Vertical Earthquake Acceleration Coefficient Ci = Coefficient for impulsive period of tank system (Fig. E-1) D/H = Ratio of Tank Diameter to Design Liquid Level Density = Density of tank product (SG * 62.42786) Fc = Allowable longitudinal shell-membrane compressive stress Fty = Minimum specified yield strength of shell course Fy = Minimum yield strength of bottom annulus Ge = Effective specific gravity including vertical seismic effects I = Importance factor defined by Seismic Use Group k = Coefficient to adjust spectral acceleration from 5% - 0.5% damping L = Required Annular Ring Width Ls = Actual Annular Plate Width Mrw = Ringwall moment-portion of the total overturning moment that acts at the base of the tank shell perimeter Ms = Slab moment (used for slab and pile cap design) Pa = Anchorage chair design load Pab = Anchor seismic design load Q = Scaling factor from the MCE to design level spectral accelerations RCG = Height from Top of Shell to Roof Center of Gravity Rwc = Force reduction factor for the convective mode using allowable stress design methods (Table E-4) Rwi = Force reduction factor for the impulsive mode using allowable stress design methods (Table E-4) S0 = Design Spectral Response Param. (5% damped) for 0-second Periods (T = 0.0 sec) Sd1 = The design spectral response acceleration param. (5% damped) at 1 second based on ASCE7 methods per API 650 E.2.2 Sds = The design spectral response acceleration param. (5% damped) at short periods (T = 0.2 sec) based on ASCE7 methods per API 650 E.2.2 SigC = Maximum longitudinal shell compression stress SigC-anchored = Maximum longitudinal shell compression stress SUG = Seismic Use Group (Importance factors depends on SUG) T-L = Regional Dependent Transition Period for Long Period Ground Motion (Per ASCE 7-05, fig. 22-15) ta = Actual Annular Plate Thickness less C.A. ts1 = Thickness of bottom Shell course minus C.A. tu = Equivalent uniform thickness of tank shell V = Total design base shear Vc = Design base shear due to convective component from effective sloshing weight Vi = Design base shear due to impulsive component from effective weight of tank and contents wa = Force resisting uplift in annular region Wab = Design uplift load on anchor per unit circumferential length Wc = Effective Convective (Sloshing) Portion of the Liquid Weight Weff = Effective Weight Contributing to Seismic Response Wf = Weight of Floor (Incl. Annular Ring) Wi = Effective Impulsive Portion of the Liquid Weight wint = Uplift load due to design pressure acting at base of shell Powered by EBPC

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Wp = Total weight of Tank Contents based on S.G. Wr = Weight Fixed Roof, framing and 10 % of Design Snow Load & Insul. Wrs = Roof Load Acting on Shell, Including 10% of Snow Load Ws = Weight of Shell (Incl. Shell Stiffeners & Insul.) wt = Shell and roof weight acting at base of shell Xc = Height to center of action of the lateral seismic force related to the convective liquid force for ringwall moment Xcs = Height to center of action of the lateral seismic force related to the convective liquid force for the slab moment Xi = Height to center of action of the lateral seismic force related to the impulsive liquid force for ringwall moment Xis = Height to center of action of the lateral seismic force related to the impulsive liquid force for the slab moment Xr = Height from Bottom of Shell to Roof Center of Gravity Xs = Height from Bottom to the Shell's Center of Gravity g = 9.8 m/s^2 WEIGHTS Ws = 9,365.9151 kgf or 91,848.2511 N Wf = 3,501.9373 kgf or 34,342.2733 N Wr = 4,068.4091 kgf or 39,897.4639 N EFFECTIVE WEIGHT OF PRODUCT D/H = 1.2626 Wp = 217,147 kgf Wi = (1 - (0.218 * D/H)) * Wp Wi = (1 - (0.218 * 1.2626)) * 217,147 Wi = 157,376 kgf Wc = 0.23 * D/H * TANH (3.67 * H/D) * Wp Wc = 0.23 * 1.2626 * TANH (3.67 * 0.792) * 217,147 Wc = 62,685 kgf Weff = Wi + Wc Weff = 157,376 + 62,685 Weff = 220,061.4331 kgf Wrs = 4,068.4091 kgf DESIGN LOADS Vi = Ai * (Ws + Wr + Wf + Wi) Vi = 0.0495 * (9,365.9151 + 4,068.4091 + 3,501.9373 + 157,376) Vi = 8,628.474 kgf Vc = Ac * Wc Vc = 0.0495 * 62,685 Vc = 3,102.9119 kgf Powered by EBPC

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V = SQRT (Vi^2 + Vc^2) V = SQRT (8,628.474^2 + 3,102.9119^2) V = 9,169.4397 kgf CENTER OF ACTION FOR EFFECTIVE LATERAL FORCES Xs = 3.0175 m RCG = 1/3 * R * (TAND (Theta)) RCG = 1/3 * 3830.85 * (TAND (9.4623)) RCG = 212.825 mm or 0.2128 m Xr = Shell Height + RCG Xr = 7.3152 + 0.2128 Xr = 7.528 m CENTER OF ACTION FOR RINGWALL OVERTURNING MOMENT Xi = (0.5 - (0.094 * D/H)) * H Xi = (0.5 - (0.094 * 1.2626)) * 6.035 Xi = 2.3012 m Xc = (1 - (COSH (3.67 * H/D) - 1) / ((3.67 * H/D) * SINH (3.67 * H/D))) * H Xc = (1 - (COSH (3.67 * 0.792) - 1) / ((3.67 * 0.792) * SINH (3.67 * 0.792))) * 6.035 Xc = 4.1739 m CENTER OF ACTION FOR SLAB OVERTURNING MOMENT Xis = (0.5 + (0.06 * D/H)) * H) Xis = (0.5 + (0.06 * 1.2626)) * 6.035) Xis = 3.4747 m Xcs = (1 - (COSH (3.67 * H/D) - 1.937) / ((3.67 * H/D) * SINH(3.67 * H/D))) * H Xcs = (1 - (COSH (3.67 * 0.792) - 1.937) / ((3.67 * 0.792) * SINH(3.67 * 0.792))) * 6.035 Xcs = 4.3872 m Dynamic Liquid Hoop Forces

SHELL

Width Y (m) Ni (N/mm) (m)

SUMMARY

= 2.6 * Ai * G * D^2

Shell 1 Shell 2 Shell 3 Shell 4

1.8288 1.8288 1.8288 1.8168

5.7302 3.9014 2.0726 0.2438

5.8961 5.3227 3.5145 0.4942

Nc (N/mm)

Nh (N/mm)

Sig T+ (MPa)

Sig T- (MPa)

= 1.85 * Ac * G * D^2 * (COSH (3.68 * (H - Y)) / D) / (COSH (3.68 * H / D)) 0.4586 0.7165 1.5708 3.7322

= 4.9011293 * Y*D*G

= (+ Nh (SQRT (Ni^2 + Nc^2 + (Av * Nh / 2.5)^2))) / t-n 22.4615 19.1824 10.3204 1.7256

= (- Nh (SQRT (Ni^2 + Nc^2 + (Av * Nh / 2.5)^2))) / t-n 20.2849 17.0255 8.9148 0.5369

168.8487 114.9604 61.0722 7.1839

Overturning Moment Powered by EBPC

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Overturning Moment Mrw = ((Ai * [(Wi * g) * Xi + (Ws * g) * Xs + (Wr * g) * Xr])^2 + [Ac * (Wc * g) * Xc]^2)^0.5 Mrw = ((0.0495 * [(157,376 * 9.8) * 2.3012 + (9,365.9151 * 9.8) * 3.0175 + (4,068.4091 * 9.8) * 7.528])^2 + [0.0495 * (62,685 * 9.8) * 4.1739]^2)^0.5 Mrw = 240,636.2692 N-m Ms = ((Ai * [(Wi * g) * Xis + (Ws * g) * Xs + (Wr * g) * Xr])^2 + [Ac * (Wc * g) * Xcs]^2)^0.5 Ms = ((0.0495 * [(157,376 * 9.8) * 3.4747 + (9,365.9151 * 9.8) * 3.0175 + (4,068.4091 * 9.8) * 7.528])^2 + [0.0495 * (62,685 * 9.8) * 4.3872]^2)^0.5 Ms = 322,923.5235 N-m RESISTANCE TO DESIGN LOADS Fy = 205 MPa Ge = S.G. * (1- 0.4 * Av) Ge = 0.789 * (1- 0.4 * 0.0924) Ge = 0.7598 wa = MIN (99 * ta * (Fy * H * Ge)^0.5 , 201.1 * H * D * Ge) wa = MIN (99 * 6.3 * (205 * 6.035 * 0.7598)^0.5) , 201.1 * 6.035 * 7.62 * 0.7598) wa = MIN ( 19,122.8217 , 7,026.9302) wa = 7,026.9302 N/m wt = (Wrs + Ws) / (Pi * D) wt = (4,068.4091 + 9,365.9151) / (3.1416 * 7.62) wt = 5,503.4072 N/m wint = P * (Pi * D^2 / 4) / (Pi * D) wint = 400 * (3.1416 * 7.62^2 / 4) / (3.1416 * 7.62) wint = 762 N/m Anchorage Ratio J = Mrw / (D^2 * [wt * (1 - 0.4 * Av)] + wa - 0.4 * wint J = 240,636.2692 / (7.62^2 * [5,503.4072 * (1 - 0.4 * 0.0924)] + 7,026.9302 - 0.4 * 762 J = 0.3447 Since J <= 0.785, The tank is self-anchored, per API 650 Table E-6 Maximum Longit udinal Shell-Membrane Compressive Stress ts1 = 4.7 mm SigC = [wt * (1 + (0.4 * Av)) + (1.273 * Mrw) / D^2] * (1 / (1,000 * ts)) SigC = [5,503.4072 * (1 + (0.4 * 0.0924)) + (1.273 * 240,636.2692) / 7.62^2] * (1 / (1,000 * 4.7)) SigC = 2.3367 MPa Allo wab le Longi tudinal Shel l-Mem brane Compression Stress Powered by EBPC

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Fty = 205 MPa Criteria for Fc Since [G * H * D^2 / ts1^2] < 44 Since [0.789 * 6.035 * 7.62^2 / 4.7^2] < 44 Since 12.5161 < 44 Then Fc = (83 * ts) / (2.5 * D) + (7.5 * SQRT(G * H)) Fc = (83 * ts) / (2.5 * D) + (7.5 * SQRT(SG * H)) Fc = (83 * 4.7) / (2.5 * 7.62) + (7.5 * SQRT(0.789 * 6.035)) Fc = 36.8435 MPa Hoop Stresses SHELL SUMMARY Shell 1 Shell 2 Shell 3 Shell 4

SigT+ Sd * 1.333 Fy * 0.9 * E Allow able Membrane 22.4615 182.621 156.825 156.825 19.1824 182.621 156.825 156.825 10.3204 182.621 156.825 156.825 1.7256 182.621 156.825 156.825

t-Min Shell Ok 3.8731 OK 3.5853 OK 3.4072 OK 3.2346 OK

Mechanically Anchored Number of anchor = 8 Max spacing = 3 m Actual spacing = 3.0787 m Minimum # anchor = 8 Wab = (1.273 * Mrw) / D^2 - wt * (1 - 0.4 * Av) + wint Wab = (1.273 * 240,636.2692) / 7.62^2 - 5,503.4072 * (1 - 0.4 * 0.0924) + 762 Wab = 737.692 N/m Pab = Wab * Pi * D / Na Pab = 737.692 * 3.1416 * 7.62 / 8 Pab = 2,207.4452 N Pa = 3 * Pab Pa = 3 * 2,207.4452 Pa = 6,622.3357 N Shell Compression in Mechanically-Anchor ed Tanks SigC-anchored = [Wt * (1 + (0.4 * Av)) + (1.273 * Mrw) / D^2] * (1 / (1,000 * ts)) SigC-anchored = [5,503.4072 * (1 + (0.4 * 0.0924)) + (1.273 * 240,636.2692) / 7.62^2] * (1 / (1,000 * 4.7)) SigC-anchored = 2.3367 MPa Powered by EBPC

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Fc = 36.8435 MPa SigC-anchored <= Fc Then the design is acceptable. Detailing Requirements (Anchorage) SUG = I Sds = 0.198 g or 19.8 %g Freeboard - Sloshin g TL-sloshing = 4 sec I-sloshing = 1.0 Tc = 2.8804 k = 1.5 Sd1 = 0.1901 g or 19.01 %g Af = 0.099 g per API 650 E.7.2 Delta-s = 0.42 * D * Af Delta-s = 0.42 * 7.62 * 0.099 Delta-s = 0.3168 m 0.7 * Delta-s = 0.2218 m Since Sds < 0.33g and SUG = I per API 650 Table E-7. a. A freeboard of O.7*Delta-s is recommended for economic considerations but not required. Sliding Resistance mu = 0.4 (friction coefficient) V = 9,169.4397 kgf Vs = mu * (Ws + Wr + Wf + Wp) * (1 - 0.4 * Av) Vs = 0.4 * (9,365.9151 + 4,068.4091 + 3,501.9373 + 217,147) * (1 - 0.4 * 0.0924) Vs = 90,172.6176 kgf Since V <= Vs Then the tank will not experience major sliding and does not require additional lateral anchorage, per API 650 E.7.6. Local Shear Transfer Vmax = 2 * V / (Pi * D) Vmax = 2 * 9,169.4397 / (3.1416 * 7.62) Vmax = 766.0691 kgf/m

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7.16 ANCHOR BOLT DESIGN Bolt Material : A36M Sy = 250 MPa UPLIFT LOAD CASES, PER API-650 TABLE 5-21b A-s-r = Bolt Root Area Req'd bt = Uplift load per bolt D = Tank D (m) Fp = Pressure Combination Factor Mrw = Seismic Ringwall Moment (Nm) N = Anchor bolt quantity P = Design pressure (pa) Pf = Failure pressure per F.6 (KPa) Pt = Test pressure per F.7.6 = 1.25 * P = 0.5 (pa) sd = Allowable Anchor Bolt Stress (MPa) Shell-sd-at-anchor = Allowable Shell Stress at Anchor Attachment (MPa) t-actual = Actual Roof plate thickness (mm) t-h = Roof plate thickness less CA (mm) Vf = Velocity factor (kph) W1 = Dead Load of Shell minus C.A. and Any Dead Load minus C.A. other than Roof Plate Acting on Shell W2 = Dead Load of Shell minus C.A. and Any Dead Load minus C.A. including Roof Plate minus C.A. Acting on Shell W3 = Dead Load of New Shell and Any Dead Load other than Roof Plate Acting on Shell For Tank wi th Structural Supported Roof W1 = W-shell-corroded + Shell Insulation W1 = 47,546.2439 + 0 W1 = 47,546.2439 N W2 = W-shell-corroded + Shell Insulation + Corroded Roof Plates Supported by Shell + Roof Dead Load Supported by Shell W2 = 47,546.2439 + 0 + 34,146.4781 + 0 W2 = 81,692.722 N W3 = New Shell + Shell Insulation W3 = 90,511.2095 + 0 W3 = 90,511.2095 N Uplift Case 1: Design Pressure Only U = [(P - 0.08 * t-h) * D^2 * 785] - W1 U = [(0.4 - 0.08 * 9.5) * 7.62^2 * 785] - 47,546.2439 U = -63,955.243346529656 N bt = U/N Powered by EBPC

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bt = -7,994.405418316207 N sd = 104.1666 MPa Shell-sd-at-anchor = 136.6666 MPa A-s-r = N.A., since Load per Bolt is zero Uplift Case 2: Test Pressure Only U = [(Pt - 0.08 * t-h) * D^2 * 785] - W1 U = [(0.5 - 0.08 * 9.5) * 7.62^2 * 785] - 47,546.2439 U = -59,397.18794652966 N bt = U/N bt = -7,424.648493316207 N sd = 138.8888 MPa Shell-sd-at-anchor = 170.8333 MPa A-s-r = N.A., since Load per Bolt is zero Uplift Case 3: Failure Pressure Only Not applicable since if there is a knuckle on tank roof, or tank roof is not frangible. Pf (failure pressure per F.6) = N.A. Uplift Case 4: Wind Load Only PWR = Wind-Uplift per API 650 Table 5-21a, 5-21b PWS = Wind-Pressure per API 650 Table 5-21a, 5-21b PWR = 1.2924 KPa PWS = 771.8559 N/m^2 MWH = PWS * D * (H^2 / 2) per API 650 Table 5-21a, 5-21b MWH = 771.8559 * 7.62 * (7.3152^2 / 2) MWH = 157,366.9921 Nm U = PWR * D^2 * 785 + (4 * MWH / D) - W2 U = 1.2924 * 7.62^2 * 785 + (4 * 157,366.9921 / 7.62) - 81,692.722 U = 59,823.3854 N bt = U/N bt = 7,477.9231 N sd = 200 MPa Shell-sd-at-anchor = 170.8333 MPa A-s-r = bt / sd A-s-r = 7,477.9231 / 200 A-s-r = 37.3896 mm^2 Uplift Case 5: Seismic Load Only Powered by EBPC

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U = [4 * Mrw / D] - W2 * (1 - 0.4 * Av) U = [4 * 240,636 / 7.62] - 81,692.722 * (1 - 0.4 * 0.0924) U = 47,644.8924 N bt = U/N bt = 5,955.6115 N sd = 200 MPa Shell-sd-at-anchor = 170.8333 MPa A-s-r = bt / sd A-s-r = 5,955.6115 / 200 A-s-r = 29.778 mm^2 Uplift Case 6: Design Pressure + Wind Load U = [(Fp * P + PWR - 0.08 * t-h) * D^2 * 785] + [4 * MWH / D] - W1 U = [(0.4 * 0.4 + 1.2924 - 0.08 * 9.5) * 7.62^2 * 785] + [4 * 157,366.9921 / 7.62] - 47,546.2439 U = 66,621.5311 N bt = U/N bt = 8,327.6913 N sd = 138.8888 MPa Shell-sd-at-anchor = 170.8333 MPa A-s-r = bt / sd A-s-r = 8,327.6913 / 138.8888 A-s-r = 59.9593 mm^2 Uplift Case 7: Design Pressure + Seismic Load U = [(Fp * P - 0.08 * t-h) * D^2 * 785] + [4 * Mrw / D] - W1 * (1 - 0.4 * Av) U = [(0.4 * 0.4 - 0.08 * 9.5) * 7.62^2 * 785] + [4 * 240,636 / 7.62] - 47,546.2439 * (1 - 0.4 * 0.0924) U = 53,180.9844 N bt = U/N bt = 6,647.623 N sd = 200 MPa Shell-sd-at-anchor = 170.8333 MPa A-s-r = bt / sd A-s-r = 6,647.623 / 200 A-s-r = 33.2381 mm^2 Uplift Case 8: Frangibili ty Pressure Not applicable since if there is a knuckle on tank roof, or tank roof is not frangible. Pf (failure pressure per F.6) = N.A. Powered by EBPC

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7.17 ANCHOR BOLT SUMMARY Bolt Root Area Req'd = 59.9593 mm^2 Bolt Diameter (d) = 64 mm (M64) Threads per centimeters (n) = 0.1667 A-s = Actual Bolt Root Area A-s = (pi / 4) * (d - 33.02 / n)^2 A-s = 0.7854 * (64 - 33.02 / 0.1667)^2 A-s = 2480.6388 mm^2 Exclusive of Corrosion Bolt Diameter Req'd = 16.0986 mm (per ANSI B1.1) Actual Bolt Diameter = 64 mm (M64) Bolt Diameter Meets Requirements ANCHORAGE REQUIREMENTS Wind or Uplift calculations require anchorage Minimum # Anchor Bolts = 8 per API-650 5.12.3 Actual # Anchor Bolts = 8 Anchorage Meets Spacing Requirements ANCHOR CHA IR DESIGN (from AISI 'Steel Plate Engr Data' Dec. 92, Vol. 2, Part VII) Entered Parameters Chair Material : A283M-C Top Plate Type : DISCRETE Chair Style : VERT. TAPERED Top Plate Width (a) : 200 mm Top Plate Length (b) : 200 mm Vertical Plate Width (k) : 125 mm Top Plate Thickness (c) : 26 mm Bolt Eccentricity (e) : 102 mm Outside of Top Plate to Hole Edge (f) : 59 mm Distance Between Vertical Plates (g) : 108 mm Chair Height (h) : 315 mm Vertical Plates Thickness (j) : 32 mm Bottom Plate thickness (m) : 9.5 mm Shell Course + Repad Thickness (t) : 7.9 mm Nominal Radius to Tank Centerline (r) : 3813.95 mm Design Load per Bolt (P) : 12492 N Bolt Diameter (d) = 64 mm (M64) Threads per unit length (n) = 0.1667 Powered by EBPC

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Bolt Yield Load = A-s * Sy Bolt Yield Load = 2480.6388 * 250 Bolt Yield Load = 620,159.6943 N Seismic Design Bolt Load (Pa) = 6,622.3357 N Anchor Chairs will be designed to withstand Design Load per Bolt Anchor Chair Design Load, (P) : 12,491.537 N For anchor Chair Material: A283M-C (per API-650 Table 5-2b, Sd-Chair = 137 MPa Since bottom t <= 10 mm, and Seismic anchorage required (J) > 1.45, or Wind Speed is > 160.9344 kph, h-min is 305 mm. For Discrete Top Plate, Max. Chair Height Recommended : h <= 3 * a h-max = 3 * a h-max = 3 * 200 = 600 mm. h-actual = 315 mm. e-min = 0.886 * d + 15 e-min = 0.886 * 64 + 15 = 71.704 mm. e-actual = 102 mm. g-min = d + 26 g-min = 64 + 26 = 90 mm. g-actual = 108 mm. f-min = d/2 + 4 f-min = 64/2 + 4 = 36 mm. c-min = SQRT[P / Sd-Chair / f * (0.375 * g - 0.22 * d)] c-min = SQRT[12,491.537 / 137 / 59 * (0.375 * 108 - 0.22 * 64)] = 6.3898 mm. c-actual = 26 mm. j-min = MAX(13, [0.04 * (h - c)]) j-min = MAX(13, [0.04 * (315 - 26)]) = 13 mm. j-actual = 32 mm. b-min = e-min + d + 7 b-min = 71.704 + 64 + 7 = 142.704 mm. Powered by EBPC

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Stress due to Top Plate Thickness S-actual-Top-Plate = P / (f * c^2) * (0.375 * g - 0.22 * d) S-actual-Top-Plate = 12,491.537 / (59 * 26^2) * (0.375 * 108 - 0.22 * 64) = 8.2746 MPa Shell Stress due to Chair Height (For discrete Top Plate) S-actual-ChairHeight = P * e / t^2 * F3 Where F3 = F1 + F2 now F1 = (1.32 * z) / (F6 + F7) where F6 = (1.43 * a * h^2) / (r * t) and F7 = (4 * a * h^2)^(1/3) and z = 26 / (F4 * F5 + 26) where F4 = (0.177 * a * m) / SQRT(r * t) and F5 = (m / t)^2 yields F5 = (9.5 / 7.9)^2 F5 = 1.446 yields F4 = (0.177 * 200 * 9.5) / SQRT(3,810 * 7.9) F4 = 1.9384 yields z = 26 / (1.9384 * 1.446 + 26) z = 0.9026 yields F7 = (4 * 200 * 315^2)^(1/3) F7 = 429.7709 yields F6 = (1.43 * 200 * 315^2) / (3,810 * 7.9) F6 = 942.8336 yields F1 = (1.32 * 0.9026) / (942.8336 + 429.7709) F1 = 0.0008 now F2 = 0.031 / SQRT(r * t) yields F2 = 0.031 / SQRT(3,810 * 7.9) F2 = 0.0057 yields F3 = 0.0008 + 0.0057 F3 = 0.0066 yields S-actual-ChairHeight = 12,491.537 * 102 / 7.9^2 * 0.0066 yields S-actual-ChairHeight = 135.3979 MPa Maximum Recommended Stress is 170 MPa for the Shell (per API-650 E.6.2.1.2) Sd-ChairHeight = 170 MPa ANCHOR CHAIR SUMMARY S-actual-Top-Plate Meets Design Calculations (within 105% of Sd-Chair) S-actual-Top-Plate/Sd-Chair 8.2746/137 = 6.03% S-actual-ChairHeight Meets Design Calculations (within 105% of Sd-ChairHeight) S-actual-ChairHeight/Sd-ChairHeight 135.3979/170 = 79.64%

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7.18 NORMAL AND EMERGENCY VENTING (API-2000 6TH EDITION) NORMAL VENTING T_boil (Product boiling point) = 49 degc T_flash (Product flash point) = 12 degc Vpe (Maximum emptying rate) = 13.2 m^3/hr Vpf (Maximum filling rate) = 72.0 m^3/hr Vtk (Tank capacity) = 340.8116 m^3 In-breathing Required in-breathing flo w rate due to liquid movement API-2000 A.3.4.1.1 Vip = 0.94 * Vpe = 0.94 * 13.2 = 12.408 m^3/hr As per API-2000 A.3.4.1.2 Table A.3 Column 2, Required in-breathing flow rate due to thermal effects (VIT) = 57.3584 m^3/hr Total required in-breathing volu metric flow rate Vi = Vip + VIT = 12.408 + 57.3584 = 69.7664 m^3/hr Out-breathing (T_flash < 37.8) OR (T_boil < 148.9) ==> Use API-2000 section A.3.4.2.2 Required out-breathing flo w rate due to liquid movement API-2000 A.3.4.2.2 Vop = 2.02 * Vpf = 2.02 * 72.0 = 145.44 m^3/hr As per API-2000 A.3.4.2.2 Table A.3 Column 4, Required out-breathing flow rate due to thermal effects (VOT) = 57.3584 m^3/hr Total required out-breathing volu metric flow rate Vo = Vop + VOT = 145.44 + 57.3584 = 202.7984 m^3/hr EMERGENCY VENTING D (Tank diameter) = 7.62 m H (Tank height) = 7.3152 m Pg (Design pressure) = 0.4 kPa inslation_type (Insulation type) = no insulation vapour_pressure_type (Vapour pressure type) = hexane or similar As per API-2000 Table 9, Environmental factor for insulation (F_ins) = 1.0 As per API-2000 Table 9, Environmental factor for drainage (F_drain) = 0.5 Environmental factor API-2000 4.3.3.3.4 F = MIN(F_ins , F_drain) = MIN(1.0 , 0.5) = 0.5 Powered by EBPC

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Wetted surface area ATWS = pi * D * MIN(H , 9.14) = pi * 7.62 * MIN(7.3152 , 9.14) = 175.1181 m^2 Required emergency venting capacity API-2000 Table 5 and 4.3.3.3.4 q = 17419.7982 * F = 17419.7982 * 0.5 = 8709.8991 m^3/hr

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7.19 FLOATING ROOF DESIGN

Figura 4.

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Datos generales

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Figura 5.

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Datos de la membrana propuesta.

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Figura 6.

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Datos de la membrana propu esta (continuación).

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Figura 7.

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7.20 PLAN VIEW APPURTENANCE MARK

CUST. MARK

N-14

N-14 MUESTREO N-15 VALVULA DE PRESION VACIO N-16 BOQUILLA DE EMERGENCIA N-2 TRANSMISOR INDICADOR TEMPERATURA N-3 INTERRUPTOR NIVEL DESPLAZAMIENTO N-5 TRANSMISOR NIVEL N-13 ESCOTILLA

N-15 N-16 N-2 N-3 N-5 RM01 WR01A WS01AB

OUTSIDE INSIDE RADIUS DESCRIPTION PROJ PROJ ORIENT (mm) (mm) (mm) N-14 MUESTREO 178mm 7200mm 65' 3410mm N-15 VALVULA DE 203mm 0mm 30' 1500mm PRESION VACIO N-16 BOQUILLA DE 203mm 0mm 0' 1499mm EMERGENCIA N-2 TRANSMISOR INDICADOR 203mm 0mm 45' 2846mm TEMPERATURA N-3 INTERRUPTOR NIVEL 178mm 0mm 55' 3410mm DESPLAZAMIENTO N-5 TRANSMISOR 203mm 7200mm 45' 3410mm NIVEL N-13 ESCOTILLA 242mm 0mm 75' 2000mm BARANDAL --- 96.79' 3733mm ESCALERA 609 5/8" BOTTOM --10' 3000mm SUMP

7.21 ELEVATION VIEW APPURTENANCE MARK

CUST. MARK

AC01A N-9 N-10 N-1 N-11 Powered by EBPC

N-9 ENTRADA ETANOL ANHIDRO N-10 SALIDA ETANOL ANHIDRO N-1 BOQUILLA DISPONIBLE N-11 ESPUMA

OUTSIDE INSIDE ELEVATION DESCRIPTION PROJ PROJ ORIENT (mm) (mm) (mm) SEE ANCLAS ---TABLE N-9 ENTRADA ETANOL 200mm 0mm 190' 355mm ANHIDRO N-10 SALIDA ETANOL 175mm 0mm 180' 609mm ANHIDRO N-1 BOQUILLA 200mm 0mm 250' 306mm DISPONIBLE N-11 ESPUMA 175mm 0mm 0' 7100mm FOR-I-004-RA

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SUPERFICIAL SUPERFICIAL N-7 DREN N-7 DREN CON N-7 CON SUMIDERO SUMIDERO N-8 SWITCH N-8 SWITCH N-8 MUY ALTO MUY ALTO NIVEL NIVEL PEMEX TTV-368 / TVNP01A REFINACIÓN 369 PIPE PS01 SUPPORT CLIP 24" SHELL SM01 MANWAY N-4 SWITCH N-4 SWITCH SN03 MUY BAJO MUY BAJO NIVEL NIVEL

150mm

0mm

10'

175mm

150mm

0mm

115'

6035mm

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225'

1016mm

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40'

6200mm

272mm

0mm

341'

750mm

150mm

0mm

150'

609mm

Nozzle N-14 Reinfor cement Requir ements (Per API-650 and other references below) NOZZLE Description : 4 in SCH 80 TYPE RFWN t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Roof Material) CA = (Corrosion Allowance of Neck) MOUNTED ON ROOF: Elevation = 7.3997 ft ROOF PARAMETERS: t-calc = 10.5143 mm t_cr = 8.9143 mm (Roof t-calc less C.A) t_c = 10.5143 mm t_Basis = 8.9143 mm (FOR ROOF NOZZLE,REF. API-650 FIG 5-19, TABLE 5-14 AND FOOTNOTE A OF TABLE 5-14, or API-650 FIG 5-20, TABLE 5-15 AND FOOTNOTE A OF TABLE 5-15) Required Area = t_Basis * D Required Area = 8.9143 * 114.3 Required Area = 1018.9093 mm^2 Available Roof Area = (t_c - t_Basis) * D Available Roof Area = (10.5143 - 8.9143) * 114.3 Available Roof Area = 182.88 mm^2 Powered by EBPC

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Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (8.5598 - 3.2) + 10.5143] * (8.5598 - 3.2) * MIN((124.1056/137) 1) Available Nozzle Neck Area = 308.2974 mm^2 A-rpr = (Required Area - Available Roof Area - Available Nozzle Neck Area) A-rpr = 1018.9093 - 182.88 - 308.2974 A-rpr = 527.7319 mm^2 t_rpr = (A_rpr / D) + repad_CA t_rpr = (527.7319 / 114.3) + 3.2 t_rpr = 7.8171 mm Reinforcement Pad is required. Based on Roof Nozzle Size of 4 in Repad Size (OD) Must be 275 mm Nozzle N-3 Reinfo rcement Requi rements (Per API-650 and other references below) NOZZLE Description : 3 in SCH 80 TYPE RFWN t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Roof Material) CA = (Corrosion Allowance of Neck) MOUNTED ON ROOF: Elevation = 7.3997 ft ROOF PARAMETERS: t-calc = 10.5143 mm t_cr = 8.9143 mm (Roof t-calc less C.A) t_c = 10.5143 mm t_Basis = 8.9143 mm (FOR ROOF NOZZLE,REF. API-650 FIG 5-19, TABLE 5-14 AND FOOTNOTE A OF TABLE 5-14, or API-650 FIG 5-20, TABLE 5-15 AND FOOTNOTE A OF TABLE 5-15) Required Area = t_Basis * D Required Area = 8.9143 * 88.9 Required Area = 792.485 mm^2 Available Roof Area = (t_c - t_Basis) * D Available Roof Area = (10.5143 - 8.9143) * 88.9 Available Roof Area = 142.24 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (7.62 - 3.2) + 10.5143] * (7.62 - 3.2) * MIN((124.1056/137) 1) Available Nozzle Neck Area = 239.188 mm^2 Powered by EBPC

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A-rpr = (Required Area - Available Roof Area - Available Nozzle Neck Area) A-rpr = 792.485 - 142.24 - 239.188 A-rpr = 411.057 mm^2 t_rpr = (A_rpr / D) + repad_CA t_rpr = (411.057 / 88.9) + 3.2 t_rpr = 7.8238 mm Reinforcement Pad is required. Based on Roof Nozzle Size of 3 in Repad Size (OD) Must be 225 mm Nozzle N-2 Reinforcement Requirements (Per API-650 and other references below) NOZZLE Description : 8 in SCH 80 TYPE RFWN t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Roof Material) CA = (Corrosion Allowance of Neck) MOUNTED ON ROOF: Elevation = 7.4937 ft ROOF PARAMETERS: t-calc = 10.5143 mm t_cr = 8.9143 mm (Roof t-calc less C.A) t_c = 10.5143 mm t_Basis = 8.9143 mm (FOR ROOF NOZZLE,REF. API-650 FIG 5-19, TABLE 5-14 AND FOOTNOTE A OF TABLE 5-14, or API-650 FIG 5-20, TABLE 5-15 AND FOOTNOTE A OF TABLE 5-15) Required Area = t_Basis * D Required Area = 8.9143 * 219.075 Required Area = 1952.9095 mm^2 Available Roof Area = (t_c - t_Basis) * D Available Roof Area = (10.5143 - 8.9143) * 219.075 Available Roof Area = 350.52 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (12.7 - 3.2) + 10.5143] * (12.7 - 3.2) * MIN((124.1056/137) 1) Available Nozzle Neck Area = 688.963 mm^2 A-rpr = (Required Area - Available Roof Area - Available Nozzle Neck Area) A-rpr = 1952.9095 - 350.52 - 688.963 A-rpr = 913.4265 mm^2 Powered by EBPC

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t_rpr = (A_rpr / D) + repad_CA t_rpr = (913.4265 / 219.075) + 3.2 t_rpr = 7.3695 mm Reinforcement Pad is required. Based on Roof Nozzle Size of 8 in Repad Size (OD) Must be 450 mm Nozzle N-15 Reinfor cement Requir ements (Per API-650 and other references below) NOZZLE Description : 6 in SCH 80 TYPE RFWN t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Roof Material) CA = (Corrosion Allowance of Neck) MOUNTED ON ROOF: Elevation = 7.7181 ft ROOF PARAMETERS: t-calc = 10.5143 mm t_cr = 8.9143 mm (Roof t-calc less C.A) t_c = 10.5143 mm t_Basis = 8.9143 mm (FOR ROOF NOZZLE,REF. API-650 FIG 5-19, TABLE 5-14 AND FOOTNOTE A OF TABLE 5-14, or API-650 FIG 5-20, TABLE 5-15 AND FOOTNOTE A OF TABLE 5-15) Required Area = t_Basis * D Required Area = 8.9143 * 168.275 Required Area = 1500.0609 mm^2 Available Roof Area = (t_c - t_Basis) * D Available Roof Area = (10.5143 - 8.9143) * 168.275 Available Roof Area = 269.24 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (10.9728 - 3.2) + 10.5143] * (10.9728 - 3.2) * MIN((124.1056/137) 1) Available Nozzle Neck Area = 515.0558 mm^2 A-rpr = (Required Area - Available Roof Area - Available Nozzle Neck Area) A-rpr = 1500.0609 - 269.24 - 515.0558 A-rpr = 715.7651 mm^2 t_rpr = (A_rpr / D) + repad_CA t_rpr = (715.7651 / 168.275) + 3.2 t_rpr = 7.4535 mm Powered by EBPC

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Reinforcement Pad is required. Based on Roof Nozzle Size of 6 in Repad Size (OD) Must be 375 mm Nozzle N-5 Reinforcement Requirements (Per API-650 and other references below) NOZZLE Description : 8 in SCH 80 TYPE RFWN t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Roof Material) CA = (Corrosion Allowance of Neck) MOUNTED ON ROOF: Elevation = 7.3997 ft ROOF PARAMETERS: t-calc = 10.5143 mm t_cr = 8.9143 mm (Roof t-calc less C.A) t_c = 10.5143 mm t_Basis = 8.9143 mm (FOR ROOF NOZZLE,REF. API-650 FIG 5-19, TABLE 5-14 AND FOOTNOTE A OF TABLE 5-14, or API-650 FIG 5-20, TABLE 5-15 AND FOOTNOTE A OF TABLE 5-15) Required Area = t_Basis * D Required Area = 8.9143 * 219.075 Required Area = 1952.9095 mm^2 Available Roof Area = (t_c - t_Basis) * D Available Roof Area = (10.5143 - 8.9143) * 219.075 Available Roof Area = 350.52 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (12.7 - 3.2) + 10.5143] * (12.7 - 3.2) * MIN((124.1056/137) 1) Available Nozzle Neck Area = 688.963 mm^2 A-rpr = (Required Area - Available Roof Area - Available Nozzle Neck Area) A-rpr = 1952.9095 - 350.52 - 688.963 A-rpr = 913.4265 mm^2 t_rpr = (A_rpr / D) + repad_CA t_rpr = (913.4265 / 219.075) + 3.2 t_rpr = 7.3695 mm Reinforcement Pad is required. Based on Roof Nozzle Size of 8 in Repad Size (OD) Must be 450 mm Powered by EBPC

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Nozzle N-16 Reinfor cement Requir ements (Per API-650 and other references below) NOZZLE Description : 8 in SCH 80 TYPE RFWN t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Roof Material) CA = (Corrosion Allowance of Neck) MOUNTED ON ROOF: Elevation = 7.7182 ft ROOF PARAMETERS: t-calc = 10.5143 mm t_cr = 8.9143 mm (Roof t-calc less C.A) t_c = 10.5143 mm t_Basis = 8.9143 mm (FOR ROOF NOZZLE,REF. API-650 FIG 5-19, TABLE 5-14 AND FOOTNOTE A OF TABLE 5-14, or API-650 FIG 5-20, TABLE 5-15 AND FOOTNOTE A OF TABLE 5-15) Required Area = t_Basis * D Required Area = 8.9143 * 219.075 Required Area = 1952.9095 mm^2 Available Roof Area = (t_c - t_Basis) * D Available Roof Area = (10.5143 - 8.9143) * 219.075 Available Roof Area = 350.52 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (12.7 - 3.2) + 10.5143] * (12.7 - 3.2) * MIN((103.4213/137) 1) Available Nozzle Neck Area = 574.1358 mm^2 A-rpr = (Required Area - Available Roof Area - Available Nozzle Neck Area) A-rpr = 1952.9095 - 350.52 - 574.1358 A-rpr = 1028.2537 mm^2 t_rpr = (A_rpr / D) + repad_CA t_rpr = (1028.2537 / 219.075) + 3.2 t_rpr = 7.8936 mm Reinforcement Pad is required. Based on Roof Nozzle Size of 8 in Repad Size (OD) Must be 450 mm Nozzle N-8 Reinfor cement Requir ements Powered by EBPC

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NOZZLE Description : 2 in SCH STD TYPE RFWN t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Shell Course Material) CA = (Corrosion Allowance of Neck) MOUNTED ON SHELL 4 : Elevation = 6.035 ft COURSE PARAMETERS: t-calc = 5 mm t_cr = 1.8 mm (Course t-calc less C.A) t_c = 3.15 mm (Course t less C.A.) t_Basis = 1.8 mm (SHELL NOZZLE REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7) Required Area = t_Basis * D Required Area = 1.8 * 60.325 Required Area = 108.585 mm^2 Available Shell Area = (t_c - t_Basis) * D Available Shell Area = (3.15 - 1.8) * 60.325 Available Shell Area = 81.4387 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (5.54 - 3.2) + 3.15] * (5.54 - 3.2) * MIN((124.1056/137) 1) Available Nozzle Neck Area = 46.5499 mm^2 A-rpr = (Required Area - Available Shell Area - Available Nozzle Neck Area) A-rpr = 108.585 - 81.4387 - 46.5499 A-rpr = -19.4037 mm^2 Since A-rpr <= 0, t_rpr = 0 No Reinforcement Pad required. Nozzle N-4 Reinfo rcement Requi rements NOZZLE Description : 2 in SCH STD TYPE RFWN t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Shell Course Material) CA = (Corrosion Allowance of Neck) MOUNTED ON SHELL 1 : Elevation = 0.609 ft Powered by EBPC

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COURSE PARAMETERS: t-calc = 6 mm t_cr = 2.8 mm (Course t-calc less C.A) t_c = 4.7 mm (Course t less C.A.) t_Basis = 2.8 mm (SHELL NOZZLE REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7) Required Area = t_Basis * D Required Area = 2.8 * 60.325 Required Area = 168.91 mm^2 Available Shell Area = (t_c - t_Basis) * D Available Shell Area = (4.7 - 2.8) * 60.325 Available Shell Area = 114.6175 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (5.54 - 3.2) + 4.7] * (5.54 - 3.2) * MIN((124.1056/137) 1) Available Nozzle Neck Area = 59.6925 mm^2 A-rpr = (Required Area - Available Shell Area - Available Nozzle Neck Area) A-rpr = 168.91 - 114.6175 - 59.6925 A-rpr = -5.4 mm^2 Since A-rpr <= 0, t_rpr = 0 No Reinforcement Pad required. Nozzle N-7 Reinfo rcement Requi rements NOZZLE Description : 2 in SCH STD TYPE RFSO t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Shell Course Material) CA = (Corrosion Allowance of Neck) MOUNTED ON SHELL 1 : Elevation = 0.175 ft COURSE PARAMETERS: t-calc = 6 mm t_cr = 2.8 mm (Course t-calc less C.A) t_c = 4.7 mm (Course t less C.A.) t_Basis = 2.8 mm (SHELL NOZZLE REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7) Required Area = t_Basis * D Powered by EBPC

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Required Area = 2.8 * 60.325 Required Area = 168.91 mm^2 Available Shell Area = (t_c - t_Basis) * D Available Shell Area = (4.7 - 2.8) * 60.325 Available Shell Area = 114.6175 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (5.54 - 3.2) + 4.7] * (5.54 - 3.2) * MIN((124.1056/137) 1) Available Nozzle Neck Area = 59.6925 mm^2 A-rpr = (Required Area - Available Shell Area - Available Nozzle Neck Area) A-rpr = 168.91 - 114.6175 - 59.6925 A-rpr = -5.4 mm^2 Since A-rpr <= 0, t_rpr = 0 No Reinforcement Pad required. Nozzle N-9 Reinfo rcement Requi rements NOZZLE Description : 6 in SCH 40 TYPE RFWN t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Shell Course Material) CA = (Corrosion Allowance of Neck) MOUNTED ON SHELL 1 : Elevation = 0.355 ft COURSE PARAMETERS: t-calc = 6 mm t_cr = 2.8 mm (Course t-calc less C.A) t_c = 4.7 mm (Course t less C.A.) t_Basis = 2.8 mm (SHELL NOZZLE REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7) Required Area = t_Basis * D Required Area = 2.8 * 168.275 Required Area = 471.17 mm^2 Available Shell Area = (t_c - t_Basis) * D Available Shell Area = (4.7 - 2.8) * 168.275 Available Shell Area = 319.7225 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (10.97 - 3.2) + 4.7] * (10.97 - 3.2) * MIN((103.4213/137) 1) Available Nozzle Neck Area = 292.575 mm^2 Powered by EBPC

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A-rpr = (Required Area - Available Shell Area - Available Nozzle Neck Area) A-rpr = 471.17 - 319.7225 - 292.575 A-rpr = -141.1275 mm^2 Since A-rpr <= 0, t_rpr = 0 No Reinforcement Pad required. Nozzle N-10 Reinfor cement Requir ements NOZZLE Description : 4 in SCH STD TYPE RFWN t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Shell Course Material) CA = (Corrosion Allowance of Neck) MOUNTED ON SHELL 1 : Elevation = 0.609 ft COURSE PARAMETERS: t-calc = 6 mm t_cr = 2.8 mm (Course t-calc less C.A) t_c = 4.7 mm (Course t less C.A.) t_Basis = 2.8 mm (SHELL NOZZLE REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7) Required Area = t_Basis * D Required Area = 2.8 * 114.3 Required Area = 320.04 mm^2 Available Shell Area = (t_c - t_Basis) * D Available Shell Area = (4.7 - 2.8) * 114.3 Available Shell Area = 217.17 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (8.56 - 3.2) + 4.7] * (8.56 - 3.2) * MIN((103.4213/137) 1) Available Nozzle Neck Area = 162.8218 mm^2 A-rpr = (Required Area - Available Shell Area - Available Nozzle Neck Area) A-rpr = 320.04 - 217.17 - 162.8218 A-rpr = -59.9518 mm^2 Since A-rpr <= 0, t_rpr = 0 No Reinforcement Pad required. Nozzle N-1 Reinfor cement Requir ements Powered by EBPC

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NOZZLE Description : 6 in SCH STD TYPE RFWN t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Shell Course Material) CA = (Corrosion Allowance of Neck) MOUNTED ON SHELL 1 : Elevation = 0.306 ft COURSE PARAMETERS: t-calc = 6 mm t_cr = 2.8 mm (Course t-calc less C.A) t_c = 4.7 mm (Course t less C.A.) t_Basis = 2.8 mm (SHELL NOZZLE REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7) Required Area = t_Basis * D Required Area = 2.8 * 168.275 Required Area = 471.17 mm^2 Available Shell Area = (t_c - t_Basis) * D Available Shell Area = (4.7 - 2.8) * 168.275 Available Shell Area = 319.7225 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (10.97 - 3.2) + 4.7] * (10.97 - 3.2) * MIN((124.1056/137) 1) Available Nozzle Neck Area = 351.09 mm^2 A-rpr = (Required Area - Available Shell Area - Available Nozzle Neck Area) A-rpr = 471.17 - 319.7225 - 351.09 A-rpr = -199.6425 mm^2 Since A-rpr <= 0, t_rpr = 0 No Reinforcement Pad required. Nozzle N-11 Reinfor cement Requi rements NOZZLE Description : 4 in SCH STD TYPE RFWN t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Shell Course Material) CA = (Corrosion Allowance of Neck) Powered by EBPC

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MOUNTED ON SHELL 4 : Elevation = 7.1 ft COURSE PARAMETERS: t-calc = 5 mm t_cr = 1.8 mm (Course t-calc less C.A) t_c = 3.15 mm (Course t less C.A.) t_Basis = 1.8 mm (SHELL NOZZLE REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7) Required Area = t_Basis * D Required Area = 1.8 * 114.3 Required Area = 205.74 mm^2 Available Shell Area = (t_c - t_Basis) * D Available Shell Area = (3.15 - 1.8) * 114.3 Available Shell Area = 154.305 mm^2 Available Nozzle Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1) Available Nozzle Neck Area = [4 * (8.56 - 3.2) + 3.15] * (8.56 - 3.2) * MIN((103.4213/137) 1) Available Nozzle Neck Area = 137.7349 mm^2 A-rpr = (Required Area - Available Shell Area - Available Nozzle Neck Area) A-rpr = 205.74 - 154.305 - 137.7349 A-rpr = -86.2999 mm^2 Since A-rpr <= 0, t_rpr = 0 No Reinforcement Pad required. Manway N-12 Reinforcement Requirements MANWAY Description : 24 in SCH -t_rpr = (Re Pad Required Thickness) t_n = (Thickness of Neck) Sd_n = (Stress of Neck Material) Sd_s = (Stress of Shell Course Material) CA = (Corrosion Allowance of Neck) MOUNTED ON SHELL 1 : Elevation = 0.75 ft COURSE PARAMETERS: t-calc = 6 mm t_cr = 2.8 mm (Course t-calc less C.A) t_c = 4.7 mm (Course t less C.A.) t_Basis = 2.8 mm (SHELL MANWAY REF. API-650 TABLE 5-6, TABLE 3-6 AND FOOTNOTE A OF TABLE 5-7) Powered by EBPC

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Required Area = t_Basis * D Required Area = 2.8 * 635 Required Area = 1778 mm^2 Available Shell Area = (t_c - t_Basis) * D Available Shell Area = (4.7 - 2.8) * 635 Available Shell Area = 1206.5 mm^2 Available Manway Neck Area = [4 * (t_n - CA) + t_c] * (t_n - CA) * MIN((Sd_n/Sd_s) 1) Available Manway Neck Area = [4 * (12.7 - 3.2) + 4.7] * (12.7 - 3.2) * MIN((137/137) 1) Available Manway Neck Area = 539.6 mm^2 A-rpr = (Required Area - Available Shell Area - Available Manway Neck Area) A-rpr = 1778 - 1206.5 - 539.6 A-rpr = 31.9 mm^2 t_rpr = (A_rpr / D) + repad_CA t_rpr = (31.9 / 635) + 3.2 t_rpr = 3.2502 mm Reinforcement Pad is required. Based on Shell Manway Size of 24 in Repad Size (L x W) Must be 1257.3 x 1524 mm Manway N-13 Reinforcement Requirements (Per API-650 Section 5.8.4 and other references below) MANWAY Description : 24 in SCH -- TYPE t_rpr = (Re Pad Required Thickness) MOUNTED ON ROOF: Elevation = 7.6347 ft ROOF PARAMETERS: t-calc = 10.5143 mm t_cr = 8.9143 mm (Roof t-calc less C.A) t_c = 10.5143 mm t_Basis = 8.9143 mm (FOR ROOF MANWAY,REF. API-650 FIG 5-16, TABLE 5-13) Required Area = t_Basis * D Required Area = 8.9143 * 623.6 Required Area = 5558.9837 mm^2 Available Roof Area = (t_c - t_Basis) * D Available Roof Area = (10.5143 - 8.9143) * 623.6 Available Roof Area = 997.76 mm^2 Available Manway Neck Area = [4 * (t_n - CA) + t_c] * (t_n - ca) * MIN((Sd_n/Sd_s) 1) Available Manway Neck Area = [4 * (7 - 3.2) + 10.5143] * (7 - 3.2) * MIN((137/137) 1) Powered by EBPC

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Available Manway Neck Area = 172.1707 mm^2 A-rpr = (Required Area - Available Roof Area - Available Manway Neck Area) A-rpr = 5558.9837 - 997.76 - 172.1707 A-rpr = 4389.053 mm^2 t_rpr = (A_rpr / D) + repad_CA t_rpr = (4389.053 / 623.6) + 3.2 t_rpr = 10.2383 mm Reinforcement Pad is required. Based on Roof Manway Size of 24 in Repad Size (OD) Must be 1150 mm 7.22 CAPACITIES AND WEIGHTS Maximum Capacity (to Max Liq Level) : 272 M^3 Capacity to Top of Shell (to Tank Height) : 331 M^3 Working Capacity (to Normal Working Level) : 248 M^3 Net working Capacity (Working Capacity - Min Capacity) : 223 M^3 Minimum Capacity (to Min Liq Level) : 25 M^3 Component New Conditi on (N) New Conditi on (Kg) Corroded (N) Corrod ed (Kg) SHELL 90,512 9,230 47,547 4,849 ROOF 39,898 4,069 34,147 3,482 RAFTERS 0 0 0 0 GIRDERS 0 0 0 0 FRAMING 0 0 0 0 COLUMNS 0 0 0 0 BOTTOM 34,343 3,502 22,775 2,323 STAIRWAYS 5,835 595 5,835 595 STIFFENERS 1,376 141 1,375 141 WIND GIRDERS 0 0 0 0 ANCHOR CHAIRS 3,923 400 3,923 400 INSULATION 0 0 0 0 TOTAL 175,887 17,937 115,602 11,790 Weight of Tank, Empty : 175,887 N Weight of Tank, Full of Product (SG = 0.789) : 2,305,371.6275 N Weight of Tank, Full of Water : 2,874,855.24 N Net Working Weight, Full of Product : 2,090,483.6392 N Net Working Weight Full of Water : 2,602,498.7101 N Foundation Area Req'd : 47.0081 m^2 Powered by EBPC

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Foundation Loading, Empty : 3,741.63 N/m^2 Foundation Loading, Full of Product : 45,300.3552 N/m^2 Foundation Loading, Full of Water : 57,414.9343 N/m^2 SURFACE AREAS Roof : 46.7401 m^2 Shell : 175.1181 m^2 Bottom : 47.0081 m^2 Wind Moment : 381,923.2178 N-m Seismic Moment : 322,923.5235 N-m MISCELLANEOUS ATTACHED ROOF ITEMS MISCELLANEOUS ATTACHED SHELL ITEMS 7.23 MAWP & MAWV SUMMARY MAWP = Maximum calculated internal pressure MAWV = Maximum calculated external pressure 7.24 MAXIMUM CALCULATED INTERNAL PRESSURE MAWP = 18 kPa or 1,835.658 mmh2o (per API-650 App. F.1.3 & F.7) MAWP = 275.3005 kPa or 28,075 mmh2o (due to shell) MAWP = 8.5443 kPa or 871.3563 mmh2o (due to roof) TANK MAWP = 8.5443 kPa or 871.3596 mmh2o

7.25 MAXIMUM CALCULATED EXTERNAL PRESSURE MAWV = -6.9 kPa or -703.6689 mmh2o (per API-650 V.1) MAWV = N/A (due to shell) (API-650 App.V not applicable) MAWV = -0.6361 kPa or -64.8714 mmh2o (due to roof) TANK MAWV = -0.6361 kPa or -64.8714 mmh2o

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8.0

CONCLUSIONES Los espesores indicados en la Hoja de Datos DCPA-SO-SCAR-SAR-GOMT-E-15-14, fueron corroborados, obteniéndose los valores mostrados en el numeral 7.2, como resultado de los pesos muertos y al análisis sísmico del lugar de acuerdo a los datos y de la estratigrafía de la Mecánica de Suelos INFORME EGG1508660. El tanque deberá ser anclado de acuerdo al diseño mostrado en los numerales 7.16 y 7.17. El diseño de la membrana interna, es de acuerdo a lo propuesto a lo mostrado en las pantallas del numeral 7.19.

9.0

NORMATIVIDAD APLICABLE Norma

NRF-113-PEMEX-2007

Diseño de Tanques Atmosféricos.

Estándar

“Welded Tanks for Oil Storage”

Código

API-650 Ed. 2013 ASME SECC II PART. D 2013. ASME SECC V 2013.

Manual

MDOC-CFE-2008

Manual

MDOC-CFE-2008

Manual

AISC

Manual

IMCA

Código

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Properties (Metric) Materials. Nondestructive Examination. Manual de Diseño DE Obras Civiles. Diseño por Sismo. CFE 2008. Manual de Diseño DE Obras Civiles. Diseño por Viento. CFE 2008. American Institute of Steel Construction 3rd. Edition. Manual de Construcción en Acero. DEP. IMCA 4ta. Edición.

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10.0

GEOMETRÍA DEL DISEÑO

Figura 8.

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Vista elevación .

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Figura 9.

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Vista plant a.

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