Turbofan Turbofan Engine Seminar Report 2015 - 2016
A seminar report report on
TURBOFAN ENGINE Seminar Report submitted in partial fulfilment of the requirements requirements For the award of
Diploma In Mechanical Engineering Of
Department of Technical Education Government of Kerala By
ABIN.B Under the guidance of
Lt. SANIL KMA!.S
MA!"# $%&' DE(A!TMENT )* ME"#ANI"AL ENGINEE!ING
Dept of Mechanical engineering SNPT! "otti#am
1
Turbofan Turbofan Engine Seminar Report 2015 - 2016
Kotti+am ,(.)- ,(.)- Kollam '/&01&
DE(A!TMENT )* ME"#ANI"AL ENGINEE!ING
Kottiyam (P.O), Kollam 691571
"E!TI*I"ATE This This is to cert certiify that hat the sem semin ina ar repo report rt enti ntitle tled TURBOFAN ENGINE being being submitted by ABIN.B ( 13020070 )
for
the
award
of
the
Diploma
in
Mechanical
Engi Engine neer erin ing g of Depa Depart rtme ment nt of Techn echnic ical al Educa ducati tion on Government of Kerala is a bonade account of the work carr carriied out by him in thi this depa depart rtm ment ent duri durin ng the the academic year 2!"#2!$ under our supervision $
Dept of Mechanical engineering SNPT! "otti#am
2
Turbofan Turbofan Engine Seminar Report 2015 - 2016
Kotti+am ,(.)- ,(.)- Kollam '/&01&
DE(A!TMENT )* ME"#ANI"AL ENGINEE!ING
Kottiyam (P.O), Kollam 691571
"E!TI*I"ATE This This is to cert certiify that hat the sem semin ina ar repo report rt enti ntitle tled TURBOFAN ENGINE being being submitted by ABIN.B ( 13020070 )
for
the
award
of
the
Diploma
in
Mechanical
Engi Engine neer erin ing g of Depa Depart rtme ment nt of Techn echnic ical al Educa ducati tion on Government of Kerala is a bonade account of the work carr carriied out by him in thi this depa depart rtm ment ent duri durin ng the the academic year 2!"#2!$ under our supervision $
Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Turbofan Engine Seminar Report 2015 - 2016
Lt. SANIL KMA!.S Lecturer Mechanical Dept. (Seminar guide)
Er. 2IN)D KMA! 2.M #ead of the Dept Mechanical SN(T" Kottt+am
E3ternal e3aminer 44444444. 44444444.
ACKNOWLEDGEMENT ACKNOWLEDGEMENT Firs Firstt of all all I um um!ly !ly rem remem!e em!err te te gra" gra"ee and and !les !lessi sing ngss tat at The Almight+ God !esto#ed on me, #itout #i" my attem$t #ould not a%e
!een a su""ess
&is seminar #ould not a%e !een $ossi!le #itout te sin"ere assistan"e of a num!er of eminent $eo$le. I ta'e tis o$$ortunity to a"'no#ledge my eartfelt gratitude to my res$e"ted $rin"i$al Mr. A5ith 2 for $ro%iding all te ne"essary fa"ilities in tis institution.
I e$ress $rofound and sin"ere tan' to Mr.2inod Kumar 2.M ead of te *e$artment *e$artment of +e"ani"al +e"ani"al ngineering ngineering for gi%ing gi%ing me te o$$ortunity o$$ortunity to underta'e tis seminar
-et I #ould li'e to tan' my seminar "oordinators Mr.D.Monilal le"turer in *e$artment of +e"ani"al ngineering for is %alua!le ad%i"es and suggestions #i" el$ed me in te su""ess of tis seminar #or'.
Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Turbofan Engine Seminar Report 2015 - 2016
I #ould li'e to tan' my seminar guide Lt. Sanil Kumar.S le"turer in *e$artment of +e"ani"al ngineering for is %alua!le ad%i"e and guidan"e
I #oul #ould d also also li'e li'e to tan tan' ' all all fa"u fa"ult lty y mem!e em!ers rs of *e$a *e$art rtme ment nt of +e"ani"al ngineering for teir el$ and "oo$eration.
I o#e my in"al"ula!le in"al"ula!le de!t to my $arents, $arents, friends and all oters for teir teir insigtful su$$ort and suggestions and "oo$eration.
ABSTRACT ABSTRACT To To ma&e an aircraft mo'e mo'e for(ar) (e nee) a pu*hing force calle) thru*t (hich i* create) b# ma&ing air accelerate) bet(een the front an) rear of the engine (ith the help of a giant fan! compre**or*! turbine*! etc$$$ Di+erent t#pe* of engi engine ne e,i*t ,i*t but but the mo*t mo*t eci ecien entt amon among g them them i* the the turbofan engine becau*e of their lo( fuel con*umption an) high thru*t$ Engine* u*e) in the earlier part* of 20th cent centur ur# # ha) ha) )e.c )e.cie ienc ncie ie* * in *pit *pite e of thei theirr a)'a a)'ant ntag age* e*$$ The The engine* u*e) in tho*e time* (ere Turboprop engine*$ The*e engi engine ne* * coul coul) ) pro) pro)uc uce e onl# nl# 10/ of thei theirr thru* hru*tt from from the the e,hau*t et$ The# coul) not attain high *pee)$ Re*earche* (ere con)ucte) further! (hich le) to the )e'elopment* of Turbofan engine*$ The (or) turbofan i* a combination of turbine an) fan$ The turbo portion refer* to a ga* turbine (hich ta&e* mechanical energ# from the combu*tion an) the fan that u*e* the mechanical energ# from
Dept of Mechanical engineering SNPT! "otti#am
Turbofan Engine Seminar Report 2015 - 2016
the ga* turbine to accelerate the air rear(ar)* to the core of engine$ Turbofan engine* combine) the hot air et (ith b#pa**e) air from a fan$ The air pa**ing through the giant fan *plit up into t(o maor portion mo'e* through the b#pa** port (hile the remain enter* the compre**or* that compre**e* the air (hich increa*e* it* pre**ure an) )eli'er* it to the combu*tion chamber (here it burn* (ith the fuel that further increa*e* the pre**ure$ The pre**uri*e) air then enter* the turbine (hich help* in the (or&ing of compre**or an) the giant fan$ The air lea'ing the turbine combine* (ith the air from b#pa** port (hich pro)uce* the thru*t for the mo'ing of aircraft$ 3 turbofan engine i* a 4uieter engine (ith greater boo*t at lo( *pee)*! ma&ing it a popular choice for commercial airplane*$ Due to generation of more thru*t for nearl# the *ame amount of fuel! it i* highl# fuel-ecient$ ith a better all-aroun) performance at a lo(er rate of fuel con*umption turbofan engine* are no( (i)el# u*e)$
CONTENTS
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Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
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Turbofan Engine Seminar Report 2015 - 2016
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LIST OF FIGURES ;ig N8 Page No
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Schematic )iagram of turbofan engine
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Thru*t of a turbofan engine
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Part* of a turbofan engine
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or&ing of turbofan engine ?$1$1
3ir entering to interior core of engine
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3ir b#pa**ing the engine core
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%$;uel inecting from the inector
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Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
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;uel an) air mi,ture ignite*
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E,hau*t ga* turn the turbine
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Thru*t of the air mo'e* the plane for(ar)
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9o( b#pa** turbofan engine
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igh b#pa** turbofan engine
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Single *pool turbofan engine
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Doublet(o *pool turbofan engine
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Three *pool turbofan engine
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Roll*-Ro#ce Ta# turbofan engine
LIST OF ABBREVIATIONS LPC : LOW PRESSURE COMPRESSOR HPC : HIGH PRESSURE COMPRESSOR
Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
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Dept of Mechanical engineering SNPT! "otti#am
LPS
:
LOW PRESSURE SHAFT
HPS
:
HIGH PRESSURE SHAFT
LPT
:
LOW PRESSURE TURBINE
HPT
:
HIGH PRESSURE TURBINE
INTRODUCTION
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Turbofan Engine Seminar Report 2015 - 2016
Bet Propul*ion i* the thru*t imparting for(ar) motion to an obect! a* a reaction to the rear(ar) e,pul*ion of a high-'elocit# li4ui) or ga*eou* *tream$ 3 *imple e,ample of et propul*ion i* the motion of an inate) balloon (hen the air i* *u))enl# )i*charge)$ hile the opening i* hel) clo*e)! the air pre**ure (ithin the balloon i* e4ual in all )irection* (hen the *tem i* relea*e)! the internal pre**ure i* le** at the open en) than at the oppo*ite en)! cau*ing the balloon to )art for(ar)$ Not the pre**ure of the e*caping air pu*hing again*t the out*i)e atmo*phere but the )i+erence bet(een high an) lo( pre**ure* in*i)e the balloon propel* it$ 3n actual et engine )oe* not operate 4uite a* *impl# a* a balloon! although the ba*ic principle i* the *ame$ More important than pre**ure imbalance i* the acceleration )ue to high 'elocitie* of the et lea'ing the engine$ Thi* i* achie'e) b# force* in the engine that enable the ga* to o( bac&(ar) forming the et$ Ne(tonF* *econ) la( *ho(* that the*e force* are proportional to the rate at (hich the momentum of the ga* i* increa*e)$ ;or a et engine! thi* i* relate) to the rate of ma** o( multiplie) b# the rear(ar)-lea'ing et 'elocit#$ Ne(tonF* thir) la( (hich *tate* that GE'er# force mu*t ha'e an e4ual an) oppo*ite reactionH! *ho(* that the rear(ar) force i* balance) b# a for(ar) reaction! &no(n a* thru*t$ Thi* thru*ting action i* *imilar to the recoil of a gun! (hich increa*e* a* both the ma** of the proectile an) it* muIIle 'elocit# are increa*e)$ igh-thru*t engine*! therefore! re4uire both large rate* of ma** o( an) high et-e,it 'elocitie*! (hich can onl# be achie'e) b# increa*ing internal engine pre**ure* an) b# increa*ing the 'olume of the ga* b# mean* of combu*tion$ Bet-propul*ion )e'ice* are u*e) primaril# in high-*pee)! high-altitu)e aircraft! in mi**ile*! an) in *pacecraft$ The *ource of po(er i* a high-energ# fuel that i* burne) at
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Turbofan Engine Seminar Report 2015 - 2016
inten*e pre**ure* to pro)uce the large ga* 'olume nee)e) for high et-e,it 'elocitie*$ The o,i)iIer re4uire) for the combu*tion ma# be the o,#gen in the air that i* )ra(n into the engine an) compre**e)! or the o,i)iIer ma# be carrie) in the 'ehicle! *o that the engine i* in)epen)ent of a *urroun)ing atmo*phere$ Engine* that )epen) on the atmo*phere for o,#gen inclu)e turboet*! turbofan*! turboprop*! ramet*! an) pul*e et*$ Non atmo*pheric engine* are u*uall# calle) roc&et engine*$
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Turbofan Engine Seminar Report 2015 - 2016
2.
HISTORY
Bet po(er a* a form of propul*ion ha* been &no(n for hun)re)* of #ear*! although it* u*e for propelling 'ehicle* that carr# loa)* i* comparati'el# recent$ The earlie*t &no(n reaction engine (a* an e,perimental! *teamoperate) )e'ice )e'elope) about the .r*t centur# =$$ b# the 7ree& mathematician an) *cienti*t ero of 3le,an)ria &no(n a* the 3eolipile! eroF* )e'ice )i) no practical (or&! although it )emon*trate) that a et of *team e*caping to the rear )ri'e* it* generator for(ar)$ The aeolipile con*i*te) of a *pherical chamber into (hich *team (a* fe) through hollo( *upport*$ The *team (a* allo(e) to e*cape from t(o bent tube* on oppo*ite *i)e* of the *phere! an) the reaction to the force of the e*caping *team cau*e) the *phere to rotate$ The )e'elopment of the *team turbine i* cre)ite) to the :talian engineer 7io'anni =ranca! (ho )irecte) a *team et again*t a turbine (heel! (hich in turn po(ere) a *tamp mill in 162C$ The .r*t recor)e) patent for a ga* turbine (a* obtaine) in 1?C1 b# the =riti*h in'entor Bohn =arber$ :n 1C10! *e'en #ear* after the .r*t ight* b# the 3merican in'entor* 8r'ille an) ilbur right! the ;rench *cienti*t enri Marie oan)a )e*igne) an) built a etpropelle) biplane! (hich too& o+ an) e( un)er it* o(n po(er (ith oan)a a* pilot$ oan)a u*e) an engine that he terme) a Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
reaction motor! but! )i*courage) b# the lac& of public acceptance of hi* aircraft! he aban)one) hi* e,periment*$ During the ne,t 20 #ear* the ga* turbine (a* )e'elope) further in both the -1! or buII bomb! .r*t o(n in 1C2! (a* po(ere) b# pul*e et$ 3l*o in the mi)-1C0* the .r*t commercial airline ight* u*ing turboprop engine* occurre)$ :n 1C? the =ell -1 e,perimental airplane!
Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
po(ere) b# a four-chambere) li4ui)-roc&et engine an) carrie) to the *trato*phere in the bell# of a bomber for launching! (a* the .r*t pilot-operate) craft to brea& the *oun) barrier$ Sub*e4uentl# the Dougla* S&#roc&et e,perimental airplane! po(ere) b# a et engine in a))ition to a li4ui)-roc&et engine! bro&e the *oun) barrier at lo( altitu)e after ta&ing o+ un)er it* o(n po(er$ The .r*t commercial et airplane! the =riti*h omet! (a* o(n in 1C52! but thi* *er'ice (a* *toppe) after t(o *eriou* acci)ent* in 1C5$ :n the <$S$! the =oeing ?0? et (a* the .r*t et airplane to be te*te) commerciall#! in 1C5$ ommercial ight* began in 1C5@$ :mpro'e) material* an) intro)uction of t(in compre**or* *uch u* in =ri*tol 8l#mpu* an) the later Pratt hitne# BT% engine! increa*e) the thermo)#namic ecienc# of engine*$ =ut the# al*o le) to a poor propul*i'e ecienc# b# re)ucing the e,hau*t 'elocit# to a 'al'e clo*er to that of the aircraft$ The Roll* Ro#*e con'e# the (orl)O* .r*t pro)uction turbofan! ha) a b#pa** ratio of 0$% *imilar to the mo)ern engine*$ i'ilian turbofan* of the 1C60* *uch u* Pratt hitne# an) the Roll* Ro#*e Spe# ha) b#pa** ratio clo*er to 1$0 but (here not *imilar to militar# e4ui'alent*$ The unu*ual electric ;?00 turbofan engine (a* )e'elope) (ith a 2$0 b#pa** ratio$ Thi* (a* )eri'e) from the general electric turboet to po(er the larger mo)el aircraft*$ The ;?00 (a* the (orl)O* .r*t *malle*t turbofan engine to be certi.e) b# the ;e)eral 3'iation 3)mini*tration$ There are no( o'er a four hun)re) ;?00 aircraft* in operation aroun) the (orl) (ith an e,perience ba*e of o'er 10 million *er'ice hour*$ The ;?00 (a* al*o u*e) to train moon-boun) a*rtronent* in proect 3ppolo a* the po(er
Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
plant for the lunar lan)ing re*earch 'ehicle$ The :@0-5% (a* *imilar but larger in )e*ign$ The continuou* )e'elopment of et propul*ion for air po(er ha* re*ulte) in *uch a)'ance* a* pilote) aircraft capable of attaining *pee)* *e'eral time* greater than the *pee) of *oun)! an) intercontinental balli*tic mi**ile* an) arti.cial *atellite* launche) b# po(erful roc&et*
3.
THEORY
What is !"#$si"%&
Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
The (or) i* )eri'e) from t(o 9atin (or)* pro meaning before or for(ar)* an) pellere mean* to )ri'e$ Propul*ion mean* to pu*h for(ar) or )ri'e an obect for(ar)$ 3 propul*ion *#*tem i* a machine that pro)uce* thru*t to pu*h an obect for(ar)$ 8n airplane*! thru*t i* u*uall# generate) through *ome application of Ne(tonF* thir) la( of action an) reaction$ The engine accelerate* a ga* or (or&ing ui)! an) the reaction to thi* acceleration pro)uce* a force on the engine$ 3 general )eri'ation of the thru*t e4uation *ho(* that the amount of thru*t generate) )epen)* on the ma** o( through the engine an) the e,it 'elocit# of the ga*$ Di+erent propul*ion *#*tem* generate thru*t in *lightl# )i+erent (a#*$
What is a T#!'"(a% E%)i%*& 3 turbofan engine i* the mo*t mo)ern 'ariation of the ba*ic ga* turbine engine$ 3* (ith other ga* turbine*! there i* a core engine$ :n the turbofan engine! a fan in the front an) an a))itional turbine at the rear *urroun)* the core engine$ The fan an) fan turbine are compo*e) of man# bla)e*! li&e the core compre**or an) core turbine! an) are connecte) to an a))itional *haft$ 3ll of thi* a))itional turbo machiner# i* coloure) green on the *chematic )iagram a* *ho(n in the .gure belo(-
;ig %$1 Schematic )iagram of turbofan engine
Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
3* (ith the core compre**or an) turbine! *ome of the fan bla)e* turn (ith the *haft an) *ome bla)e* remain *tationar#$ The fan *haft pa**e* through the core *haft for mechanical rea*on*$ Thi* t#pe of arrangement i* calle) a t(o-*pool engine Kone Q*poolQ for the fan! one Q*poolQ for the core$L Some a)'ance) engine* ha'e a))itional *pool* for *ection* of the compre**or! (hich pro'i)e* for e'en higher compre**or ecienc#$
Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
%&
+*t E%)i%* Th!#st
The force pro)uce) b# a et engine i* e,pre**e) in term* of &ilogram* of thru*t$ Thi* i* a mea*ure of the ma** or (eight of air mo'e) b# an engine time* the acceleration of the air a* it goe* through the engine$ Technicall#! if the aircraft (ere to *tan) *till an) the pre**ure at the e,it plane of the et engine (a* the *ame a* the atmo*pheric pre**ure! the formula for the et engine thru*t (oul) be
eight of air in &ilogram* per *econ) 'elocit# Thru*t C$@1 Knormal acceleration )ue to gra'it#! in meter per *econ) 2L :magine an aircraft *tan)ing *till! capable of han)ling C?$522 &ilogram* of air per *econ)$ 3**ume the 'elocit# of the e,hau*t ga*e* to be 1!500 feet per *econ)$ The thru*t (oul) then be C?$522 &g of air per *econ) 5?$2 m * Thru*t C$@1 m *U2
Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
C$C1 5?$2
Thru*t 55$025 &g$
:f the pre**ure at the e,it plane i* not the *ame a* the atmo*pheric pre**ure an) the aircraft (ere not *tan)ing *till! the formula (oul) be *ome(hat )i+erent$ :t i* not 'er# practical to tr# to compare et engine output in term* of hor*epo(er$ 3* a rule of thumb! ho(e'er! it ma# be note) that that at %?5 mile* per hour KmphL! one poun) of thru*t e4ual* one hor*epo(er at ?50 mph one poun) of thru*t e4ual* t(o hor*epo(er$
Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
,.
WORKING -RINCI-LE
The *cienti.c principle on (hich the et engine operate* (a* .r*t *tarte) in *cienti.c term* b# Sir :*aac Ne(ton in 16@?$ Turbofan engine* (or&* un)er the Ne(tonO* Secon) an) Thir) la($ Thir) la( *tate* that G;or e'er# action there i* an e4ual an) oppo*ite reactionH$ Thi* i* the ba*ic principle of all et engine*$ So b# the thru*t pro)uce) b# the engine the plane mo'e* for(ar)$ Secon) la( *tate* that G3cceleration i* pro)uce) (hen a force act* on a ma** Kof the obect being accelerate)L the greater the amount of force nee)e) Kto accelerate the obectL$ ; ma
Th!#st "( a T#!'"(a% *%)i%* The engine inlet capture* the incoming air$ Some of the incoming air pa**e* through the fan an) continue* on into the core compre**or an) then the burner!
Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
(here it i* mi,e) (ith fuel an) combu*tion occur*$ The hot e,hau*t pa**e* through the core an) fan turbine* an) then out the noIIle! a* in a ba*ic turboet$ Thi* airo( i* calle) the core airo( an) i* )enote) b# m$ The re*t of the incoming air! coloure) blue on the .gure! pa**e* through the fan an) b#pa**e*! or goe* aroun) the engine! u*t li&e the air through a propeller$ The air that goe* through the fan ha* a 'elocit# that i* *lightl# increa*e) from free *tream$ Thi* airo( i* calle) the fan o(! or b#pa** o(! an) i* )enote) b# m$ The ratio of m to m i* calle) the b#pa** ratio$ So a turbofan get* *ome of it* thru*t from the core an) *ome of it* thru*t from the fan$ The ratio of the air that goe* aroun) the engine to the air that goe* through the core i* calle) the b#pa** ratio$ The total ma** o( rate through the inlet i* the *um of the core an) fan o(* mmVm 3 turbofan get* *ome of it* thru*t from the core an) *ome of it* thru*t from the fan$ :f (e )enote the e,it of the core a* *tation QeQ! the e,it of the fan a* *tation QfQ! an) the free *tream a* *tation Q0Q! (e can u*e the ba*ic thru*t e4uation for each *tream to obtain the total thru*t ; m - m >0 V Km >L e - m >0
Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
;ig 5$1 Thru*t of a turbofan engine
e can combine the term* multipl#ing >0 an) u*e the )e.nition of the b#pa** ratio bpr to obtain the .nal thru*t e4uation ; Km >L e V bpr m > f - Km >L0
=ecau*e the fuel o( rate for the core i* change) onl# a *mall amount b# the a))ition of the fan! a turbofan generate* more thru*t for nearl# the *ame amount of fuel u*e) b# the core$ Thi* mean* that a turbofan i* 'er# fuel ecient$ :n fact! high b#pa** ratio turbofan* are nearl# a* fuel ecient a* turboprop*$ =ecau*e the fan i* enclo*e) b# the inlet an) i* compo*e) of man# bla)e*! it can operate ecientl# at higher *pee)* than a *imple propeller$ That i* (h# turbofan* are foun) on high *pee) tran*port* an) propeller* are u*e) on lo( *pee) tran*port*$ 9o( b#pa** ratio turbofan* are *till more fuel ecient than ba*ic turboet*$ Man# mo)ern .ghter plane* actuall# u*e lo(
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Turbofan Engine Seminar Report 2015 - 2016
b#pa** ratio turbofan* e4uippe) (ith afterburner*$ The# can then crui*e ecientl# but *till ha'e high thru*t (hen )og .ghting$ E'en though the .ghter plane can # much fa*ter than the *pee) of *oun)! the air going into the engine mu*t tra'el le** than the *pee) of *oun) for high ecienc#$ Therefore! the airplane inlet *lo(* the air )o(n from *uper*onic *pee)*$
Dept of Mechanical engineering SNPT! "otti#am
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Turbofan Engine Seminar Report 2015 - 2016
.
-ARTS OF A TURBOFAN ENGINE
The )i+erent part* of a Turbofan engine are a* *ho(n in the .gure belo(-
6$1 Part* of a turbofan engine
Fan - The fan i* the .r*t component in a turbofan$ The fan pull*
air into the engine$ The large *pinning fan *uc&* in large 4uantitie* of air$ :t then! *pee)* the air up an) *plit* it into t(o part*$ 8ne part continue* through the QcoreQ or centre of the engine! (here it i* acte) upon b# the other engine component*$ The *econ) part Qb#pa**e*Q the core of the engine! in*tea) tra'elling through a )uct that *urroun)* the core to the bac& of the engine (here it pro)uce* much of the force that propel* the airplane for(ar)$111
Compressor - The compre**or i* the .r*t component in the
engine core$ The compre**or *4ueeIe* the air that enter* it into *maller area*! re*ulting in an increa*e in the air pre**ure$ Thi*
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re*ult* in an increa*e in the energ# potential of the air$ The *4ua*he) air i* force) into the combu*tion chamber$
Combusor - :n the combu*tor the air i* mi,e) (ith fuel an)
then ignite)$ Thi* proce** re*ult* in high temperature an) high energ# airo($ The fuel burn* (ith the o,#gen in the compre**e) air! pro)ucing hot e,pan)ing ga*e*$
Turb!ne - The high energ# airo( coming out of the combu*tor
goe* into the turbine! cau*ing the turbine bla)e* to rotate$ Thi* rotation e,tract* *ome energ# from the high-energ# o( that i* u*e) to )ri'e the fan an) the compre**or$ The ga*e* pro)uce) in the combu*tion chamber mo'e through the turbine an) *pin it* bla)e*$ The ta*& of a turbine i* to con'ert ga* energ# into mechanical (or& to )ri'e the compre**or$
No""#e - The noIIle i* the e,hau*t )uct of the engine$ The
energ# )eplete) airo( that pa**e) the turbine! in a))ition to the col)er air that b#pa**e) the engine core! pro)uce* a force
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(hen e,iting the noIIle that act* to propel the engine! an) therefore the airplane! for(ar)$ The combination of the hot air an) the col) air are e,pelle) an) pro)uce an e,hau*t (hich cau*e* a for(ar) thru*t$ The noIIle ma# be prece)e) b# a mi,er! (hich combine* the high temperature air coming from the engine core (ith the lo(er temperature air that (a* b#pa**e) in the fan$ Thi* re*ult in a 4uieter engine than if the mi,er (a* not pre*ent$
A$erburner - :n a))ition to the ba*ic component* of a ga*
turbine engine! one other proce** i* occa*ionall# emplo#e) to increa*e the thru*t of a gi'en engine$ 3fterburning Kor reheatL i* a metho) of augmenting the ba*ic thru*t of an engine to impro'e the aircraft ta&eo+! climb an) Kfor militar# aircraftL combat performance$ 3fterburning con*i*t* of the intro)uction an) burning of ra( fuel bet(een the engine turbine an) the et pipe propelling noIIle! utiliIing the unburne) o,#gen in the e,hau*t ga* to *upport combu*tion$ The increa*e in the temperature of the e,hau*t ga* increa*e* the 'elocit# of the et lea'ing the propelling noIIle an) therefore increa*e* the engine thru*t$ Thi* increa*e) thru*t coul) be obtaine) b# the u*e of a larger engine! but thi* (oul) increa*e the (eight an) o'erall fuel con*umption$ :n other (or)* 3fterburner i* a )e'ice for increa*ing the thru*t Kfor(ar)-)irecte) forceL of a ga* turbine KetL airplane engine$
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/.
WORKING OF TURBOFAN ENGINE
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;ig ?$1 or&ing of turbofan engine
The engine initiall# *tart* a* follo(* through the opening of blee) air 'al'e*! blee) air i* *ent to an air turbine *tarter$ Thi* )e'i*e t#picall# u*e the high pre**ure blee) air to *pin an) engage a centrifugal clutch connecte) to the engine acce**or# )ri'e$ Thi* in turn cau*e* the high pre**ure *haft (ithin the engine to rotate$ ith the high pre**ure *haft! high pre**ure compre**or an) turbine are *pinning$ Thi* begin* to force the air through the engine from front to bac&$ ith the acce**or# *haft an) high pre**ure *haft *pinning! acce**orie* *houl) al*o *tart (or&ing$ ith the increa*e) high pre**ure *haft rotation ignition (ill be turne) on$ The*e igniter* are locate) in the hot *ection of the engine an) pro)uce *mall *par&*$ There *houl) be increa*e in *haft rotation an) fuel i* intro)uce)$ No( the .re burning in the hot *ection *upplie) b# air from the compre**or i* thru*t acro** high pre**ure an) lo( pre**ure *haft*$ 3* the *pee) of high pre**ure *haft increa*e*! the air turbine *tarter (ill clo*e an) the *tarter )i*engage*$ Then the engine (ill *ettle into a *table i)le thru*t *etting con)ition$ Thi* i* ho( turbofan engine initiall# *tart*$ The .r*t component of the engine i* a huge nine foot titanium fan (hich rotate* at 2@00rpm at the
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time of ta&eo+$ The giant titanium fan *uc&* in enough air to 'acuum out the air in le** than half a *econ)$ 3* the air ri*e* through the ma**i'e fan an) i* *eparate) into t(o *tream*$ Some of the air enter* the interior core of engine (hile maorit# of the air b#pa**e* the engine core an) i* force) through a narro(ing *pace ta&ing up *pee) along the (a#$ The ratio of air b#pa**e* the core to the air pa**ing through the core i* calle) b#pa** ratio$ =ecau*e of it* huge bo)# the b#pa** air onl# nee)* to accelerate of *mall amount in or)er to )e'elop enormou* amount of thru*t$
;ig ?$1$1 3ir entering to interior core of engine
;ig ?$1$2 3ir b#pa**ing the engine core
The *mall amount of air enter* the core .r*t enter* the core .r*tl# reache* the lo( pre**ure compre**or (hich initiall# compre**e* the air forcing it* pre**ure an) temperature to ri*e$ Then it enter* the high pre**ure compre**or (hich rotate* fa*ter an) i* re*pon*ible for
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the ?5/ of the total compre**ion$ 3fter it pa**e* through both the compre**or* it i* %5 time* than the out*i)e pre**ure an) 1000 than out*i)e temperature$ The compre**e) air i* no( at right pre**ure but it i* mo'ing 'er# fa*t *o that a )i+u*er i* pro'i)e) to *lo( )o(n the air$ The air then enter* the combu*tor (here the energ# le'el i* greatl# increa*e)$ Thi* i* accompli*he) b# a))ing fuel through a *eriou* of inector* to the compre**e) air (hich (ill cau*e ignition$
;ig ?$1$% ;uel inecting from inector
;ig ?$1$ ;uel an) air mi,ture ignite*
Thi* (ill further increa*e the temperature b# 1600 an) pre**ure increa*e* to %5 bar$ The more the temperature an) pre**ure of the air! the more energ# (ill be a))e) )uring the combu*tion an) more ecient the proce** become$ Thi* i* (h# the compre**or i* u*e) to increa*e
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the air pre**ure$ No( the *uperheate) an) compre**e) air mi,ture i* rea)# for the ne,t *tage$ =la*ting through the high pre**ure turbine the high energ# air *pin* the bla)e* o'er 10000rpm$ The*e bla)e* are connecte) to a *haft name) high pre**ure *haft that )ri'e* through the centre of the engine an) )ri'e* the high pre**ure compre**or$ The onl# purpo*e of the high pre**ure turbine i* to e,tract enough energ# from the air to )ri'e the high pre**ure compre**or$ Together the*e t(o component* ma&e up the high *pool$ 3fter that the air pa**e* to the larger high pre**ure turbine$ Thi* turbine ha* t(o purpo*e*$ ;ir*t it e,tract* enough energ# from the air to po(er the lo( pre**ure compre**or at the front of the engine core$ The *econ) an) important ob of the lo( pre**ure turbine i* to turn the large titanium fan bla)e* at the front$ The fan an) lo( pre**ure compre**or are connecte) to the lo( pre**ure turbine u*ing a *ame *haft name) lo( pre**ure *haft (hich i* pa**ing through the centre of the high *pool$ Together the*e three component* ma&e the lo( *pool$
?$1$5 E,hau*t ga* turn* the turbine*
;inall# the compre**e) air ri*e* out through the noIIle at the bac& of the engine (hich i*
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accelerate) one la*t time b# the b#pa**e) air (hich further increa*e* the thru*t an) it help* to re)uce the *oun) of the engine$ The high thru*t air .nall# goe* out through the noIIle$ The e,hau*t noIIle i* locate) )irectl# at )o(n*tream of the lo( pre**ure turbine an) it i* the la*t component that the air o( touche* before e,iting the engine$ The e,hau*t noIIle i* *tationar#! li&e the combu*tion chamber$ The purpo*e of the e,hau*t noIIle i* to propel the core o( out of the engine! pro'i)ing a))itional thru*t$ Thi* i* accompli*he) b# (a# of it* geometr# or *hape$ The noIIle al*o help* regulate pre**ure* (ithin the engine to &eep the other component* functioning properl# an) ecientl#$ The *pee) at (hich the ga* e,it* the noIIle i* calle) et 'elocit#$ The e,hau*t *tream pro)uce* the 20/ of the engine* total thru*t! remaining @0/ i* pro)uce) b# the large 'alue of accelerate) b#pa**e) air$
?$1$6 Thru*t of air mo'e* the plane for(ar)
:n *hort! thi* entire proce** can be bro&en )o(n into *tep* a* follo(* 1$ 3ir enter* the engine through the fan! (hich i* being )ri'en b# the lo( pre**ure turbine$ 2$ Mo*t of the air i* accelerate) out of the bac& of the engine through b#pa** port! creating thru*t$ %$ 3 portion of the air enter* the core of the engine (here it tra'el* through the lo( pre**ure an) high pre**ure compre**or*$
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$ Thi* compre**e) air i* then mi,e) (ith fuel an) ignite) in the combu*tor (here heat energ# i* a))e)$ 5$ eat energ# an) pre**ure energ# cau*e the air to e,pan) through the turbine*! *pinning the high pre**ure an) lo( pre**ure turbine* (hich in turn *pin the fan an) the compre**or*$ 6$ 3ir e,it* the turbine* an) e,it* the engine through the e,hau*t noIIle! (hich al*o generate* thru*t! propelling the engine an) 'ehicle for(ar)$ Thi* proce** i* continuou*! (ith each component )oing a *peci.c ta*& to &eep the engine a* a (hole running$
0.
CLASSIFICATION OF TURBOFAN ENGINE
The turbofan engine* are generall# cla**i.e) into t(o 1$ 3ccor)ing to amount of air b#pa**e* the engine core • •
9o( b#pa** turbofan engine igh b#pa** turbofan engine
2$ 3ccor)ing to *pool of engine Single *pool turbofan engine Double T(o *pool turbofan engine
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Three *pool turbofan engine
0.1
L" Bass T#!'"(a% E%)i%*
;ig @$1 9o( b#pa** turbofan engine
3 high *peci.c thru*t or lo( b#pa** ratio turbofan normall# ha* a multi-*tage fan! )e'eloping a relati'el# high pre**ure ratio an) thu* #iel)ing a high Kmi,e) or col)L e,hau*t 'elocit#$ The core airo( nee)* to be large enough to gi'e *ucient core po(er to )ri'e the fan$ 3 *maller core o(higher b#pa** ratio c#cle can be achie'e) b# rai*ing the KPL turbine rotor inlet temperature$ 3 b#pa** o( can onl# be intro)uce) if the turbine inlet temperature i* allo(e) to increa*e! to compen*ate for a corre*pon)ingl# *maller core o($ :mpro'ement* in turbine coolingmaterial technolog# (oul) facilitate the u*e of a higher turbine inlet temperature! )e*pite increa*e* in cooling air temperature! re*ulting from a probable increa*e in o'erall pre**ure ratio$ Ecientl# )one! the re*ulting turbofan (oul) probabl# operate at a higher noIIle pre**ure ratio than the turboet! but (ith a lo(er e,hau*t temperature to
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retain net thru*t$ Since the temperature ri*e acro** the (hole engine Kinta&e to noIIleL (oul) be lo(er! the K)r# po(erL fuel o( (oul) al*o be re)uce)! re*ulting in better *peci.c fuel con*umption KS;L$
0.2 Hi)h Bass T#!'"(a% E%)i%*
@$2 igh b#pa** turbofan engine
The lo( *peci.c thru*t or high b#pa** ratio turbofan* u*e) in to)a#F* ci'il etliner* an) *ome militar# tran*port aircraft e'ol'e) from the high *peci.c thru*tlo( b#pa** ratio turbofan* u*e) in *uch Wpro)uctionX aircraft bac& in the 1C60*$ 9o( *peci.c thru*t i* achie'e) b# replacing the multi-*tage fan (ith a *ingle-*tage unit$
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ecienc#$ Re)ucing the core ma** o( ten)* to increa*e the loa) on the 9P turbine! *o thi* unit ma# re4uire a))itional *tage* to re)uce the a'erage *tage loa)ing an) to maintain 9P turbine ecienc#$ Re)ucing core o( al*o increa*e* b#pa** ratio$ ;urther impro'ement* in core thermal ecienc# can be achie'e) b# rai*ing the o'erall pre**ure ratio of the core$ :mpro'e) bla)e aero)#namic* re)uce* the number of e,tra compre**or *tage* re4uire)$ ith multiple compre**or* )ramatic increa*e* in o'erall pre**ure ratio ha'e become po**ible$ >ariable geometr# Ki$e$! *tator*L enable high-pre**ure-ratio compre**or* to (or& *urge-free at all throttle *etting*$
0.3 Si%)$* S""$ T#!'"(a% E%)i%*
@$% Single *pool turbofan Engine
The *ingle-*haft turbofan i* probabl# the *imple*t t#pe of turbofan con.guration$ :t con*i*t* of compri*ing a fan an) high-pre**ure compre**or )ri'en b# a *ingle turbine unit$ 3ll of the part* compre**or! turbine! an) the fan are arrange) on a *ingle *haft$ The SNEM3 M5%! (hich po(er* Mirage .ghter aircraft! i* an e,ample of a *ingle-*haft turbofan$ De*pite the *implicit# of the
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turbo machiner# con.guration! the M5% re4uire* a 'ariable area mi,er to facilitate part-throttle operation$
0. D"#'$* 4 T" S""$ T#!'"(a% E%)i%*
@$ Double ' Two spool turbofan engine
%&'&( Bas!) *o spoo# Man# turbofan* ha'e the ba*ic t(o-*pool con.guration (here both the fan an) lo( pre**ure turbine are mounte) on a *econ) lo( pre**ure *haft! running concentricall# (ith the P *pool Ki$e$! P compre**or )ri'en b# P turbineL$ The =R?10 i* t#pical of thi* con.guration$ 3t the *maller thru*t *iIe*! in*tea) of all-a,ial bla)ing! the P compre**or con.guration ma# be a,ialcentrifugal Ke$g$! 7eneral Electric ;E?%@L! )ouble-centrifugal or e'en )iagonalcentrifugal Ke$g$! Pratt hitne# ana)a P600L$
%&'&+ Boose, *o spoo# igher o'erall pre**ure ratio* can be achie'e) b# either rai*ing the P compre**or pre**ure ratio or a))ing an interme)iate-pre**ure K:PL compre**or bet(een
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the fan an) high pre**ure compre**or! to *upercharge or boo*t the latter unit helping to rai*e the o'erall pre**ure ratio of the engine c#cle to the 'er# high le'el* emplo#e) to)a# Ki$e$! greater than 01! t#picall#L$ 3ll of the large 3merican turbofan* Ke$g$! 7eneral Electric ;6! 7EC0 an) 7En, plu* Pratt hitne# BTCD an) P000L feature an :P compre**or mounte) on the 9P *haft an) )ri'en! li&e the fan! b# the 9P turbine! the mechanical *pee) of (hich i* )ictate) b# the tip *pee) an) )iameter of the fan$ The Roll*-Ro#ce =R?15 i* a non3merican e,ample of thi*$ The high b#pa** ratio* Ki$e$! fan )uct o(core o(L u*e) in mo)ern ci'il turbofan* ten)* to re)uce the relati'e )iameter of the attache) :P compre**or! cau*ing it* mean tip *pee) to )ecrea*e$ on*e4uentl#! more :P *tage* are re4uire) to )e'elop the nece**ar# pre**ure ri*e$
0., Th!** S""$ T#!'"(a% E%)i%*
@$5 Three *pool turbofan engine
Thi* i* the mo*t complicate) t#pe of turbofan engine*$ :t con*i*t* of three turbine *tage*$ ;ir*t one for the rotation of the giant fan! *econ) one for the rotation of the lo( pre**ure compre**or an) the thir) one for the rotation of high pre**ure compre**or$ Thi* i* more ecient compare) to
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all other turbofan* )ue to ma,imum utili*ation of po(er in three 'ariou* *tage*$ Roll*-Ro#ce cho*e a three *pool con.guration for their large ci'il turbofan* Ki$e$! the R=211 an) Trent familie*L! (here the interme)iate pre**ure K:PL compre**or i* mounte) on a *eparate K:PL *haft! running concentricall# (ith the 9P an) P *haft*! an) i* )ri'en b# a *eparate :P turbine$ The .r*t three *pool engine (a* the earlier Roll*-Ro#ce R=$20% Trent of 1C6?$
5.
ROLLS6ROYCE TAY TURBOFAN ENGINE
C$1 Roll*-Ro#ce Ta# Turbofan Engine
3* an e,ample for the turbofan engine con*i)er the Roll*-Ro#ce Ta# turbofan engine a* *ho(n in the .gure$ Thi* Roll*-Ro#ce Ta# turbofan engine pu*he* nearl# three time* a* much air through the b#pa** )uct* a* it
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pu*he* through the central core of the engine! (here the air i* compre**e)! mi,e) (ith fuel! an) ignite)$ Turbofan engine* li&e the Roll*-Ro#ce Ta# are not a* po(erful a* turboet*! but the# are 4uieter an) more ecient$ The turbofan engine i* an impro'ement on the ba*ic turboet$ Part of the incoming air i* onl# partiall# compre**e) an) then b#pa**e) in an outer *hell be#on) the turbine$ Thi* air i* then mi,e) (ith the hot turbinee,hau*t ga*e* before the# reach the noIIle$ 3 b#pa** engine ha* greater thru*t for ta&eo+ an) climb! an) increa*e) ecienc# the b#pa** cool* the engine an) re)uce* noi*e le'el$ :n *ome turbofan engine* the b#pa** air i* not remi,e) in the engine but e,hau*te) )irectl#$ :n thi* t#pe of b#pa** engine! onl# about one-*i,th of the incoming air goe* through the (hole engine the remaining .'e-*i,th* i* compre**e) onl# in the .r*t compre**or or fan *tage an) then e,hau*te)$ Di+erent rotational *pee)* are re4uire) for the high- an) lo(-pre**ure portion* of the engine$ Thi* )i+erence i* achie'e) b# ha'ing t(o *eparate turbinecompre**or combination* running on t(o concentric *haft* or t(in *pool*$ T(o high-pre**ure turbine *tage* )ri'e the 11 highpre**ure compre**or *tage* mounte) on the outer *haft! an) turbine *tage* pro'i)e po(er for the fan an) lo(-pre**ure compre**or *tage* on the inner *haft$ To mo'e an airplane through the air! thru*t i* generate) b# *ome &in) of propul*ion *#*tem$ Mo*t mo)ern airliner* u*e turbofan engine* becau*e of their high thru*t an) goo) fuel ecienc#$
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Turbofan Engine Seminar Report 2015 - 2016
17. ADVANTAGES AND DISADVANTAGES A.ANTAGES
Turbofan
engine* can pro)uce higher thru*t at lo( air*pee)* compare) to other engine* )ue to the (or&ing of the giant fan$
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The#
onl# re4uire) *horter ta&e o+ )i*tance becau*e it can pro)uce high thru*t in a *hort time$ Their rate of climb i* higher$ The# (or& at high operation *pee) Kabout more than %000&mhourL$ Turbofan engine ha* con*i)erable noi*e re)uction$ :t* maor a)'antage i* that it ha* lo( fuel con*umption! ie more fuel ecient$
ISA.ANTAGES
Turbofan
engine* are uneconomical for *hort )i*tance
ight$ The# ha'e high maintenance co*t )ue to more part*$ The# are le** ecient at i)le con)ition$ The# ha'e higher *peci.c (eight$
11. CONCLUSION The turbofan engine ha* gaine) popularit# for a 'ariet# of rea*on*$ :n thi* one or more ro(* of compre**or bla)e* e,ten) be#on) the normal compre**or
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Turbofan Engine Seminar Report 2015 - 2016
bla)e*$ The re*ult i* that for time* a* much air i* pulle) into the turbofan engine a* in the *imple turboet$ o(e'er! mo*t of thi* e,ce** air i* )ucte) through b#pa**e* aroun) the po(er *ection an) out the rear (ith the e,hau*t ga*e*$ 3l*o! a fan burner permit* the burning of a))itional fuel in the fan air *tream$ ith the burner o+! thi* engine can operate economicall# an) ecientl# at lo( altitu)e* an) lo( *pee)*$ ith the burner on! the thru*t i* )ouble) b# the burning fuel! an) it can operate on high *pee)* an) high altitu)e* fairl# ecientl#$ The turbofan ha* greater thru*t for ta&eo+! climbing! an) crui*ing on the *ame amount of fuel than the con'entional turboet engine$ ith better all-aroun) performance at a lo(er rate of fuel con*umption! plu* le** noi*e re*ulting from it* operation! it i* ea*# to un)er*tan) (h# mo*t ne( et-po(ere) airplane* are .tte) (ith turbofan engine*$ Thi* inclu)e* militar# an) ci'ilian t#pe*$ 8'erall! the i)ea behin) a turbofan engine i* relati'el# *imple a))ing energ# to the air o(ing through the engine then e,tract* thi* energ# in or)er to )ri'e the fan an) create thru*t$ Turbofan* are the main po(er plant propelling et liner* acro** our countr# an) aroun) the (orl)$ ith *ome general ph#*ic* an) chemi*tr# concept*! one can gain an un)er*tan)ing of the*e machine* that ha'e re'olutioniIe) the (a# (e tra'el an) ha'e a greater appreciation for the technolog# behin) them$
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Turbofan Engine Seminar Report 2015 - 2016
12. REFERENCE
Rolt! 3$ =a&er! N$ W200CX$ :ntercoole) Turbofan Engine De*ign an) Technolog# Re*earch in the E< ;rame(or& 6 NE3 Programme! :S3=E 200C Procee)ing*! :S3=E-200C12?@! Montreal! ana)a$
=orra)aile! B$ W1C@@X$ To(ar)* the optimum )ucte) <=R engine! Procee)ing* of 3:33S3E3SME3SEE 2th Boint Propul*ion onference! 3:33-@C-2C5! =o*ton! Ma**achu*ett*!
Sirignano! $ 3$! an) 9iu! ;$! GPerformance :ncrea*e* for 7a* Turbine Engine* Through ombu*tion :n*i)e the Turbine!H Bournal of Propul*ion an) Po(er! >ol$ 15! No$ 1! 1CCC! pp$ 111Y11@$
"#priani)i*! "$ W2011X$ ;uture 3ero Engine De*ign* 3n E'ol'ing >i*ion! in E$ =enini Ke)$L! 3)'ance* in 7a* Turbine Technolog#! :nTech! chapter 1$ )oi10$11151$001C@2$
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