Configurazioni innovative di turbine di bassa pressione per motori aeronautici: studio preliminare aerodinamico e analisi affidabilistica % **

Transcript

1 !!"# Configurazioni innovative di turbine di bassa pressione per motori aeronautici: studio preliminare aerodinamico e analisi affidabilistica $%&' '%() *%)+ % ** %&'

2 ,,

3 *, -.,./, *&0.,1,/(.,,/2 % *,,..1/,,(3,/,/4 5.,/.,(-% *6.,.///(7.8 &96//-,,( /-% :*,()+// /*,%,,% *,/ 8%)/ /,/,*;69)/.1,,. / 8; ( &9, /,6,..,,/%

4 INDICE... I INTRODUZIONE...II CAPITOLO L AVAN-PROGETTO DI UNA TURBINA DI BASSA PRESSIONE PER MOTORI AERONAUTICI DESIGN PRELIMINARE AFFIDABILISTICO: FASE DI DEFINIZIONE DEL PRODOTTO Introduzione Analisi RAMS [1] Maintainability Safety DESIGN PRELIMINARE AERODINAMICO Parametri fondamentali da tenere sotto controllo durante il design preliminare di una turbina aeronautica...29 CAPITOLO PROGETTO VITAL CONFRONTO FRA ARCHITETTURA TRADIZIONALE, CONTROROTANTE E LPT AD ALTA VELOCITÀ CON SCATOLA DI RIDUZIONE INTRODUZIONE PROGETTO VITAL DIRECT DRIVEN TURBO FAN DDTF Lungo raggio DDTF Corto raggio CONTRO ROTANTE TURBO FAN Contro rotante turbofan lungo raggio...51 Contro-rotante turbo fan corto raggio GEARED TURBO FAN GTF lungo raggio GTF corto raggio CONFRONTI FRA LE TRE CONFIGURAZIONI...59 CAPITOLO AVAN-PROGETTO DI CONFIGURAZIONI OPEN ROTOR STORIA DEL PROPFAN Ricerche su propfan da parte di alcuni fra i più grandi motoristi aeronautici DREAM (VALIDATION OF RADICAL ENGINE ARCHITECTURE SYSTEMS) E GLI STUDI EFFETTUATI DA AVIO SULL OPEN ROTOR CONTRO- ROTANTE SNECMA e DREAM Analisi di Affidabilità CONCLUSIONI E SVILUPPI FUTURI BIBLIOGRAFIA...125

5 * * >61**/(9%/%%6*,/ ///*% '( (((///*6 /,////,/*? %! #6. -.,/, A)( ( ( /, //)6,,, 8* /// (*6.. 8* /*./ // /*% (. (//,/* (,,,/6//,/,,* /* /* ( /$ (// *,6 8*(% > 1 (// /, 9(//6,* ( %%&%9., // (// / * *./. (( / (, %, (**,/*/,,/(//*; 1/ -.(*@B'-(( '')///*/,,%, (//, /;/ C - (.// (,,,.,%

6 * 6 / / 1/-./2(/2 (,-%%% * ' 1 / *. /,(,(-.//( 6-,/./,./ (,/*(% /,,. *,,. // / - 6 ( - *6 -( ( ).,, 6,. ( ( ( / / / /, D((//,/,, (., */. ( (,/,/ ( %! * ') / 1 ( 6 / //, - 1 / - // % -*1/6(/. (.6/7,/ /2 66/*, E?=./7*//6*,/(.,/,/**./%, *((, ////*//6 / ;&6-1 ((. *6/,8,**/(,/, /// 8***,% /(/,/6 ((/,/(*6, //(//6/-8 6/,(68*%

7 B/, /* 6 3, / /6/7.,**(,..$ * B, 6 (( / -/(,/, /D///(// (.,, /,/,*9/ - / *6 * /*,6 */, /.. *,F 0 ***% B* 9., $./6(,*/ / /( // /D.

8 /,,*.(,,6*(*. / /6 * //, *(/,6,*/,6B"! 6,,.*/6/6 / /( 6 * /, / *D /,( /* D (///*&'% ( $-. 6 ( ( (,/.,/6/ (,/ D ( *6 ***6 **,/*/1//. /* D 1 (, ( * &' %

9 &$ '$ $""$ "$ // 6 /* / /,,,/6. 6 -,. * ( /6 (( *,6 ',6 96,6 (,/.G6 1, /, 6 (/-- (/ 1 -/(//** ( * - ( / */,-. / *.,/ / (( " /,6 1 / / (. ( ** / -,,/ ** 1-/ ( (,/(% 6/,,"/*(-/,6 / /*, 1 * * /.,,/ * 6, (,,/,.(,/% >/**/.,(** / -..,/,** /,**,/,/(% ' / $ 6 /6&6 9**6 &9 '0 ( / E6 (*, 6 // *,, 1, / &9 6H,//,, /- *** /(./ /,* B//*/** % A

10 J /6,/ /.6-, 6 **,/, /*//% B, / - -/,,/6 /.G *, D/2 / / (6, &9, -/ *.6(*6 //,, 6,@0 0 6,,/,,./ 6-,/(0 /6,/,% B, /* - // * (, // / *6,*.((*//D,, &9 )H6)&;6&0 06)'6 6,*.% )*+, &91, o 06 o (06/ o &06& o 9069** -/,,/,*6,.***/-1/% B. -/, /, ( **6 /,, 6 1, (**%' (F (&@9' KL+% ;,/A*$ I

11 o 'F % 9 ( ( /,, % o 'F % 9 ( ( /* (*% o 'F A% 9 / ( ( (// */*%.// o!"-'$'0./1 * /,, /. ( -/, 6 (. 6 ***6 6 /,. /(%'/( (//-/,% o *$"$ $"$$(!#$"#"$ (0./)1 - (,,/-/,,/% o '$230./41% C (M, -, (*,/,,%,,, N%% 6B B,0(M 6 (M %9,(M % o ( $"5 - $#"2 #"$ -" 010./61 C,/ ( ( /( (//6-* %'/( / %) 9 1, /.6 1 ( ( ( * (% ) 9 ( % o (237$ 0./81% C, /./, / (*, ) 9% ; / / *,,(**( ( (%) + ( *(% L

12 o!"-*$ 0.)/1 /,// * 1 (//, * -/, ** - /(%, 1 /,*,-/,,,, (/,/*% :,/,,,/7 /, * *D ((,,,. ( 6 / /(,,/% */(///,,. 6.. / //*,,,% ; * * -/,% 9,.,,.(**/*F% o!"-$#"$0.)/)1 ;,/ * /* ( / /% 9,/ -,/ - // ( -"( -/, (,,/% 9 ) 6 λ (,.,(,*,%,1 P6 /, (/, *,%!,,,/,/ / λ,/,$ MOTORE COMPLETO 0.01 CORE SHORT CORE EXHAUST ACCESSORI $ "!(&$ ("λ O

13 o!"-' #"$0.)/41 C/ ( " -/, *%@*/1/, /%,//(/-/,,6 (* /% 9 /,$ 9,,,.% C /* (/,(*% B %', **,/,.,,/6 / /% B9%&/2,/. / /,/ 6,6,-*,/% o '"'$0.)/91 9/ F 1 ** /2/ / /% % &@9'#OL o!"-"#"0.)/:1% 9/ (1/-,./, - %', -.. ( 6 /*,/ **6( // 6..//*/./6%;,/2F,(,/ /,,% o #" $ (#"$ "5 "$5 ; 5 '#.5 $""$ *"#0.)/<1% -/, (/ // /(6.6,,**,%@/, /% o (*$ 5 #"5 "#"- - 0*1 0. / % /,, 1/, ()H% '/,/,-/,6,//7,/66./(% K

14 @)&;( (// O#%;,/. )&;, ( - //,* / (,06 06 )&; 1 /.6/ / (,/6 -.,, * 9** / )H 6/ (* // * ((% B,/* ( * / 6 ( (/,/*/(.D7 *,( (/6. //((/*/% )&;//,** $ o (,/ ( * -/, /D o (/",/D o -,/../ * >0 /(D o (*/.% //(*/**$ o (. D o //,*D o )&;6/7, //$ 9MJ.M% /,, 9M J/( / *6 * *., - * /6, // HM,/**//,($1 -/,, 6-,/.,6,/(%.,**/// //,,* /6 (()&;/,.,$

15 ITEMS / FUNZIONI FAILURE MODES EFFETTI LOCALI EFFETTI FINALI AZIONI / SOLUZIONI )=>(& (* /1$ o /,6,6 -/, ( ( //,*D o / - ( 1 /,.,,/ 6,. (*,(D o / *// 1 /., // 1 (,/%,/*($ o *,/D o,d o *% 9, )&; /.M.,/, 6/,,. * /D 7,,**.,./,,E 00=% /,**,E000=/* B,0)&;B)&; D,/(6 ((,/* ( 0 &0 /, /6 (/-/ *,. (/**/% #

16 @ )&; 6, *6,/ - / /2,/,/( *,/. * /.% 9/(1*,/ B)&;")&; /D /. //.,, /(D ( // / / * B)&; )&; / // %A - ( *,/ $ B)&; *B )&; B* TIPO MOMENTO FINALITÀ INPUT ESECUTORE Funzionale Alla definizione del Prodotto Hardware Progettazione In caso di evoluzione degli standards del progetto Aggiornamenti per ritorni sperimentali Consentire analisi di trade-off su configurazioni alternative Generare l analisi qualitativa e quantitativa del progetto PFMEA General Arrangement Lessons learned FMECA Schemi PFMEA Allocazioni FMEA preliminare di processo 4("$("(" (* Responsabilità: Team leaders dei Centri di Prodotto Operatività: Specialisti di Sistema Specialisti di Disciplina Supporto RAMS Responsabilità: Team leaders dei Centri di Progettazione; Operatività: Specialisti di Sistema di Progettazione;Specialisti di Disciplina di Progettazione Fornitori Supporto RAMS Partecipazione di personale di Industrializzazione di B)&; 1- /, / / D///,/*1/9MJ6. (*//*% ;/(/*,6.,-*/*(,** *%

17 ;/2 ;* B&; )&;6 * *. (/, 1 ( / ( 6 (, )&;/ * (/,. (* (/,D G, * / / ( /(,/%! /(- (, / (*6,,/ * * */((/ 6/,/6 /* // -* (* 6 ( 6 ( /, ((6, /*,, 6 /2/ (* ( 6 (, D /7 (*.,, //* /((, (/ (../,/ % ;//)&;6** (*0,",D7/, (* ( -. (* (, B)&;/7,/ /, (* /6,.,/, D ( **,",/2,/6, *,/2 (% '//(/,,. / ( * (D/, ( * ( ( / ( / B)&; 1 // ( D ( * 1-/ *

18 /,,6(",,( /, $ ';& $,,,(,/ /.,,% B '"):!'J! $(,** (,/",,6 * //, $ /6 % D/ (,/ / * * /2 (% A)@: ;&J; $ /,(/2,/D, ( * / (, //% I:9; $/,(% LB J++@'5 $/,/, -(6 QBQI H D IQBQO & & DBRO@+.((.% O!'@;));' $)* * /(/, (% 9 /,*,/( ( /,D /* /2 - ( /*% K :@'&';;));' $) * (* (* (,% 9 (*/2 6 - ( /*%

19 9;C; '5 $(/(6 Classification Abbreviation Catastrophic Hazardous Cat Haz - / (% Failure condition Catastrophic: Failure Conditions, which would result in multiple fatalities, usually with the loss of the aeroplane. There are no specifics about failure conditions classified Catastrophic in CS-E or CS-P. This classification is only defined on A/C level. Hazardous Engine Effects: i) Non-containment of high-energy debris, ii) Concentration of toxic products in the Engine bleed air for the cabin sufficient to incapacitate crew or passengers, iii) Significant thrust in the opposite direction to that commanded by the pilot, iv) Uncontrolled fire, v) Failure of the Engine mount system leading to inadvertent Engine separation, vi) Release of the propeller by the Engine, if applicable, vii) Complete inability to shut the Engine down. Hazardous Propeller Effects: i) The development of excessive drag. ii) A significant thrust in the opposite direction to that commanded by the pilot. iii) A release of the Propeller or any major portion of the Propeller. iv) A failure that results in excessive unbalance. Hazardous: Failure Conditions, which would reduce the capability of the aeroplane or the ability of the crew to cope with adverse operating, conditions to the extent that there would be: i) A large reduction in safety margins or functional capabilities; ii) Physical distress or excessive workload such that the flight crew cannot be relied upon to perform their tasks accurately or completely; or iii) Serious or fatal injury to a relatively small number of the occupants other than the flight crew. Major Propeller Effects - iv) An inability to feather the Propeller (for feathering Propellers); v) An inability to change Propeller pitch when commanded; vi) An uncommanded change in pitch; vii) An uncontrollable torque or speed fluctuation. Major Minor Maj Major: Failure Conditions which would reduce the capability of the aeroplane or the ability of the crew to cope with adverse operating conditions to the extent that there would be, for example, a significant reduction in safety margins or functional capabilities, a significant increase in crew workload or in conditions impairing crew efficiency, or discomfort to the flight crew, or physical distress to passengers or cabin crew, possibly including injuries. An Engine Failure in which the only consequence is partial or complete loss of thrust or power (and associated Engine services) from the Engine must be regarded as a Minor Engine Effect. Minor: Failure Conditions which would not significantly reduce aeroplane Min safety, and which involve crew actions that are well within their capabilities. Minor Failure Conditions may include, for example, a slight reduction in safety margins or functional capabilities, a slight increase in crew workload, such as routine flight plan changes, or some physical discomfort to passengers or cabin crew. 6#&$ 2"?!""$ ("$ A

20 # )-0 $ -(, /. (.% Probability qualitative definition Extremely Improbable Extremely Remote Remote Reasonable Probable Quantitative value P< <P> <P> <P> 10-5 Frequent P>= &$ 2 $!!"? )&. $9-" - ( /*% ;& S9" 'J! $ - /,* *. / 6, / (*. -( # )-0 $ -(, /.(.%.4//% o 2$""#010.4/1 9/,*/(.,*(*6 / * /./ (* - / *,,% 9 /,. *, //(*,/ (*. KL+,.T;99%/.%1( I

21 /,, *, /% o!"- "'$ 1 0. '% 1 / -/,6 //;%9%9% /1(.-/,/% '/, * /( 6, */% :-,0?/,/- * (., M. %,,/**/(-/, (*%:, (* M. 1, % 9,, &'+) &', +M)$',/, (6 1 / % o!"-a(#"$ "0A 1'$0.4/41 >' 1 ** //*//(. / -/*.% '/.G1,, - ( /.1 1 */% o '$ (#"$!"- ##"# "'$ 0' /61 /. /* 1 * B '( /,. - /*(,% > -* (% L

22 / 1 /,, 1 /.,,( 6,6 0 //, /. -,6/,* % %; // /. -/,/1**-,* ( /((,%!/ E= 1 / E = 1,,6 ( /,6,/, /D/,. //. 0,,% 9/-/(/,/. (,/%;,/$LTRIL,%D#LTRA%D T R O %' - -/, ( ( 6,0% )4*"!"- 9/ (&,0 1- / // ** /., // G,/ (6.,,*/,/./* 6/G, (0 %@,*, U& /,,// - -/, 1,/, / %;/-. (,,/,% B,&,/.,/ /,/,%, 6 /.-/,/, (,6,,**. /,,,6G, (**%' (F (&@9'IK+% ;,/A*$ o 'F % 9 ( ( /,,,%/* O

23 /,,,%9,- 6(,/,,,/,*,/% o 'F%9 (( /*, % o 'F A% 9 / ( ( (*,/(%.// o *"!"-'$'0./1 * /,, /. ( -/, 6 (. 6 ***6 6 /,. /(%'/( (//-/,% o *$"$ $"$$(!#$"#"$ $0./)1 -,(,,/-/,,/% o '$230./41 C (M, -, (*,/,,% U&-,/, 6B 6 %.(M((% o " $#"$5 - $#"2 #"$ -" 0. /61 > (,.,%;/ /*6 // /( (//6,*.,/ (*%,,,,* (,/ *,(6,/.6 / 6 ** **//6,%.)// *"!"-*$ //,*.(-/,,/% *** ///,/7 (// K

24 /**/(,./%, -/,,,/-,,//((( ( %/(/////,,(/*%:,/,,,// &'' &', /$ 1,/,,* /%*,&'' 1 (// /*D/- / 1,/(,,/,* -/,1$ &&' V'BW')W' W'W'JVΤ 6 ('B1,/,//*6') 6' */*6',*6'J /(Τ 1,,,/,,/-/,% *"!"-$#"$0.)/)1, - / (,/ ( ( ( -/,%; / (//.,( /(%' (/ /, &'' //, /,&&H"JH&&H/J/H$1//,,**,%;(,/* (/ //&&H")H&&H/).HD1//,,*( % SISTEMA A MTTR=1.20 SOTTOSISTEMA 1 MTTR=0.45 SOTTOSISTEMA 2 MTTR=0.75 COMPONENTE 1 MTTR=0.25 COMPONENTE 2 MTTR=0.50 B#=*"!"-$#"$ *"!"-' #"$0.)/41 9/ ( 1,, -/, (,% * / **,*,(/**6,,. *6*,/* %@/*,/,* (// **,/

25 % / /6 - -,*,/ 7/, /*% o ( *$ 5 #"5 "#"- - 0*1 - * /%)&; // & /,(&00'FL % &6 00%>1 (.( (&@9'IAKA../ ( F,*/(( // %; /./ )&;/, ( F (6/( *6 /*6 * /,,. %!/,, (.,&9A & 9 /.1 &% o *"!"--0.)/81% > 1 F.( /,,,% / 1 (,, (6( (6 //,*6.%;,/.(/,//(/% o *"!"-"0.)/B1% 9/ ( 1 - / /*,% 9/ ( /*/ 6-/6-H,;./( ( &@9'IK% o '"$ $ (""$"= " *"#' $"#($"-010.)/91% / (,( /6 *,/*,*%@91 -,. /6 F6 **6 / -.. -/, 6,6 0 % %@9( 6-.6 &@9'A% #

26 o / 1,,. -/, 1,,/(%;,,,,,/(//6 -, - F,/,,. -/,/ ** (*%@ (( // / (/*/*,*% 9//*(,**//*B,B.( %; / *,*6 * -/,6 (* **6 *,,*,-% )6"- B-/-/,6 /7,(*,61%J( (90, 90 1 * / ** (*, //%, / &9./901 /,,90,90/./**/% * /,, 1 &@9' + 90, 90 B, -,%. - ( ( /* 'F (/(*'F %.// o (0,*% o ""$@*"$(!#$"#"$0./)1%, /- ( (, //% o -""-'$230./41% ( /% o -""-C$.$(0./61% C // (,/ //,..,//*/*

27 (//-/,% o ;& #..$("$0./81% 9/ ( 1,,/ * H**//*%;/ -/,.% o " ** (, / G, ( **. / (//(-/,% o -""-'$(-0./91% > 1 //.,,.. ( (*,/,,0,0% o '$A(#"$0./:1% > F - /*. / ( (**(/%.)// o '-;& "0.)/1% >F/(6*/6//*./*/,%; / ( %'. //, % o '-;& -0.)/)1% 9.F,-(.* ///% /*.( *% o (!-";& -0.)/41% > 1 //,,,/ M/ 0, (/-%;/,*F U%,-F,F% o -";& -0.)/61% > 1 0.(,,/% F / 1 ( / %@( (/,,/* **( 6 ( - % + 1 B,0 H*@ )&;% 9/ (,/ )' 0 )'./,

28 /6 / **6. /,**,,% o " ($";& (1-., /,6/6/-/,//% o ##("$;"=;& "0.)/B1% C ( /. / /. ** -/,,%@/*,,(*6,6 % ( % F 1.,., % o ;(/,(,/6 /% o 0.)/:1% /(/6(//6-/, (, /.%@/ - ( 1 //(//% o "-"0.)/<1 :(* **( /, (/// (/ ** /- /./% o "-$#"0.)/1% C. (* (,,,6*6,/,/%6 --/,/../- **6-/F//% o ='$$0'1230.)1% 9/F1/((,./( **/,, ((///(*% o $"3;& -0.))1% F/(**/-9M%B.G,, ** 9"X/ *, 1.-.**%C69"XF%

29 9/,, X/ 0, / -* ((% B7. ** * -/,//% A

30 )'$ *, //, */,,,6,/./ /,/7.,** ( /*% 9 ($ $""&$$ # / / -/, (, (, 6, (*,, 6,, (, *,/ ( /-,/,,%: -/, 6,. /,///* *% (,,$/6,/6 /6 D/ 6/*.6// 6,/6/ /, *./7,/6 // (,6 //, ( * ( /**./,/ % I

31 :,/* ( * * -,1,,% >,/ -/, 6 /,6( 8,,/ **,,6/,/, /,-1 8,/(. ( /,/6 // /..M/.% >1,//,,/6. M/. ( /, 0, D /,.,..,/ ///. % B,,** / * 1. 8* 1, /*(,,,,D1 -,**,,** / /(/2,/,% /, - /, -,6 ( /*,. ( *,/% o M/./ o,. o,/. o o (, o ///* L

32 ;,.6 -/, /,/%*/*,6,- ((/6*(*,/,/ / ( * (6-. ( (1*./,,,6,. (/ (,. * 6,.6.6/-(,/% (/, ((,/ (// ; 9(//C+//6E'2% (, 6 M/.6 * -* 6 -, (,,, ';'; /,///%!%1/(/, 6,, 6,/ * M/.6/6,*M.% :"## D! O

33 / -,** 1 (,/* *,/(. 7. 1,, (, 6/7 /. M ( *,,6,,% (/,*/* -/ -,, *6,,/6,,,/6,,,6LY%%*, / (,/, (.,//6,**,% <$#"$"$ 2$#"? "=5$("(" "$$ : (,** (,/ *,,6/, */,/,6. (,.,'26 (// /, 9(//C+//%' *,6 /,..17.1)6;6% B,,/ / 1 * ',6 6, (* %%K /*%!,/0/,/1,. ( /6,/,*** / LT. 6//7,/ (*6/,//, /./,,6((.,%!(/2AL,6I///, (,% 9 -/,.6-1/ / (% K

34 /"&$ "(!" "!2$5(( $ """&$""(""! /, ( / )6-/,( /6 **,. /M6 6 6 /6,.6,/6./,(/%,,/. (,,/ /( /,6,,/-,//,,/% >,1,,//.G/,,6/, /,/ (//-%

35 )'"$ " "$""$ #$"$$ (" ( "(!$("# )$#" ##$0E1$#" '$""0F1 >/,/ (,,9,.6 -/Z -[ % 9,, 9,. / )M' 6.,,6*6., 6,.//,,/,/ 6//* / 6//* % "= /*,,, 9,./, / /6(,,/*/ ( (*6/*6- /,, /, /2 ( (*/2((% B,//(, A/6/.G, /.*#IT-ZVA.*#T-,,*/#T6(,,( #

36 (,,,(,,*, #AT% )) $ &$ *,. 1 /,,. (8*1(*/.. (,.% 9 *,., // (, ( (, // 6.16(*/ (*/$ ( (. // ,/(6,.% 9//7($ V##= &$,/ 6(1(* /% R R##=&$6(*/(( % V##=&$(6(1(*/ 6,(**% 9,. *,/%I%L% )4#" ($ " :,,/,/- %6. / ( *,, * +B 0/ $//.//, -. (,/6, 6(,% / ( +B H /,,.,, *6 //,/,,/,*/% A

37 )7'GH2 ($ " B,/,+B,,* (#/7*/K/.G( K(#//,/,/(.,*/,,,**/6(,,/ L(K/,,6L//(% :,,/,,/ -/,1/+B 6L+B 6 +B 1,,')6(,,+B,,,% >(+B,/7(, 6,//"*. /,///*.(,/% //,1/%%((, *,/%:/*. 6 (, (- ( *6/,,,.(,/.,6 * //, \/ /(6 ( -.//*6,*/7%!/,/ //*.6 (,/2 -/2/2-/2/% A

38 4"G )6#" ($ #=""$#= $"$ B,B, /,% Mach Number "!(&$ ##$(($$$ #$ ]M ((,,- ( * (( //, % 9 B (,/ /,,//';% Optimal Work A

39 /. * / / (,1,/6.,6.,,/ 6.,&., - - (, / B9.,/(,,6-,, % B///.*/1,/ ---..,1/2 /B%9%,,*//.,,..,/% 9-.((/.]M(( %-%>,1//.G/(]M, // 6 1, %A, // ( - 6, * //,6 (]M/2. ((. *, 6*66, 0/% %I,, * % Vane Blade α in= Vane Blade α in=α out Yp* αout Yp* αout s/c 8$ "?(&$ $$ $ (#" s/c!(/6- (1 ((6* A A

40 6,,/6/.*%9(..( (,/(///% )8 *. 1 /,,,/,.,/,(*/% (/7 (* /,,., **,/%,( /, ( /7 (,,,/ T AT.,% (, $^RKLY&. R%#% B-..^RLY&. R%I% ( /(. ** ^RLY% A I

41 ** / BC. *6@B' (*% )"$ (// / 1 (,/, /%@ * / 6,, / / %OT / / L, %!,,,6, / LT 6/.#T/((//,% :,, +_`.,(*- /* (* ( /, # %@ ***6,,***,.6,,(*,, *.,/ E@M =6/, / / AL, / /, ;: JJ!' J@ '.;/ J. 90!( _A`%'., /( AO((%& T - (*$ 7. /,( A L

42 ** /2 # (((_`6 KLT 1 (,"// %(,/(,1, A,a!,6B;/% )G#" ($ #"$$)/ ))G#"$2"$"#$$($$)/)/+4, --(//6,*., */,//,/ % A O

43 **!3E;/.=; _I`6..((// /,6.(* /%*-,;/1/(( / (// /* 6/ 3 ( 9,, E. M,,/(0,FM,0=% 9-6 6,,/ B.// +-/,/ ; 6,, ( / 6 7 E/ B=% -/*/6.,EC= _L`% E, 0 0, M ( 6 (-06.(0..0(,/ 0,.,0M../MF=_L` /, / ( */-/6,66**6,/,D./ /, % //./ *// **,/ /(C$3E(0. ;/= %%% %;%.. / (/ 6 /,//* %'($ *T,!J? D,*(,//D,*TD, O,( D *LT,J //D,,L,/##T(% >,9 <9. 6 L6-((//,, E;: 9?.. ),MF B,,= )BO ),MF B,, )B /6 /,6 ##% A K

44 ** ## / :;/. // AL/ 6/ (,/(I,;6-,*/(% / (,6..,,,/ /*$ o!!"""$ $ * 1/, //,,/((,% B7//,((./,,(,%%A $3 I_O`6 (/// 6.,,-,,/,-/,.,% )4G$ (#$!("$"(!$+B, :,/ - 1- (, ( /,,,,%>./7**,,*6./7/, 6 ((,,,,,.,/%//-(61 66,,,,*6,. *,,/., 6,/,N % ;, % A

45 ** ()6G$ $#$!("$$3I#$$"0JI51 o (&$ 1(,* /7 (,,*, / 9) %,, (,/2 / (,,.,//*%@, */ ($ %,***.% % (/6,,(/,$ o *6,*/,/2 %H.9@H.@ 6E/= o */(,D/,/,, / // */ /*% o * /,/ **/,/6/ 6,* / 6 / 6,,/,,, * (( ( / (6, 6,,% > *,/( A #

46 **,. */, /*%,//*/,$ % * '). * 6./,,,-(//0 /**/,(,,* / - /,,,/ /*% % * './( ( * // 0/%, 1 /(,,(,- ( * (.6,, /(,% B, * **,, / 0/,//2./ * EJ/ = - /2,/,% )8G$ $(&$#="""($2"2% $"$ o!!"""$ (,// / % B,(*,/(%%% %;%6 1,, /*,,% J.(( ') ')6.( /((,6* ** E M =6 (*/.6 (,/*,*A.M6/ % I

47 ** B/ 1 / (* ( * ((./,,/,,,,/*6/,6,-,% )B2$(&$!-"$#$$ ))'$""$" C 1 /,, /6. (*. /,* - ;6,/, // % / (,6- ( / **, *,///LT6*8T*!J? 6*LT6 ;/I/-,,;/.,L*/2LT/% */LA/9,6-.,/, /6-06&': ;6 (6 C( 6'B% / (//,/ /,6(/ (, 6,../ ///,-% I

48 ** J (-(6 / //6 / C6/,/(/26-$ B,(, /,/ /,/(//(///,/2 9(//*./,/(,% 9/.')6 ')6')6 ///*@.9. /C )4#"2"(!$ ///,,/ ')6 / * 6./-. 1,***,, ** 6,/, / 6/,,/, /*,,% //,6,/,*** **,,/* (,,/6 *,,**6 /6, /,,,,**% /,.,,/,( A% F. * ')6 ((. *, (/6,*/,,/% )9#=#"2 (!$K I

49 ** )4 ($$ (/,***, ((*6, *./((,/6,, *.//,,/,-,/.,//% /,(((,***% B,///*//(,/(/,,***% Eta ):#&!////,*(/,***(,,*6**( #%OT6..*// -(6-.(,,***,/,/(.,,/*./2./,D,/, ((,%./,/% &(/,**6*1// 6 7./*,/(-/,,. */26/7(.,,/,,/ I A

50 **,/(,/./ (% Weight ):!'$ *.//(/%%% Blade Number ):#($#$2$ $ I I

51 ** 0.58 rtip ): $$ $ duct ):$ (#" B- 1/(/,.G*(/ /, /,( //,/ - /2 / ( 6 /* -,. (/,% I L

52 **,(//16*1-,,,.- ;-,***,/ 1. *. /,% acous ):#("# % (% 1 %,, 9,. %, /*, 6 /*-((*6 /,..*/2% )<"#$$!"(!' #&$ I O

53 ** )/$#"$ ) $ 2$#"? )) "= I K

54 ** )4) $"$$./ * ( 1 /*/,(*,,,/,, *. (,/ /* ( (*6,./- (,,/, - *6/6% B * /* / /,/,***% Dati ciclo Inlet Mass Flow MF [kg/s] Inlet Total Pressure P [kpa] Inlet Total Temperature T [K] Inlet swirl Angle α [deg] Outlet Swirl Angle α out [deg] Outlet Total Pressure P out [kpa] Rotational Speed n 3040 [rpm] Turbine T.T. Efficiency η 90.11% [-] Specific Heat Ratio γ 1.35 [-] Gas Constant R [J/KgK] Dati di ingombro geometrici Inlet Hub Radius R in_hub [m] Inlet Tip Radius R in_tip [m] Outlet Hub Radius R out_hub [m] Outlet Tip Radius R out_tip [m] Turbine Length L [m] )4"##$$!$"# I

55 ** )6#$#"$ )8 $ 2$#"? )B "= I #

56 ** )6$"$$"""(!$ /,, / *,.6(H" :,%K% /, b 1 (/ - *(% %K /7 ( /,.. / /*,6,//,./,(**(/,(/ //,/1(. % )9#=(&$ L

57 ** )6$"$$"""(!$($$,,./*,,/,/% 9 /,/. /*,, / - / ((,M/.-.(, / - 6 (,, 9,.% Dati ciclo Inlet Mass Flow MF [kg/s] Inlet Total Pressure P [kpa] Inlet Total Temperature T [K] Inlet swirl Angle α [deg] Outlet Swirl Angle α out [deg] Outlet Total Pressure P out [kpa] Rotational Speed 1 n [rpm] Turbine T.T. Efficiency h 0.89 [-] Specific Heat Ratio g 1.35 [-] Gas Constant Ρ [J/KgK] Rotational speed 2 ν [rpm] Dati di ingombro geometrici Inlet Hub Radius R in_hub [m] Inlet Tip Radius R in_tip [m] Outlet Hub Radius R out_hub [m] Outlet Tip Radius R out_tip [m] Turbine Length L [m] ):"##$$"# /. - *,.,(%.,, 9,. 1 (*. ((% L

58 ** )<#$#"$ ))/ $ 2$#"? )) "= L

59 ** $"$G$"""(!$#$"$$!////* Dati ciclo Inlet Mass Flow MF [kg/s] Inlet Total Pressure P [kpa] Inlet Total Temperature T [K] Inlet swirl Angle α [deg] Outlet Swirl Angle α out [deg] Outlet Total Pressure P out [kpa] Rotational Speed 1 n [rpm] Turbine T.T. Efficiency h 0.89 [-] Specific Heat Ratio g 1.35 [-] Gas Constant Ρ [J/KgK] Rotational speed 2 ν [rpm] Dati di ingombro geometrici Inlet Hub Radius R in_hub [m] Inlet Tip Radius R in_tip [m] Outlet Hub Radius R out_hub [m] Outlet Tip Radius R out_tip [m] Turbine Length L [m] )))"##$$"# ))4$#"$ L A

60 ** ))6 $ 2$#"? ))8 "= L I

61 ** )8 "(!$ * ') /// ((/ 6, 1 * *,.,, /%O/(*)% ))B."#= )8 ($$ Dati ciclo Inlet Mass Flow MF [kg/s] Inlet Total Pressure P [kpa] Inlet Total Temperature T [K] Inlet swirl Angle α [deg] Outlet Swirl Angle α out [deg] Outlet Total Pressure P out [kpa] Rotational Speed 1 n [rpm] Turbine T.T. Efficiency h 0.93 [-] Specific Heat Ratio g 1.35 [-] Gas Constant Ρ [J/KgK] Dati di ingombro geometrici Inlet Hub Radius R in_hub [m] Inlet Tip Radius R in_tip [m] Outlet Hub Radius R out_hub [m] Outlet Tip Radius R out_tip [m] Turbine Length L [m] ))9"##$$"# L L

62 ** )):$#"$ ))< $ 2$#"? )4/ "= L O

63 ** )8) #$"$$ Dati ciclo Inlet Mass Flow MF [kg/s] Inlet Total Pressure P [kpa] Inlet Total Temperature T [K] Inlet swirl Angle α [deg] Outlet Swirl Angle α out [deg] Outlet Total Pressure P out [kpa] Rotational Speed 1 n [rpm] Turbine T.T. Efficiency h 0.93 [-] Specific Heat Ratio g 1.35 [-] Gas Constant Ρ [J/KgK] Dati di ingombro geometrici Inlet Hub Radius R in_hub [m] Inlet Tip Radius R in_tip [m] Outlet Hub Radius R out_hub [m] Outlet Tip Radius R out_tip [m] Turbine Length L [m] )4"##$$!$"# )4)$#"$ L K

64 ** )44 $ 2$#"? )46 "= ( * /*,,, 9,.6,-.-/* **,%:,(//-,/,1,(% L

65 ** )B$$""#$(&$ *. 6 / ( *% Lungo Raggio Corto Raggio DDTF CRTF GTF DDTF CRTF GTF Deflessione Massima Numero di Pale Peso Efficienza 89.68% 88.61% 94.39% 90.11% 89.39% 93.51% )48#=("2$ "#"2 B#$(&$".&':6_K`,,/* * ')/ -,/ *, / - / /*/,'9)'./),/ * '9)/7 (,,,,6//2,//2-, /, (,//* E0/ **\(0=%: 0/ **(0 // //)-/7(,/ /.% %AO /,/ /., )B +0/.//,/,,,**,,(--,/ ;% L #

66 ** )4B#="""( 2 $"$"(!$2 7-"$ '("$ :(,/,/ 6 / *./- % B,,, 0/,*/, % ((),.-,(( 6 1 / *, 6 - ( 1 (,,,/%,0/.,,, - ( ( (,/2/6,(( /,% >/,/7 / //, ( *)./,** /.(/,/. *//,(((,0/6*,.**,/(,-/,/,*% '1//(,6, 6 % O

67 ** :/*, / 0/ 1 *-.,)% B- / //,,6-(-( % ( ( *, / * ( / (*,1/,,% :, ( (/, (,(**@B'* (,*% ;.,(,,,/ 1,+0B)M/.G, (, *,6,/.,,,.///2 //**% 9_`*(*+B O +0B //E=/,/ 6,/*,/,+B % )49"$#$!-"$ 2B>("$/>(!$ O

68 ** :,+B (O /,, %%A(*IT/7/((* // ( 1 * * * ') / // *,/ 6 * 6/ %,, /**,% : /,,,./, +B 1 * /*, /, / % )4:#&(&$ 7-"$ B-),+B (,,.//,.6-/7,/(*,.(/*% >/ (, +B,/,, /6.,(, %%A#,/ 9)% )4< "(!#$2&$2 ($ " O

69 **, (* /.-,. */,1!,V+B -+B % (,,1,/. (,/,./2% +B, *.,//*-(/,/6 6/,,,,/* % > /, +B 1 *.//,(* /*% * ') ')6 (., */%%I6/(,,...,,/,,6.,6,/?6-1- /2% /(,,/.1,6 (,6/,*/2% )6/#= #$2&$ O A

70 /A(B*J/ /A (B*J/ 4"$ '$ *, /** / /, /2 /. / // / /*, -,,% 4 "$ &&$ "$$0 $1 OK *1 /* *** /,,//% > / // /*, 6(LF,".// F!6,, / - 6 OI

71 /A(B*J/ / %KF".FX. * A/ / %,//6,,//*.. 0/ 1, (,6 (/ 8,%//*//.*, /%! /2, / (,.., -,% >, 1 /.G 8(( ( - 6 / 86, ((/ ((6/ *% > (( / ( ( / - 6 /.,/ ( (%B,//((*8(,61 ((/,/,6, -,((,. /6 /.6((.% 9/ (- (( ( /,(6-/7(-,,6.,, 8,%,- 1 (*86./7,(% B(-/,6.,/../** /*,6/,,// 8. / / (// L/,. %:, -. 1 / (6./, * */,% OL

72 /A(B*J/ 4)$"$$BK5("&&"((K '-,. /,( * 8/2 /%@( * /,..,//,**8 % >/ * 6, -((,,,.((..61 ** /,. 3., ( / 8 / 6!9%!(./,.(*/2- - /% //.., /,6 * 6.6,, (*6, /( /6/(.,. -./,,,,(,,% &,,// 0// -. +B,/ -6, //, * +B,/(% OO

73 /A(B*J/ >/,(*,**,// ((, 6,,, / L% // 1 ** ( # / (,,%K/7. *c#/**/(,6( (// -,6 ( / /, 6 (*//% / 1 / /,6 /2 /,.-,,6,. - ; //%@ *** -, (6-6,, - *6,/ //6/,-,,% 4##=($ " #( D $"$"$("# 4#"##"01!,* #I6 ; ;!9/ // (// ;AO,,,( :) :' 6 (/ //,,( :)%@/(//-///// // (,/ /// 1 *..0/ /(( ( / ///( *. /* (% - /* (6 - / ( //, /8% OK

74 /A(B*J/ (#" // 1,/ -. /.. //2. / 8 8 //% - / 6 - / ((% 3 // /( *, 6 *//(,,,(//%/1 **/,,*//(.-/.G *,/ /, / 1 /, / ; 7. * -./(?, */,,6 - / 8((,%.(-* //, //, ( A /, /*6 ; /,. ((, * 8*/6 */ / * /,.,/2/,/2/%6 O

75 /A(B*J/ );).0;6,,/**.6,** /, 6 ;. /,% : ( - * (. / /,/( /2 6/.G //./*/,(,6., // 8((,%!8#L;*/,;AO8,,%C-8/7 /*6, * / 6/7,/ 8 /,,%; 7 / /*,,*,68#O67,;AO +KK,(/%, 36 #O6 /( 6, (* / /6 *,,,%!(,#O,7/*, - /,/ #K% 9(,6 /, /6//(**7&&%@;6 /9,6((7-(//,;AO/F! /%! ##/76 / (/** /6/(/% 46*G:/#$$($$ O#

76 /A(B*J/ ;AO( / E) 9'.0, &:);/=!96- ( (% 'ipo Propfan a due alberi. Generatore di gas Turbofan a basso rapporto di bypass, modello F404-GE-400 con massima quantità di aria trattata pari a circa 65 kg/s, massima spinta a livello del mare pari a 72 kn, rapporto spinta-peso di 8:1, consumo specifico pari a kg/hn Compressore Tre stadi di fan (indicato successivamente come compressore di bassa e pressione) e sette di compressore assiali con rapporto di compressione Turbine totale pari a 26:1. Turbine di bassa ed alta pressione ad uno stadio. Il compressore di alta pressione del GE-36, a differenza di quello originale presente nell F404 ha il primo statore a geometria variabile, ciò al fine di evitare lo stallo a bassi regimi di funzionamento Turbina di Potenza A bassa velocità divisa in due gruppi e direttamente connessa alle pale dell elica. Ciascuno dei due gruppi è composto da cinque anelli con palette di turbina classiche ed uno invece composto da palette più grandi che costituiscono la base delle pale dell elica. Non sono presenti statori, in quanto gli stessi rotori della parte controrotante agiscono da statore nei confronti degli altri e viceversa. Temperatura d ingresso turbina: 710 C. Sistemi di Controllo Oltre a quelli già presenti sul motore F404 è stato aggiunto un sistema DEC (Digital Electronic Control) che provvede al controllo totale del motore monitorando la potenza del generatore di gas, la velocità del gruppo propulsore e l angolo di attaccco delle pale Velocità dei Rotori Gruppo di bassa pressione rpm Gruppo di alta pressione Elica Composta da due serie da otto pale controrotanti ad alta efficienza propulsiva, derivanti da avanzati studi sia nel campo aerodinamico che meccanico. Sono costituite da un anima in titanio ricoperto da un guscio in materiale composito. Diametro del fan 3.55m Velocità di rotazione 1393 rpm K

77 /A(B*J/ Performance Consumo specifico di carburante Rapporto mozzo-elica Carico del disco dell elica alla massima velocità di crociera (M 0.8 a metri): circa 700 kw/m^2) Spinta circa 111 kn Potenza erogata circa 11000kW In condizione di crociera kg/hn 4)'""LC="-@$01 >\(./ ***,,// LKKF!/. *;//*.,,. H, 9%,6(,LK6 (7//,(&,/##%+.G, (,,,/-/(/-,6.. /*6 L(/((8* /% 48'$89:M K

78 /A(B*J/ 44$G$-##0$"$1 /,,., dd6 0/.. / (*%,, B U X ,,/ * 8.% // -,/ 0 1, // +L#% +L#6 */2 6( 8-6,*,6**,/,/ /* % 4B'$78/<G 06.,( ( 8, ( -,/6.7, ). #. (/ /,, /.6. 6 / (, //((,/(%@.6(6 (,, +%L#dd+B,/, '9) L/ -, % K