NASA Technical Memorandum 83741 1' I' 3 Energy Efficient Engine Program Contributions to Aircraft Fuel Conservation Peter G. Batterton Lewis Research Center Cleveland, Ohio Prepared for the Aviation Fuel Conservation Symposium sponsored by the Federal Aviation Administration Washington, D.C., September 10-1 1, 1984 https://ntrs.nasa.gov/search.jsp?R=19840021807 2018-05-22T11:30:15+00:00Z
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1' Contributions to Aircraft Fuel Conservation - · PDF fileENERGY EFFICIENT ENGINE PROGRAM CONTRIBUTIONS TO AIRCRAFT FUEL CONSERVATION by Peter G. Batterton National Aeronautics and
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NASA Technical Memorandum 83741
1'
I'
3
Energy Efficient Engine Program Contributions to Aircraft Fuel Conservation
Peter G. Batterton Lewis Research Center Cleveland, Ohio
Prepared for the Aviation Fuel Conservation Symposium sponsored by the Federal Aviation Administration Washington, D.C., September 10-1 1, 1984
each year. (Currently more than 38 billion liters (10 billion
gallons) of jet fuel are burned each year.)
reduction in direct operating cost would also be realized
A ten percent
along with acoustic and environmental improvements.
The fuel savings are achieved through the four main areas
shown in the pie chart in figure 10. Improved components
using advanced aerodynauics, active clearar.2.e control, reduced
gas-path leakage, higher temperature materials, and reduced
cooling flows account for about half of the fuel savings. The
higher pressure, temperature, and bypass ratio cycle accounts
for approximately a quarter of the benefit. The efficient
10
m i x e d f low exhaust a c c o u n t s f o r abou t a f i f t h and t h e improved
n a c e l l e i n s t a l l a t i o n , the remainder .
TECHNOLOGY APPLICATION
A s t h e EEE program was p r o g r e s s i n g , b o t h General E l e c t r i c
and P r a t t & Whitney saw immediate b e n e f i t f o r t h e EEE
t echno logy . So even b e f o r e t h e EEE c o n t r a c t s are o f f i c i a l l y
comple te , w e f i n d a p p l i c a t i o n of t h e EEE t e c h n o l o g i e s
o c c u r i n g . Without g e t t i n g i n t o s p e c i f i c d e t a i l s , f i g u r e 11
i n d i c a t e s t h e numbers of technology a p p l i c a t i o n s as a p p l i e d t o
new and d e r i v a t i v e h igh bypass t u r b o f a n s of both companies.
What c o u n t s as a technology f o r f i g u r e 11 would be items l i k e
f a n and compressor t i p t r e n c h e s , h igh compressor b l a d e
l o a d i n g , improved compressor aerodynamic d e s i g n t o o l s ,
compressor vane uncambering a t endwa l l s , e t c . T a b l e s I and I1
p r o v i d e t h e complete l i s t t h a t went i n t o f i g u r e 11.
I t can be c la imed % h a t approx ima te ly half of the f u e l
s a v i n g s b e n e f i t s of t h e PW2037 are a t t r i b u t a b l e t o t h e EEE
program. A s bo th companies deve lop e n g i n e s such as t h e PW4000
and t h e CF6-80C2, s u b s t a n t i a l p o r t i o n s of t h e i r f u e l s a v i n g s
b e n e f i t s can be a t t r i b u t e d t o t echno logy developments
i n i t i a t e d by t h e EEE. Genera l E l e c t r i c has a l s o i d e n t i f i e d a
s u b s t a n t i a l number of t e c h n o l o g i e s t h a t are a p p r o p r i a t e f o r
t h e i r m i l i t a r y p r o d u c t s and are i n c o r p o r a t i n g them.
THE FUTURE
When funds were r e s t o r e d i n 1983, it was dec ided t o u s e
some of t h e funds t o e v a l u a t e t u r b o f a n eng ine t e c h n o l o g i e s and
c y c l e s of t h e f u t u r e b u i l d i n g upon t h e EEE. The s t u d i e s would
11
have an o u t p u t similar t o t h e i n i t i a l EEE s t u d y , t h a t i s a
d e f i n i t i o n of a complete t u r b o f a n p r o p u l s i o n s y s t e m , bu t f o r
t h e y e a r s 2000-2010. The s t u d i e s would t r y t o answer i f
t u r b o f a n technology I s an area of f ~ d i m i n l s h i n g r e t u r n s " and,
i f n o t , e s t a b l i s h t h e b a s i s f o r a fol low-on program a f t e r EEE.
F i g u r e 1 2 I s t h e r e s u l t of t he Prat t & Whitney s t u d y
c a l l e d t h e "Target Engine". P r a t t & Whitney used t echno logy
e x t r a p o l a t i o n s and l i m i t e d p a r a m e t r i c c y c l e ma lyses t o a r r i v e
a t t h i s c o n c e p t u a l eng ine . The T a r g e t Engine has a
g e a r - d r i v e n swept b l a d e N 1 2 : l bypass r a t i o f a n and s e p a r a t e
f low e x h a u s t . ( A m i x e r b e n e f i t a t rn 1 2 : 1 bypass r a t i o cou ld
n o t be i d e n t i f i e d . ) The o t h e r major impact i s t h e h i g h ,
~ 6 0 : 1 , c y c l e p r e s s u r e r a t i o which r e q u i r e s small and h i g h
t e m p e r a t u r e rear s t a g e s of t he h i g h p r e s s u r e compressor .
Because of t h e Improved ( approx ima te ly one p o i n t p o l y t r o p i c )
compressor e f f i c i e n c y , on ly a modest r i se i n t u r b i n e r o t o r
i n l e t t empera tu re of approx ima te ly one hundred d e g r e e s is
r e q u i r e d .
The b a s i c t e c h n o l o g i e s r e q u i r e d are advanced, c o n t r o l l e d
d i f f u s i o n , h i g h e r e f f i c i e n c y compressor ; low p r e s s u r e drop
d i f f u s e r - c o m b u s t o r ; h i g h annulus-speed-squared , f u l l
t h ree -d imens iona l d e s i g n t u r b i n e s ; c losed - loop a c t i v e
c l e a r a n c e c o n t r o l ; composi te i n t e g r a t e d s t r u c t u r e s ; s h o r t ,
s h o c k - f r e e i n t e g r a t e d f a n cowl; a swep t , shock- f r ee f a n ; and
h i g h e f f i c i e n c y r e d u c t i o n g e a r .
When t h i s t ype of eng ine is e v a l u a t e d , t h e p o t e n t i a l f u e l
s a v i n g s i s 15.5 p e r c e n t I n c r u i s e s p e c i f i c f u e l consumption
1 2
o v e r t h e EEE. T h i s t r a n s l a t e s t o a 24 p e r c e n t s a v i n g s I n f u e l
burned f o r a 3700 km (2000 n a u t i c a l m i l e ) m i s s i o n 500
p a s s e n g e r q u a d j e t . These bene f i t s are s p l i t roughly e q u a l l y
between thermal e f f i c i e n c y improvements and p r o p u l s i v e
e f f i c i e n c y improvements. Because of t h e c o n t r i b u t i o n s of t h e
swept f a n t o the e f f i c i e n c y improvements, some p r e l i m i n a r y
d e s i g n s t u d i e s have been s tar ted u s i n g EEE f u n d s .
To pu t a l l t h e EEE and the f u t u r e i n t o one p e r s p e c t i v e ,
f i g u r e 13 is prov ided . T h i s f i g u r e shows the t r e n d of
u n i n s t a l l e d , bare s p e c i f i c f u e l consumption s t a r t i n g w i t h t h e
JT3 t y p e t u r b o j e t as a f u n c t i o n of year of i n i t i a l
c e r t i f i c a t i o n . The n e x t s p o t on the c u r v e is t h e JT3D/JT8D
t y p e e n g i n e s w i t h abou t a 15 p e r c e n t improvement. The n e x t
s p o t , t h e f i r s t JT9D/CF6 type h i g h bypass e n g i n e s , a g a i n made
a s u b s t a n t i a l improvement on the o r d e r of 19 p e r c e n t ove r the
p r e v i o u s eng ines . N e x t comes t h e PW2037 w i t h an improvement
on t h e o r d e r o f 1 2 p e r c e n t over t h e JT9D/CF6. The PW2037
r e p r e s e n t s t h e f i r s t s i g n i f i c a n t use of EEE technology.
Two s p o t s f o r EEE are shown. The h i g h e r i s a b o u t 15
p e r c e n t below the JT9D/CF6 s p o t and r e p r e s e n t s the f i n a l
r e s u l t s f o r t h e EEE FPS engines . The lower s p o t r e p r e s e n t s
a p p l i c a t i o n of EEE t e c h n o l o g i e s bu t w i t h some r e - o p t i m i z a t i o n
of t h e e n g i n e c o n f i g u r a t i o n such as the number of compressor
and t u r b i n e s t a g e s . I t is about 18 p e r c e n t below the JTgD/CF6
s p o t . The Turbofan F u t u r e P o t e n t i a l s p o t r e p r e s e n t s t h e
r e s u l t s of t h e Target Engine s t u d y j u s t shown, a g a i n showing
t h a t s u b s t a n t i a l g a i n s ere s t i l l p o s s i b l e . T h i s is v e r y
i m p o r t a n t because i t is n o t c lear t h a t t u r b o p r o p s w i l l be
a v a i l a b l e i n the h i g h t h r u s t s i z e normal ly f i l l e d by t u r b o f a n s
d u r i n g t h i s time p e r i o d .
F i n a l l y , are two s p o t s f o r advanced p ropfan t y p e
t u r b o p r o p s y s t e m s which i n c l u d e advanced t echno logy c o r e s .
The higher s p o t u s e s an EEE t echno logy c o r e and low p r e s s u r e
t u r b i n e and t h e lower s p o t u s e s the advanced Target Engine
c o r e and low p r e s s u r e t u r b i n e t e c h n o l o g i e s . Thus even t h e
propfan g a i n s s u b s t a n t i a l l y from t u r b o f a n c o r e technology
developments .
C ONC LU S I ON S
The EEE program was h i g h l y s u c c e s s f u l and p r o v i d e s an
e x c e l l e n t technology base f o r much improved t u r b o f a n e n g i n e
f u e l e f f i c i e n c y . As a r e s u l t , bo th Genera l E l e c t r i c and P r a t t
& Whitney a r e r a p i d l y t r a n s l a t i n g these t e c h n o l o g i e s i n t o
t h e i r p roduc t s making the EEE program a g r e a t s u c c e s s .
Although no f u n d i n g has been i d e n t i f i e d , a fo l low-on
t u r b o f a n r e s e a r c h program cou ld o b t a i n s u b s t a n t i a l a d d i t i o n a l
f u e l s a v i n g s b e n e f i t s .
would have d i r e c t a p p l i c a t i o n t o p r o p f a n t u r b o p r o p p r o p u l s i o n
s y s t e m s p r o v i d i n g s u b s t a n t i a l b e n e f i t t o them a l s o .
The c o r e p o r t i o n of these t e c h n o l o g i e s
14
TABLE I
PW E3 TECHNOLOGIES - APPLICATION TO COMMERCIAL ENGINES
TECHNOLOGY -
:OMPRESSOR INTERMEDIATE CASE WITH THROUGH STRUTS
:AN AND COMPRESSOR T I P TRENCHES
(EDUCED LPC INNER CAVITY VOLUMES
.ow CXIU L c )RUM COMPRESSOR ROTORS WITH INTEGRAL KNIFE EDGES
:OMPRESSOR A IRFOILS WITH ELL IPT ICAL LEADING EDGE
I I N I SHROUDED HPC
MUBLE WALL COMPRESSOR ACTIVE CLEARANCE CONTROL
:ONTROLLED DIFFUSION COMPRESSOR A IRFOILS
[NCREASED COMPRESSOR STAGE LOADINGS
rANGENTIAL COMPRESSOR BLADE ATTACHMENTS
:ANTED COMPRESSOR EXIST GUIDE VANE/DIFFUSER
rwo BEARING HIGH SPOOL WITH DAMPING AND SPRINGS
ION-METALLIC TURBINE OUTER AIRSEAL
%LL RING TURBINE SIDEPLATES
IMPROVED TURBINE FEATHERSEAL SLOTS
MERMAL BARRIER COATING ON TURBINE VANE PLATFORM
IMPROVED GASPATH STATIC SEALS
rURBINE A IRFOIL INTERNAL TRIP STRIPS
rURBINE A IRFOIL INTERNAL TURNING VANES
3-D DESIGN TURBINE VANES
[MPROVED SUCTION SIDE F I L M COOLING
i I G H AN2 TURBINE
r H I N TURBINE A IRFOIL TRAILING EDGES
i I G H STAGE LOADING TURBINE AIRFOILS
U G H REACTION HP TURBINE
LOW CX/U TURBINE
TURBINE A IRFOILS WITH ELLIPTICAL LEADING EDGES
TWIST RESTRAINED HP TURBINE VANES
BOLTLESS TURBINE DISK SIDE PLATE
LP TURBINE FLOW GUIDES
LOW LOSS CONTOUR TURBINE EXIT GUIDE VANE
THREE BEARING LOW SPOOL
IT9D-7R4 PW2037 e_
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
PW4000
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
X
TABLE I 1
6E E 3 TECHNOLOGIES - APPLICATION TO COMMERCIAL/MILITARY ENGINES
TECHNOLOGY
IMPROVED COMPRESSOR AERODYNAMIC DESIGN TOOLS
:OMPRESSOR VANE UNCAMBERING AT ENDWALLS
IMPROVED BETWEEN SHINGLE SEALS FOR SHINGLE COMBUSTOR LINERS
tEDUCE0 THROUGH-FLOW VELOCITY HP TURBINE DESIGN
YIGH STAGE REACTION HP TURBINE
IMPROVED HP TURBINE FLOWPATH OVERLAPS
HP TURBINE CONVERGED STATOR BANDS
HP TURBINE IMPROVED A IRFOIL SURFACE VELOCITY DISTRIBUTIONS
CERAMIC HP TURBINE SHROUDS
LIGHTWEIGHT RADIAL STRUTTED TURBINE FRAME WITH POLYGONAL CASING
IMPROVED LP TURBINE FLOWPATH OVERLAP:
IMPROVED LP TURBINE A IRFOIL SURFACE VELOC ITY DISTRIBUTIONS
FADEC FAULT INDICATION AND CORRECTIVE ACTION SYSTEM
F6-80C2 'FM 56-3
- 110 -
X
X
X
-
- I\OWTH
-
X
X
X
X
X
-
16
REFERENCES
1.
2.
3 .
4.
5.
6.
7.
ETHELL, J. L. (19831, Fuel Economy In Aviation, NASA
SP-462
JOHNSTON, R. P., et. al. (19801, Energy Efficient Engine - Flight Propulsion System Preliminary Analysis and Design
(General Electric), NASA CR-159583
GARDNER, W. B. (19791, Energy Efficient Engine - Flight Propulsion System Preliminary Analysis and Design (Pratt &
Whitney), NASA CR-159487
SULLIVAN, T. J. and HAGER, R. D. (1983), The Aerodynamic
Design and Performance of the General Electric/NASA E3
- Fan, AIAA-83-1160
GARDNER, W. B. (1982), Energy Efficient Engine (E3)
Technology Status, AIAA-82-1052
BEITLER, R. S., SAUNDERS, A. A., and WANGER, R. P. (1980),
Fuel Conservation Through Active Control of Rotor
Clearances, AIAA-80-1087
KUCHAR, A. P., and CHAMBERLIN, R. (19841, Comparison of
Full-scale Engine and Subscale Model Performance of a
Mixed Flow Exhaust System for an Energy Efficient Engine
Propulsion System, AIAA-84-0283
Figure 1. - Overview of aircraft energy efficiency program.
PROPULSION SYSTEM DEFINITION (Ir UPDATES
COMPONENT TECHNOLOGIES
SYSTEMS INTEGRATION TECHNOLOGIES
CALENDAR YEAR 77 I 78 I 79 [ 80 I 81 I 82 I 83 I 84 I 85
’ FLIGHT PROPULSiON SYSTEM DESIGN I I I I I I
ICLS - INTEGRATED COREILOW SPOOL GENERAL ELECTRIC
0 PRATT (IrWHITNEY
Figure 2. - Energy eff icient engine program.
I- TWO-ZONE COMBUSTOR I/4-STAGE ISLAND BOOSTER7 \ \ 1 rFIVE-STAGE L. P. TURBINE SINGLE-STAGE FAN 7
I \ I \ I ' \
\
; TEN-STAGE H. P. COMPRESSORJ
LlWO-STAGE H. P. TURBINE CS-80-2098
Figure 3. - Energy efficient engine, General Electric configuration.
FOUR-STAGC L P. COMPRESSOR1 I I I SINGLE-STAGE FAN 7 I I 1
,-TWO-ZONE COMBUSTOR
I ,-FOUR-STAGE L. P. TURBINE I ,-MIXER
I t ! !
f
TEN-STAGE H. P. COMPRESSOR' SINGLE-STAGE H. P. TURBINE c s -80-2099
Figure 4 - Energy efficient engine, Pratt & Whitney configuration.
32 BLADE / 6.8 BYPASS RATIO / 1.65 PRESSURE RATIO 0.55 SPAN, AFT MOUNTED LOW LOSS SHROUD 89.2 BYPASS, 89.5 CORE EFFICIENCY QUARTER STAGE BOOSTER I FOD SEPERATION INTEGRAL STATOR-FAN FRAME / WIDE ROTOR-STATOR SPACING
Figure 5. - EEE fan technology.
(a) General Electric. 10-stage; 23: 1 pressure ratio; High speed, endbend treatment; 90.5 poly. eff.
(b) Pratt & Whitney. 10-stage; 14: 1 pressure ratio; High loading control led dif fusion;
Figure 6. - EEE compressor technology; Active and passive clearance contro l ; short, stiff
91.5 poly. eff.
rotor; low aspect rat io blades.
i
. . . .
GE
P & W
r g 3.0
RATIO
Ln a
PHASE
GE P&w m PHASE
iii MID 70’s 1978 1980 1981183
TECHNOLOGY READINESS
FEATURES GE P & W NEW E3 TECHNOLOGY 0 NUMBER OF LOBES 18 18 0 SHORT EFFICIENT MIXERS COMBINING
PENETRATION, % 45 15 HIGH MIXING EFFECTIVENESS WITH LCVY 0 MIXING LENGTH, L ID .52 .61 PRESSURE LOSS 0 MIXING EFFECTIVENESS, % 79 85 0 MIXERS AT HIGH BYPASS RATIOS
0 REDUCED WEIGHT MIXER DESIGNS
Figure 8. - EEE exhaust mixer technology.
Figure 9. - EEE experimental engine o n test stand.
REFERENCE ENGINE
OPR: 25-30 BPR. 4.3.5.3
T (SLTO1' 2300~2400'F
I I " I I
ENERGY EFFICIENT ENGINE 18% FUEL SAVINGS
OPR 36-37 BPR: 6 6 - 6 8
1 (SLTO)' 2450 - 250dF
SOURCES OF FUEL SAVINGS
IMPROVED COMPONENTS -, ,- IMPROVED CYCLE
I HIGHER BYPASS RATIO I HIGHER TEMPERATURES
,/ HIGHER PRESSURE RATIO ADVANCED AERODYNAMICS .\ ACTIVE CLEARANCE CONTROL REDUCED GAS-PATH LEAKAGE HIGHER TEMPERATURE MATERIALS REDUCED COOLING
Figure 12. -Advanced turbofan research requirements and benefits. Potential fuel savings w e r EEE -15.5% SFC, -24% fuel burned.
Figure 13. -Turbofan technology trend.
1. Report No. NASA TM-83741
2. Government Accession No. 3. Recipient's Catalog No.
17. Key Words (Suggested by Author(s) ) Energy Conservat ion Subsonic T r a n s p o r t Turb ine Engine A i r c r a f t Tu rb ine Engine Energy E f f i c i e n t Engine
4. Title and Subtitle Energy E f f i c i e n t Engine Program C o n t r i b u t i o n s t o A i r c r a f t Fuel
Conserva t i on
18. Distribution Statement
5. Report Date
6. Performing Organization Code
505-40-12C
U n c l a s s i f i e d - u n l i m i t e d STAR Category 07
7. Author(s)
P e t e r G. B a t t e r t o n
9. Performing Organization Name and Address
N a t i o n a l Ae ronau t i cs and Space A d m i n i s t r a t i o n Lewis Research Center Cleveland, Ohio 44135
12. Sponsoring Agency Name and Address
N a t i o n a l Ae ronau t i cs and Space A d m i n i s t r a t i o n Washington, D.C. 20546
8. Performing Organization Report No.
E-2226 10. Work Unit No.
11. Contract or Grant No.
13. Type of Report and Period Covered
Techn ica l Memorandum 14. Sponsoring Agency Code
* For sale by the National Technical Information Service, Springfield, Virginia 22161
19. Security Classif. (of this report)
U n c l a s s i f i e d 20. Security Classif. (of this page) 21. NO. of Pages 22. Rice'