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-.
I
N A S A Contractor Report 4 33
I
An
timisting
Fuel System
Kerosene
JT3 Engine
Integration Study
A.
Fiorentino
CONTK CIb N A b3 - 2 4 2 17, N A S3 - 2 4 3 5 3 ,
and D T F A 03-8 1-A-001 54
J A N U A R Y 1987
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PREFACE
T h i s r e p o r t d e s c r i b e s th e work c o n du c te d by t h e P r a t t 8 W h i tn e y E n g i n e e r i n g
D i v i s i o n
o f
U n i t e d T e c h n ol o gi e s C o r p o r a t i o n t o a s s i s t NASA Ames-Dryden F l igh t
Research F a c i l i t y i n t h e i r p r ep a ra t io n for t h e F u l l - s c a l e T r a n s p o r t C o n t r o l l e d
I m p a c t D e m o n s t r a t i o n T e s t .
T h i s e f f o r t was s po n so re d b y t h e N a t i o n a l
Ae ro na ut i cs and Space A d m in is t r a t i o n under Co nt ra c t s NAS3-24217 and NAS3-24353
and f unded by t he
F A A
t h rough I n te ragency Ag reemen t No.
DTFA03-81-A-00154.
The au thor w ishes t o acknowledge the gu idance o f
M r . L .
Dean Webb o f N A S A
Am es-Dryden F l i g h t R e s ea rc h F a c i l i t y whose k ee n i n t e r e s t a nd s u p p o r t we re
p a r t i c u l a r l y i n s t r u m e n t a l
i n t h e s u c c e ss fu l c o m p l e t io n of t h i s s u p p o r t p r o g r a m .
m m AGE BLANK
NOT FILMED
iii
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TABLE OF
C O N T E N T S
S e c t i n
P R E F A C E
SUMMARY
I N T R O D U C T I O N
E Q U I P M E N T
AND PROCEDURES
E n g i n e D e s c r i p t i o n
Engine Fuel System
Fuel Pump
F u e l C o n t r o l
Fuel F i l t e r Systems
Combu
s
t o r
De
s
c
r
i
t
i
n
E ng in e M o d i f i c a t i o n s f o r
AMK
B-720 F l i g h t T e s t E ng in es
F A A Techn ica l Center Ground T e s t Engine
L a b o r a t o r y
F1
ow Ch ar ac te r i za t i o n Equi pmen
t
Fue l
S y s t e m
a n d E n g i n e O p e r a b i l i t y
F u e l C h a r a c t e r i z a t i o n T e s ts an d A n a ly s e s
Engine Per formance
RESULTS
AND
D I S C U S S I O N
CONCLUDING
REMARKS
A P P E N D I C E S
Appendix
A
JT3C-7 Engine
Appendix B-1
Appendix 8-2
Appendix C
Procedure
f o r
D e te rm i ni ng F i l t e r R a t i o
Procedure for D e t e r m i n in g t h e T r a n s i t i o n
V e l o c i t y A Measure
o f
AMK D e g r a da t i on L e v e l )
T r a n s i t i o n V e l o c i t y and F i l t e r R a t i o A pp ar at us
REFERENCES
i v
Page
iii
1
1
2
2
4
4
4
9
9
10
10
17
20
20
20
23
27
31
32
38
40
42
1
43
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SUMMARY
An a n a l y t i c a l s t u d y and l a b o r a t o r y t e s t s w e r e conduc ted
t o
a s s i s t NASA i n
d e te r m in i ng t h e s a f e t y and m is s io n s u i t a b i l i t y
o f
t h e m o d i f i e d f u e l s y st em and
f l i g h t t e s t s fo r t h e F u l l - s c a l e T r a n s p o r t C o n t r o l l e d I m p ac t D e m o s t ra t i on ( C I D )
Program. Th is 12 month s tu dy rev iewe d and ana lyz ed bo th the use of a n t i m i s t i n g
kerosene ( A M K ) f u e l a n d t h e i n c o r p o r a t i o n o f a " f u e l d e g r a d er " o n t h e o p e ra -
t i o n a l a nd p e rf or m an ce c h a r a c t e r i s t i c s o f t he e n gi ne s t e s t e d . P o t e n t i a l
d e f i c i e n c i e s a n d / o r f a i l u r e s w ere i d e n t i f i e d and a pp ro ac he s to accommodate
t h e s e d e f i c i e n c i e s w e r e recommended t o NASA Ames-Dryden F l i g h t Research
F a c i 1
i
y .
T h e r e s u l t s o f f l o w c h a r a c t e r i z a t i o n t e s t s on degraded AMK f u e l s a m p l e s
i n d i c a t e d l e v e l s o f d e g r a d a t i o n s a t i s f a c t o r y fo r t h e p l a n n e d m i s s i o n s o f t h e
6-720 a i r c r a f t . The o p e r a b i l i t y and pe rf or ma nc e w i t h t h e
AMK
i n a g ro un d t e s t
e ng in e and i n t h e a i r c r a f t e n gin es d u r i n g t he t e s t f l i g h t s were c om parab le t o
t ho se w i t h u n m o d i f ie d J e t A . For t he f i n a l
C I D
t e s t , t he JT3C-7 eng ines
p er fo rm ed s a t i s f a c t o r i l y w h i l e o p e r a t i n g on AMK r i g h t up t o i m p a c t .
I N T R O D U C T I O N
I n
a
t y p i c a l a i r c r a f t c ra sh , f u e l s p i l l e d f rom r u p t u r e d f u e l t an ks forms a
f i n e m i s t w h ic h can be i g n i t e d by a number o f s ou rc es a t t h e c ra s h s i t e .
I f
f o r m a t i o n
o f
t h i s m i s t can be suppressed, f i r e hazards can be reduced and
l i v e s can be saved. FM-9, a h ig h mo lecu la r -w e igh t , l o ng ch a i n po lym er , when
b le n de d w i t h J et -A f u e l i n c o n c e n t r a t i o n s i n t h e ra ng e
o f 0.3
p e r c e n t b y
w e ig h t, ha s d em o ns tr at ed t h e a b i l i t y t o i n h i b i t
i g n i t i o n and f la me p r o p a g a t io n
o f
t h e r e l e a s e d f u e l i n s i m u la t e d cr as h
t e s t s .
T h i s a n t i m i s t i n g ke ro se ne (AMK), when subjected t o t h e s h ea r l e v e l s e x p ec t ed
i n a i r c r a f t e ng i n e sy st em s, c an ha ve u n d e s i r a b l e f l o w c h a r a c t e r i s t i c s s u c h a s
p oo r f u e l a t o m iz a t io n and f i l t e r a b i l i t y . Th is p r ec lu d es
i t s
d i r e c t use i n a
g as t u r b i n e e n g i n e b e ca us e
o f
p o s s i b l e c l o g g i n g
o f
f i l t e r s , u n a c c e p t a b l e s p r a y
q u a l i t y
o f
f u e l n o z z l e s / i n j e c t o r s and redu ced h e a t t r a n s f e r c o e f f i c i e n t s i n
f u e l hea t exchange rs (Re f . 1 ) . The re fo re , t he
AMK
f u e l m u st be a l t e r e d
t o
r e s t o r e
i t s
p a r e n t J et -A p r o p e r t i e s for p ro pe r o p e r a t i o n i n t h e e n gi ne f u e l
system.
F u el a l t e r a t i o n c an be a c co mp li sh ed b y t h e a p p l i c a t i o n o f s u f f i c i e n t m o l e c u l a r
s t r e s s
t o
r u p t u r e t h e p o l y m er i c a d d i t i v e c on ta in ed i n t h e AMK. T h i s p r o c e s s o r
a l t e r a t i o n
of
t h e
AMK
f u e l
i s
r e f e r r e d
t o
as " de g ra da t i on " . The t e ch n i ca l
f e a s i b i 1
i
y o f d e v i c e s d e s i g n a t e d " de g r ad e r s" w h i c h u t i 1 i z e e i t h e r m e c h a n
or
c a v i t a t i o n p r i n c i p l e s ha s been de mo ns tra te d ( R e f s.
1 ,
2,
3 ) .
Th i s r e p o r t documen ts a twe lve -mon th
AMK
E ng in e S ys te m I n t e g r a t i o n s t u d y
e v a l u a t e d t h e u s e o f a n t i m i s t i n a k er os e ne and t h e i n c o r p o r a t i o n o f a " fue
c a l
h a t
d e g ra d e r" o n t h e b e r f o r m a n c e , re1 a b i 1i y and s a f e t y
o f
t he P r a t t & Whi tney
JT3C-7 engines for s h o r t d u r a t i o n f l i g h t s o f a B-720
t e s t
a i r p l a n e d u r i n g t h e
F u l l - S c a l e T r a n s p o r t C o n t r o l l e d I m p ac t D e m o ns t ra t io n ( C I D ) P ro gra m h e l d a t t h e
D ry de n F l i g h t R e se ar ch
F a c i l i t y
o f
t h e NASA Ames Research Ce nte r . T hi s s tu dy
was co nd uc ted und er co n t r a c t s NAS3-24217 and NAS3-24353 and fo cu se d on two
1
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7/17/2019 An timisting Fuel System Kerosene JT3 Engine Integration Study
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major a reas of a c t i v i t y : T a s k
I-
y st em I n t e g r a t i o n St u dy a n d Ta sk
I 1 -
Des ign
R ev ie ws and F l i g h t T e s t P l a n n i n g .
I n Task
I f
th e program, a rev ie w and an a ly s i s were made
o f
the JT3C-7 AMK
eng ine f ue l system wh i ch i nc l ud ed t h e deg rade r system, hea t exchange rs , eng ine
f u e l pump and f i l t e r s , f u e l c o n t r o l s a nd t h e r e s u l t i n g o p e r a t i o n a l a nd
p er fo rm an ce c h a r a c t e r i s t i c s o f t h e e n g i n e s . T he 8-720 i n s t r u m e n t a t i o n was
re vi ew ed and recommendations were made for a d d i t i o n a l d e g r a d e r a n d e n g i n e
i n s t r u m e n t a t i o n
t o
i d e n t i f y p ro b le m s t h a t may o c c u r .
As
p a r t o f the Task I
f f o r t ,
l a b o r a t o r y f u e l c h a r a c t e r i z a t i o n t e s t s were
conduc ted
t o
de te rm ine whe the r t he AMK f u e l was s u f f i c i e n t l y pr oc e ss ed or
d e g r a d e d b e f o r e i n t r o d u c t i o n to t h e e ng i ne f u e l s ys te m. These f u e l c h a r a c t e r i -
z a t i o n
t e s t s
c o n s i s t e d o f f i l t e r r a t i o a nd t r a n s i t i o n v e l o c i t y m easurements
w hich p ro v id e d a c o r r e l a t i o n w i t h t h e f i l t e r s , f u e l n o z z l e s / i n j e c to r s ,
c om b us to r p e rf o rm a n c e, e t c . , p r e v i o u s l y e v a l u a t e d un d e r NASA C o n t r a c t
NAS3-22045 ( R e f .
1
)
.
I n Task 11, P r a t t
&
W hitn ey p a r t i c i p a t e d i n d e si g n re v i ew s and t e s t p l a n ni n g .
A
majo r bu t necessa ry gene ra l
e f f o r t was t h e a s s i s t a n c e r en d er e d t o
NASA
Ames-Dryden F l i g h t R ese arch F a c i l i t y i n t h e p l a n n i n g and i n s t a l l a t i o n o f b o t h
i n s t r u m e n t a t i o n and m o d i f i c a t i o n s
t o
t h e e n g i n e f u e l s ys te m f o r s t r u c t u r a l a n d
o p e r a t i o n a l c o n s i d e ra t i on s . T h is a c t i v i t y i n v o l v e d c o n s u l t a t i o n w i t h v e nd or s,
procurement of p r i n t s , s ch em at ic s and p a r t s , s e v er a l v i s i t s
t o
N A S A Ames-Dryden
F l i g h t Research F a c i l i t y and d i a lo g u e w i t h
NASA
Ames-Dryden F l i g h t Research
F a c i l i t y on a lm os t a d a i l y b a s i s .
T h i s r e p o r t d e s c r i b e s t h e b a s e l i n e JT3C-7 e n gi n e and i t s m o d i f i c a t i o n s
f o r
t h e
use o f AMK. T h e l e v e l s
o f
d e g r a d a t i o n a d e q u a t e f o r o p e r a b i l i t y i n t h e t e s t
a i r p l an e a re i d e n t i f i e d
f rom
f u e l c h a r a c t e r i z a t io n t e s t s . F i n a l l y , e ng in e
pe r fo rmance w i t h AMK d u r i n g t he se g ro un d and f l i g h t t e s t s
i s compared
t o
t h e
b a s e l i n e sea l e v e l p e r f or m a nc e e xp e c t ed w i t h J e t A .
EQUIPMENT
AND
PROCEDURES
T h i s
se c t i on des c r i b es t h e JT3C-7 eng ine and i t s components wh i ch wou ld be
a f f e c t e d
by
t he use
o f
a n t i m i s t i n g k ero se ne f u e l . I n a d d i t i o n , m o d i f i ca t i o n s
t o t h e b i l l - o f - m a t e r i a l e n gi n e f u e l s ys te m an d s p e c i a l t e s t e q ui pm e nt u se d
t o
a n a ly z e t h e a n t i m i s t i n g ke ro se n e w i l l
be d i scussed .
E N G I N E D E S C R I P T I O N
Four Pr a t t and Whi tney JT3C-7 eng ine s powered the C I D B-720-027(S/N 18066)
t e s t a i r p l a n e . The JT3C-7 e n g in e d e p i c t e d s c h e m a t i c a l l y i n F i g u r e
1
and
i l l u s t r a t e d i n d e t a i l i n Appendix A r e p r e s e n t s f i r s t - g e n e r a t i o n co mm ercia l
t r a n s p o r t t ec h n o lo g y . T h i s e n gi n e i s a d ua l- sp oo l, a x i a l - f l o w t u r b o j e t , w i t h a
16-stage compressor,
a c o - a nn u l a r c o m b u s ti o n s e c t i o n a nd a 3 - st a ge t u r b i n e . I n
t h e Bo ein g 7 20 a i rf r am e i n s t a l l a t i o n ,
t h e e n g in e i s 1 1. 4 f t l o n g ,
38 .9 i nches
i n d i ame te r and we ighs
3495 pounds. Key sp ec i f i c a t i o ns for t h i s e n gi ne a r e
shown i n Tab le I.
2
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ORIGINAL
PAGE
IS
OF P O O R
QUALITY
I
V
m
I--
cc
W
>
C
rd
c
.-
v
W
I/
I
V
3
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TABLE
I
S P E C I F I C A T I O N S OF T HE JT3C-7 E N G I N E
T ak e- of f R a t in g ( a t sea l e v e l )
Maximum C o nt in u ou s R a t i n g ( a t s ea l e v e l )
Maximum S pe c i f i c Fue l Consumption
T o t a l
A i r f low
P r e s s u r e R a t i o
Dry
Weight
Engi ne Diamete r
Engine Length
12,000 l b . t h r u s t
10,000 l b . t h r u s t
.785 p p h l l b . t h r u s t
182 pps
13.0
3495 lbs .
38 .9 inches
11 .4
f t
Engine Fue l
S y s t e m
T h e p r i n c i p a l f u n c t i o n
o f
t h e a i r c r a f t f u e l system
i s
to s up p ly c l ea n l i q u i d
f u e l , f r e e
from
v ap o r, a t t h e r e q u i r e d p r e s s u r e s and r a t e s
o f
f l o w ,
t o
t h e
e n g i ne und er a l l o p e r a t i n g c o n d i t i o n s . F i g u r e 2 shows t h e b a s i c JT3C-7 f u e l
sys tem for a c om me rc ia l i n s t a l l a t i o n . F u e l
i s
s u p p l i e d f rom t he a i r c r a f t t an ks
t h r o u g h t h e n e c e s s a r y
f i l t e r s
a n d v a l v e s
t o
t h e e n g i n e - d r i v e n f u e l
pump which
i s a t wo -s ta ge , b y-p as s e q u i pp e d u n i t t h a t di s c h a r g e s f u e l
a t p r e de t e rm i n e d
p r e ss u r es and q u a n t i t i e s t h r o u g h a f u e l d e - i c i n g s ys te m ( c us t om e r o p t i o n a l )
t o
t h e f u e l c o n t r o l . T he f u e l d e - i c i n g f i l t e r a ss em bly c o n s i s t s o f a
40
m i c r o n
paper
f i l t e r
e le men t en cl os ed i n a c y l i n d r i c a l h ou si ng . A f t e r p r e s s u r i z a t i o n ,
t h e f u e l p a s s e s
t o
t h e f u e l c o n t r o l t h ro u gh a c oa rs e mesh i n l e t f i l t e r . The
f u e l c o n t r o l
i s
a h y d ro m e ch a n ic a l f u e l m e t e r i n g d e v ic e d e s i g n e d t o s c h e d u l e
t h e p r o p e r
f l o w o f
f u e l
t o
m a i n t a i n t h e e n g i n e s p e e d s e l e c t e d . T h e m e t e r e d
f u e l f lows t hro ug h th e a i r c r a f t f u e l - o i l
c o o l e r
t o
t h e p r e s s u r i z i n g a n d d u m p
v a l v e w h i c h s c h e d u l e s f l o w
t o
t h e f u e l n o z z l e s ec on da ry m a n i f o l d as a f u n c t i o n
o f p r i m a r y f u e l n o z z l e p r e s s u r e d r o p. T h i s e n su re s t h e p r o p e r f u e l s p r ay
q u a l i t y and d i s t r i b u t i o n
f o r
e f f i c i e n t c om b us ti on . The f u e l m a n i f o l d c o n s i s t s
o f e i g h t c i r c u l a r c l u s t e r s , each c l u s t e r h a v in g
s i x
d ua l o r i f i c e no z z l e s,
l o c a t e d i n t h e d i f f u s e r c ase a n nu lu s. The f u e l i s i n j e c t e d t h ro u g h each
c l u s t e r i n t o each
o f
e igh t combus t ion chambers where
i t m i x e s
w i t h a i r and
b u r n s .
Fuel Pump
-
The m a in f u e l pump ( F i g u r e 3 ) c o n s i s t s
o f
two p o s i t i v e d i s p l a c e m e n t
g e a r -t y p e p um pin g e le me nt s ( b o o s t s t a ge a n d m ai n s t a g e ) o p e r a t i n g i n s e r i e s t o
s u p p l y f u e l
t o
t h e e ng in e f u e l c o n t r o l . Power t o d r i v e t h e pump i s s u pp l ed
d i r e c t l y by t h e m ain d r i v e s h a f t . U nder no rm al o p e r a t i n g c o n d i t i o n s , f u e l f l ows
t h r o u g h
t h e
pump
f rom
t h e f u e l i n p o r t t o t h e i n l e t f u e l f i l t e r e lem e n t
c o n t a i n i n g a
s e l f - r e l i e v i n g v a l v e to t h e b o o s t s t a g e . B et we en t h e b o o s t a n d
m ain stage i s t h e i n t e r s t a g e 40 m i c ro n p l e a t e d p ap er f i l t e r and o p t i o n a l
de- icer sys tem.
The bo o st s t ag e p r e s s u r e r e g u l a t i n g v a l v e c o n t r o l s t h e p r e s s u r e
o f
t h e f u e l d e l i v e r e d
to
t h e m a i n s ta g e i n l e t a t b et we en 45 a nd 65 p s i a b ov e
pump i n l e t pr e s s u r e . The r a t e d c a p a c i t y of th e pump i s 41.6 gpm a t 3260 rpm
and a d i scharge p ressu re
o f
1 0 0 0 p s i g .
Fue l Con t ro l
-
The H a m i l t o n S t a n d a r d JFC25-10 f u e l c o n t r o l ( F i g u r e 4 )
i s
a
h y dr o me c ha n ic a l h i g h c a p a c i t y f u e l
f low
m e t e r i n g u n i t d es ig ne d
to
p e r m i t
s e l e c t i o n o f t he d e s i r e d e ng in e t h r u s t l e v e l t hr ou gh ou t t h e f l i g h t en ve lo pe
o f
4
I
~
I
I
I
I
I
I
i
I
I
i
I
i
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ORIGINAL
PAGE
IS
OF
POOR
QUALITY
T H I S P A S S A O C
L O C K C D
WNEU
O C T I W A L C U L
H L A l L R
USED-
ENGINE WCCLICD
A I R r R A U C
SUPPLIED
FUEL-OIL COOLER
OPTIONAL EQUIP
OPTIONAL
---
C W l P Y C M l 1
I
IR CONTROL
VALYC
a
I I I
I ' I
OVCRBOARO
I
i
r
C YC R G C U C V
CUCL
SHUT-WC
VALVES
L
Figure
2 B a s i c
JT3C-7 Fuel System
5
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PUMP INLET PRESSURE
I 1 UMP
BOOST
PRESSURE
-
UMP OUTLET PRESSURE
MAIN DRAIN
F i g u r e
3
Two-Stage
Main
Fuel Pump
6
ORIGINAL
PAGE
IS
OF
POOR QUALITY
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ORIGIN L PAGE
IS
O POOR QUALITY
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t he J T3C- 7 e ng i ne equi pped ai r c ra f t . Two manua l l y ope ra t e d l e ve rs a r e pr ovi ded
on each cont r ol : a power l ever f or r egul a t i ng e ng i ne t hr us t i n t he r ange f r om
ful l
r ever se t hr ough i dl e
t o
t akeof f ; t he o t h er , a shut o f f l ever t o r egul at e
f uel f o r engi ne s t a r t i ng and shut down. The var i abl e s se nse d
by
t he f uel c ont r ol
ar e power l ever ang l e , bur ner pr essur e and engi ne
N Z
r ot or s peed. By ut i l i z -
i ng t hes e v ar i a bl es , t he f uel c ont r ol a c c ur a t e l y go ve r n s t he engi ne s t ea dy
s t a t e s el ec t ed s peed and l i m t s f uel f l o w f or a cc el er at i o n and dec el er a t i o n
t hr ough a speed- governi ng sys t em of t he pr opor t i onal o r dr o op t y pe.
.
f
T
The f uel cont r ol may be cons i dered as cons i s t i ng of a f uel - met er i ng s y s t em and
a comput i ng syst em
The met e r i ng sys t e m r e gul a t es t he f uel suppl i e d t o t he
f uel c ont r o l
by
t he eng i ne dr i ven f uel pump t o prov i de t he eng i ne t h rust
out put demanded by t he p i l ot , but s ubj ec t t o engi ne oper at i ng l i m t at i ons as
sensed and schedul ed by t he f uel cont r ol comput i ng sys t em The comput i ng sys t em
senses and combi nes var i ous oper at i ona l par amet er s t o gover n t he out put of t he
met er i ng syst em
of
t he f uel c ont r ol dur i ng al l e ngi ne o pe r a t i ng r egi mes .
F i gur e
5
i ndi cat es t he f uel cont r o l pa ramet er s
and
schedul i ng accur acy
r equi r ement s f or t hese par amet er s .
'2.5
SPEED GOVERNOR
DECELERATION SCHEDULEI
T
~~ ~ ~
ENGINE HIGH
ROTOR
SPEED, N2 RPM
F i gur e
5
J T3C 7
Fuel Cont r o l Schedu l i ng Accur acy Requi r ement s
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f i l
i
ng
f
ue
The
J T3C 7
combus t o r sec t i on cons i s t s
of
ei ght separ at e t ubu l ar combust i on
chamber s i n
a
co- annul ar a r r angement . The chamber s , as v i ewed f r om t he r ear
of
t he e ngi ne ,
ar e number ed c l ockwi se st art i ng wi t h t he upper most chamber as No.
1 .
These chamber s ar e i nt er connect ed by cross - over t ubes f o r f l ame pr opagat i on
dur i ng s t a r t i ng.
L i ght i ng o r s t ar t i ng i s i ni t i at ed f r om s par k i gni t er s l ocat e d
i n t he No.
4
and
No.
5 combust i on chamber s. Each combust i on chamber compr i ses
a s er i es
o f
f or med sheet - met al , ai r c ool ed c yl i ndr i c al l i ner s .
The f or t y- ei ght f uel
nozz l e assembl i es ar e suppor t ed i n t he f uel mani f o l d and
a r e a r r anged i n ei ght c l us t er s
of
s i x noz zl es eac h. Eac h c l us t e r pr oj ec t s i nt o
accommodat i ng aper t ur es i n t he upst r eam e n d o r dome of each combust i on
chamber . The
J T3C 7
combus t o r empl oys a dual - or i f i ce pr essure a t om z i ng f uel
F i l t er Sy st ems
-
The J T3C- 7 engi ne
f uel
s y s t e m i nc or por at es s ev er al f uel
t er s di f f er i ng i n c ons t r uc t i on, f i l t e r ar e a and f i l t r at i on qual i t y depend-
on t he subsys t em component pr o tec t i on r equi r ement s . Tab l e I 1 pr ovi des
a
s y s t e m f i l t er t abul at i on f or t he J T3C- 7 engi ne. I t s h oul d be not ed t h e
i nt er s t age
40
m c r o n pl eat ed paper f i l t er p r o vi des t he pr i mar y pr ot ec t i on f o r
al l s ubs y s t e m c omponent s . I t a l s o ac t s as a c ol l ec t o r of f uel bor ne i c e
c r ys t a l s . An opt i ona l f uel de i c i ng sys t emcan be added t o t he engi ne t o
i nc r eas e f uel f i l t er i nl et t emper a t ur e s, c l ear i ng t he f i l t er of c ol l ec t e d i c e
TABLE I 1
J T3C 7 FUEL SYSTEM FI LT ER SURVEY
Component
Loca t
i on
Mat er i al
Por e Si ze Ar ea (in)
Fuel Pump I nl et St ai nl es s St eel 400 m c r o ns
5. 15
Fuel Cont r ol I nl et St ai nl es s St eel
200
m c r o ns
18. 8
Fuel Cont r ol S er v o St ai nl e s s St e el 40 m c r o ns 7. 1
P r e s s ur e and I nl e t St ai nl e s s St e el 74 m c r o ns 8. 5
Dump Val ve
Fuel Nozzl e Pr mar y
St ai nl es s St eel
007
-
.009
Di a.
0. 39
Fuel Nozzl e Secondar y
St ai nl es s St eel
007
-
.009
Di a.
0. 47
openi ng
openi ng
*Repl aced for CI D Tes t - See Engi ne Modi f i cat i ons f o r AMK Sect i on
Combust or Descr i pt i on
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n o z z l e ( F i g u r e 6)
to o b t a i n t h e r e q u i re d turndown r a t i o ( r a t i o o f maximum to
min imum fue l f l o w ) . The nozz les a re des igned
t o
d i s c h a r g e a p r e d e t e r m i ne d
amount
o f
f u e l when s p e c i f i e d p r e s s u r e d r op s a r e m a i n t a i n e d a cr o s s t h e p r i m a r y
and secondary s tages,
a c t i n g b o t h as an a t o m i z i n g an d m e t e r i n g d e v i c e . The
r e l a t i o n s h i p betw een f u e l
f low
a n d n o z z l e p r e s s u r e d r o p
for
a t yp ica l JT3C-7
e n g i n e
i s
shown i n F i g u r e
7 .
The p r es su r i z in g and dump va lv e i s used
t o
channe l f l ow t o t h e p r im a r y
or
secondary
sys tem.
When the secondary c rack ing
or
s t a g in g p o i n t
i s
reached , th e secondary va lv e opens and
f l o w i s
a d m i t t e d t o
t h e s ec on da ry s y st e m. U n t i l t h e n t h e s y s te m
f l o w
i s
t o
t h e p r i m a r y o n l y . T h i s
s t a g i n g p o i n t
i s
c o n t r o l l e d b y a s p r i n g l o ad e d v a l v e , w h ic h i s s e n s i t i v e t o
t h e d i f f e r e n c e b et we en
f u e l
p r es su re and combus to r p ress u re .
1. SPRING
6.
PRIMARY STRAINER 11. NOZZ LE BOD Y INSERT
2. 1OWERPR)MARY FERRULE
7. S P R I N G S EA T S N A P R I N G 1 2 . P R IM A R Y
PLUG
3.
UPPER PRIMARY FERRULE
8. I N N E R S E C OND A R Y S TR A IN E R S N A P R I N G 1 3. N OZZL E B OD Y
4. SPRING SEAT
9
OU TE R S E C ON D A R Y S TR A IN E R S N A P R I N G
14.
I N S E R T S N A P R I N G
5.
PRIMARY STRAINER SNA PR ING 10. SECONDAR Y STRAINER
1 5 . R E T A I N I N G N U T
F i g u r e
6
Fue l Nozz le
E N G I N E M O D I F I C A T I O N S F O R A M K
8-720
F l i g h t
T e s t
Engines
The approach fohlowed by the
F A A
has been
t o
b l e n d J e t A and FM-9 ad d i t i v e
i n - l i n e a t th e a i r c r a f t f u e l i n g p o i n t
t o
produce an
AMK
f u e l w i t h a c ce p ta b le
f i r e s up re ss io n p r o p e r t i e s i n th e a i r c r a f t ' s f u e l t an ks . T h is ap pr oa ch r e q u i r e s
t h a t t h e
AMK
be a c c e p t a b l e and us e ab l e w i t h i n t h e a i r c r a f t ' s f u e l and e n gi ne
s y st e m s. C o m p a t a b i l i t y s t u d i e s
( R e f s . 1,4 ,5 ,6>
e v a lu a t in g t h e e f f e c t s
of
u s i n g
AMK
o n
the per formance
o f
a i r f r am e fue l sys tems and eng ine components showed
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1.000
1o.ooo
NOZZLE PRESSURE DROP, PSlD
(FUEL PRESSURE-BURNER PRESSURE)
F ig u re 7 JT3C-7 Fuel
Flow
Schedu le
t h a t t h e
AMK
needed
t o
be processed
or
degraded
t o
a f u e l s u i t a b l e
t o
meet t he
r e q u i r e m e n t s o f t h e JT3C-7 eng ine s f o r th e 8-720 a i r c r a f t for t h e p l a n n e d
F u l l - s c a l e T r a n s p o r t C o n t r o l l e d I m pa c t De m on s tr at io n ( C I D ) t e s t . S p e c i f i c a l l y ,
t h e s e r e q u i r e m e n t s
i n v o lv e d e ng in e o p e r a b i l i t y ( s t a r t i n g , a c c e l e ra t i o n /
d e c e l e r a t i o n , r e l i g h t ) a nd p er fo rm a nc e ( e f f i c i e n c i e s ,
e x i t
t empera tu re
d i s t r i b u t i o n , f i l t e r a b i l i t y ) .
S e v e ra l s t u d i e s n t h e U n i t e d S t a t e s and U n i t e d K in gdo m i n d i c a t e d t h a t t h e
FM-9 po lymer can be h i g h l y degraded and t h e AMK r e s t o r e d to n e a r J e t A
p r o p e r t i e s ( R e f s 1 ,2 ,3 ).
A
p r o t o t y p e
AMK
f u e l d e g r a d e r
for
t h e
C I D
a i r c r a f t
was deve loped by t h e Gene ra l E l e c t r i c Company based on a h i g h speed , a i r
d r i ve n c e n t r i f u g 1 pump. F o ur d e g ra d e r s o f t h i s t y p e , n e c e s s a r y for t he 8720 ,
were to be eng ine n a c e l l e mounted and capab le
o f
r u n n i n g o n J e t
A
and /o r
degraded AMK for t h e r e q u i r e d g ro un d and f l i g h t t e s t m i s s i o n s.
NASA
Ames-Dryden F l i g h t R es ea rc h F a c i l i t y was r e s p o n s i b l e
f o r
t he i n s t a l l a t i o n
o f
t h e f o u r d e g r a de r s ys te ms o n t h e 8 720 a i r c r a f t as
w e l l as necessary
m o d i f i c a t i o n s t o t he a i r c r a f t .
F i g u r e 8
i s
a schemat ic
of
t h e
AMK
d eg ra de r s ys te m i n s t a l l e d
f o u r e n g i n e s
o f the 8-720
C I D
a i r c r a f t .
Th e
p r i m a r y d e g ra d e r
c o n s i s t e d of t h e
F l O l
eng ine augmentor ce n t r i f u ga l pump, t he
a u x i l i a r y power a i r t u r b i n e m ot or , and f u e l p r e ss u r e t h r o t t l
11
on each o f t h e
components
C5A a i r c r a f t
n g v a l v e . The a i r
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8 7 2 0 A MK I N S T A L L A T I O N PA RT S L I S 1
I T E M
40
4 1
4 2
4 3
4 4
4 5
50
5 1
5 2
53
54
5 5
5 7
58
5 9
6 2
6 3
6 4
65
66
6 7
68
69
7 0
7 1
7 2
7 3
7 4
7 5
7 6
7 7
7 8
7 9
8 2
8 3
8 4
85
86
0 7
88
89
90
9 1
9 2
9 3
94
9 5
96
9 7
98
99
1 0 0
1 0 1
1 0 2
1 0 3
1 0 4
105
1 0 6
1 0 7
1 0 8
1 0 9
1 1 0
1 1 1
1 1 2
1 1 3
1 1 4
D ESC R I PTI O N
DEGRADER SPEED CONTROL FUEL FLOW SENSOR
DEGRADER ASSEMBLY. PUMP AND A I R TU RBINE MOTOR (AT M)
DEGRADER MOUNTING BRACKET
FUEL LIN E ADAPTER ( INCLUDE S TWO - 4 N I P P L E S )
FUEL HOSE. 3 00 0 P S I OPERATING (0. 75 - IN CH NOM)
FUEL TUBE, 10 00 P S I OPERATING (0. 75 - IN CH NOM)
FLO W O R I F I C E ( 0 . 75
-
0. 50 INCH MS REDUCER)
FUEL RECIRCULA TION HOSE, 10 00 P S I OPERATING (0. 75 - IN CH NOM)
FUEL/AIR HEAT EXCHANGER
HEAT EXCHANGER MOUNTING BRACKET
HEAT EXCHANGER AI R FLANGE CLAMPS
HEAT EXCHANGER AI R DUCT
BELLMOUTH AI R SCOOP
FAN AND RELAY (1 1 5 VAC, 3 PH, 4 00 HZ, 11 A, INRUSH 90 A/PH
FAN MOUNTING BRACKET
QTY/
ENGINE
1
1
1
2
1
1
1
1
1
1
2
1
1
FOR 1 SEC) 1
1
FAN WIRING AN0 CIRCUIT BREAKER
ATM OI L COOLER
ATM O I L COOLER MOUNTING BRACKET
ATM O I L HO SE, 100 0 P S I OPERATING (0. 50 - IN CH NOM)
A T M O I L F I L T E R
ATM OI L F IL TE R MOUNTING BRACKET
ATM O I L PUMP ( 2 8 VOC.
22
A, INRUSH 135 A FOR 0 .5 SEC)
ATM O I L PUMP BYPASS FLOW ORI FI CE ( 0. 50 - IN CH NOM)
ATM OI L PUMP MOUNTING BRACKET WI RING AN 0 RELAY
ATM O IL PRE SSURIZA TION HOSE (0.25- I NCH NOM)
ATM SEAL DRAI N HOSE (0. 37 5- INC H NOM)
FUEL THROTTLING VALVE
FUEL THROTT LING VALV E MOUNTING BRACKET
COP A IR BLEED REG CHK AND
S / O
VALVE WI TH C LAM PS ( C V880)
ENGINE FUEL SUPPLY HOSE, 1 00 0
P S I
OPERATING (1.5 - INCH NOM)
FU EL BYPASS VALVE ( 1 . 5 - I N C H , 14 / 2 8 VDC . 1 A )
FUEL BYPASS VA VE MOUNTING BRACKET
ATM SPEED SIGNAL CABLE AN0 CONNECTORS
ATM AI R SU PPLY DU CT ( 3 . 5 - I N C H N OM, 0 . 04 0 WALL STAI N LESS STEEL)
ATM AI R REGULATOR AND SHUTOFF VALVE CLAMPS
ATM A I R REGULATOR AN0 SHUTOFF VALVE ( 2 8 VDC. 1 A
ATM AIR SHUTOFF VALVE AND ATM AIR INLET CLAMPS
C DP AI R BLEED t A LV E SWI TCH ( C O C KPI T)
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
1
3
ATM AI R SHUTOFF VALVE ( 2 8 VOC. 1 A ) 1
ATM A IR EXHAUST OUCT CLAMP 1
ATM A IR EXHAUST OUCT (4.0 - INCH NOM, 0. 02 0 WALL STAINL ESS STEE L) 1
FUEL THROTTLING VALVE SERVO PRESS. TUBE. 300 0 PS I OPERATING (0 .25 - IN . ) 1
FUEL HEATER JUMPER TUBE 1
SIGNAL CONVERTER (FUEL SENSOR SIGNAL TO VDC) 1
ATM O I L PRESSUR E ( 0 - 2 00 PSI G ) 1
DEGRADER FUEL DISCHARGE PRESSURE (0 -2 00 0 PS IG) 1
DEGRADER FUEL DISCHARGE TEMPERATURE (O o- 25 O0 F) 1
THROTTLING VALVE INTERSTAGE PRESSURE (0- ?5 0 PSIG) 1
FAU LT CONVERTER (SENSOR SIGNA L TO VOC) 6
ENGINE FUEL PUMP INLET PRESSURE (0-150
P S I G )
1
PRIMARY FUEL NOZZLE PRESSURE (0-1000
P S I G )
1
SECONDARY FUEL NOZZLE PRESSURE (0 -1 00 0 P S I G ) 1
EN G IN E FU EL F I LT ER D I FFER EN T I AL PRESSU RE ( 0 - 5 0 PSI O ) 1
DEGRADER FUEL INL ET TEMPERATURE (0 " - 17 5" F) 1
DEGRADER FUEL INL ET PRESSURE (0 -50 PS IG) 1
ENGINE FUEL PUMP INLET TEMPERATURE
( 0 " - 2 0 0 " F )
1
ENGINE SCAVENGE O I L TEMPERATURE (O0 -35O "F) 1
ATM O I L TEMPERATU RE ( 0 - 300 " F) 1
FUEL CONTROL WASH SCREEN DIF FE RE NTI AL PRESSURE ( 0- 50
P S I O )
1
THROTTL ING VALVE LEAKAGE CHECK VALVE 1
THROTTLING VALVE LEAKAGE HOSE, 1000
P S I
O PER ATI N G ( 0 . 50- I N C H ) 1
CHECK VALVE 1
PRESSURE TRANSDUCER. 50 P S I 0 MFP INLET-MF P INL ET SCREEN ENG
2 3
DIFFERENTIAL PRESSURE TRANSDUCER
RESTRAINED BELLOWS
ATM AI R SUPPLY DUCT ( 3 . 5 NOM,
0 .040
WALL WITH 2- . 3- INCH BELLOWS)
SU PPLI ED
BY
NASA
NASA
NASA
NASA
GE
GE
NASA
GE
NASA
GE
NASA
GE
GE
NASA
GE
GE
NASA
GE
GE
NASA
GE
NASA
NASA
GE
GE
GE
NASA
GE
GE
GE
GE
GE
NASA
NASA
GE
NASA
NASA
NASA
NASA
NASA
GE
GE
GE
GE
GE
GE
GE
GE
GE
GE
GE
GE
GE
GE
GE
GE
GE
GE
GE
NASA
GE
GE
COCKFIT
( A > D E G R AD E R P A R T S
Figure
8 8720
Anti-Misting Kerosene Degrader Installation Schematic
ORIGINAL PAGE IS
OF POOR QUALITY
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ORIGINAL PAGE Is
OF POOR
QUALnvl
8EEcQo w
NOZZLE8
( B > D E G R A D E R S C H E MA T I C
F i g u r e
8
8720
A n t i - M i s t i n g K er os en e D egrader I n s t a l l a t i o n Sc he m at ic ( C o n t ' d )
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ORIGIN L P GE S
OF POOR QU LITY
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ORIGIN L
P GE
IS
OF
POOR QU LITY
a
n
K
7
.
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ORIGIN L P GE S
OF POOR QU LITY
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t u r b i n e w as d r i v e n b y co mp re ss or b l e e d a i r d u r i n g e n g i n e o p e r a t i o n a nd was
capab le
o f
p r o v i d i n g d eg ra de d AMK
for
e ng in e s t a r t t h r o u g h t h e u se o f h i g h
p re ss ur e a i r f rom g r o u n d c a r t s or eng ine c ross b l ee d . The
F l O l
engine pump
u t i l i z e d b y
G . E .
as the degrader had a des ign
f low
c a p a c i t y much h i g h e r t h a n
t h a t r e q u i r e d
b y
th e JT3C-7 eng in e . There fore , i t was necessary t o i n c l u d e a
r e c i r c u l a t i o n l o o p t h r ou g h an a i r - f u e l h ea t e x ch a ng e r, m ou nte d i n a n e x t e r n a l
wing mounted pod, to d i s s i p a t e e x ce ss h e a t g e n e r a t e d b y t h e d e g r a d e r t o t h e
f u e l .
A
t h r o t t l i n g v a l v e l o c a te d a t t h e degrader e x i t r ed uc es t h e f u e l
p r e s s u r e b e f o r e t h e m a in f u e l e n g i n e pump
to
a c c e p t a b l e l e v e l s
(
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I n p r ep a ra t io n for o n e s e r i e s of t e s t s c on du ct ed a t t h e F A A T e c h n i c a l C e n t e r ,
t h e JT3C-6 f u e l c o n t r o l was m o d i f i e d b y b l o c k i n g s h u t t h e s e r v o f i l t e r bypass
and r e p l a c i n g t h e 74 m i c r o n i n l e t f i l t e r s c re e n w i t h a n ew l y f a b r i c a t e d 2 00
m ic ro n s iz e f i l t e r . A t t h e r e q u e s t of
N A S A I F A A ,
a n o t h e r s e r i e s o f t e s t s w e r e
schedu led to e v a l u a t e th e o p e r a b i l i t y
of
t h e JT3C-7 co n t ro l
o f
t h e B-720 t e s t
a i r p l a n e when o p e r a t i n g o n AMK f u e l .
P r a t t & W hi tn ey a s s i s t e d i n t h e
p r e p a r a t i o n a nd
i n s t a l l a t i o n of a JT3C-7 fu e l c on t r o l on th e JT3C-6 eng ine .
The JT3C-7 f u e l co n t ro l was i nsp ec t ed , r e pa i r ed and m od i f i ed w i t h a down
c ha nge a c c e l e r a t i o n cam i n o r d e r to m a k e t h e c o n t r o l
c o m pa t ib l e w i t h t h e
JT3C-6 t e s t e n g i n e . I n s t a l l a t i o n of the cam and checkout was accompl ished by
Hami l t on S tanda rd . A mockup of t h e JT3C-7 c o n t r o l a nd s e v e r a l s p e c i a l f i t t i n g s
were prov ided
to
a s s i s t i n p l um b i ng t h e m o d i f i e d JT3C-7 f u e l c o n t r o l to t h e
JT3C-6 eng ine . The re s u l t i n g schedu le
i s
shown i n F i g u r e 1 2 w i t h t h e B i l l - o f -
M a t e r ia l JT3C-6 and JT3C-7 sch edu les.
CONTROL SPEED - Nc, RPM
x l o
F i g u r e 12 F u e l C o n t r o l A c c e l e r a t i o n S c h ed u le s
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UNDEGRADED
104,
A M K
,
-
5 81
I I
I I I 1 1 1 1 1 1 I I11111 I I 1 1 1 1 1 1 1 I
I
l l l W
C
106
1 0 5
CONDITIONS
m O A
PUMPSPEED IRPMI 2400 3000 3000
FUEL
FLOW
(kg/hr) 750 1590 1590
DISCHARGE PRESSURE IkPa) 207 0 3450 345 0
- \
3.6
1.6
1.4 1.2 1.2
- A . .
m
I V
I
i I
1
i f i I I
1 2 4 5
6
7
8
9 1 0 11 12 13 14 1 5 1 6
NUMBER OF PASSES THROUGH J T ID FUEL PUMP
F i g u r e
13
Fi l te r R a t i o S en s i t i v i t y
Undegraded AMK Degraded AMK
E
Transition
velocity
E
0.01 0.1 1 o 10 100
Velocity
approaching
f i l ter, cm /sec
F i g u r e 1 4
T r a n s i t io n V e l o c i t y
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LABORATORY FLOW C H A R A C T E R I Z A T I O N E Q U I P M E N T
Under N A S A / F A A sponso rsh ip ,
P r a t t & W h it ne y i n v e s t i g a t e d t h e e x t e n t o f
AMK
p r e - s h e a r i n g or d e g r a d a t i o n r e q u i r e d t o e na bl e s a t i s f a c t o r y o p e r a t i o n of t h e
e n g in e com ponents a t v a r i o u s f u e l t e m p e ra t u re s . F u e l c h a r a c t e r i z a t i o n t e s t s ,
d e v e l o p e d b y P r a t t & W h it ne y an d o t h e r i n v e s t i g a t o r s , w er e u se d to de te rm ine a
c o r r e l a t i o n w i t h t h e pe rfo rm an ce r e q u i r e d
o f
t h e f i l t e r s , f u e l n o z z l e s a nd
combustor o f th e JT3C-7 eng ine for t h e C I D m i s s i o n . Because t h e a n t i m i s t i n g
a d d i t i v e i nc re as es t h e e f f e c t i v e v i s c o s i t y o f t h e b l e n d e d AMK f u e l , t e c h n i q u e s
t h a t measured v i s c o s i t y a nd f i l t e r a b i l i t y were u sed t o q u a n t i f y t h e e x t e n t t o
which
AMK
was degra ded fr o m i t s i n i t i a l o r i g i n o r unshea red s t a te .
For
low
l e v e l s o f p ol ym e r d e g r a d a t i o n , t h e d e g r a d a t i o n l e v e l was e v a l u a t e d b y a f i l t e r
r a t i o o b t a i ne d f rom a s i n g l e f l o w f i l t r a t i o n t e s t . T hi s t e s t
i s
a r a t i o o f t h e
t i m e s
r e q u i r e d
f o r
a k n o w n q u a n t i t y of t e s t f u e l and t h e same q u a n t i t y
o f J e t
A
f u e l
t o
f l o w t hr ou g h a s p e c i f i e d f i l t e r (1 7 m i c ro n sc re en ) ( s e e Appendix 6-1
f o r a d e t a i l e d p r oc e du r e) .
I n an e a r l i e r p ro gra m
( R e f .
1 > , AMK was degraded by in c re a s in g number
o f
passes t h rough a JT8D fue l pump . The sens i t i v i t y o f f i l t e r r a t i o t o the number
of
passes through the pump
i s
shown i n F i g u r e 1 3 . T h i s p l o t an d su b se qu e nt
t e s t s
showed t h a t a l t ho ug h f i l t e r r a t i o i s an adequate measurement techn ique
f o r
d e g r a d a t i o n l e v e l s e q u i v a l e n t
t o f i l t e r
r a t i o s d o w n t o a p p r o x i m a t e l y two,
i t d i d n o t p ro v i de s u f f i c i e n t r e s o l u t i o n t o d e s c r ib e l e v e l s b elo w t h a t p o i n t .
F i l t e r a b i l i t y , f u e l s pr ay q u a l i t y , and c om bu st io n t e s t s r ec or de d i n R e f. 1
i n d i c a t e d t h a t t h e r e w e r e s i g n i f i c a n t d i f f e re n c e s i n t h e way AMK deg raded
between the
3
and 16 passes per fo rmed a l though
f i l t e r
r a t i o s showed a l m o s t n o
d i s t i n c t i o n .
I n f i l t r a t i o n e xp er im en ts , when
AMK
v o l u m e t r i c f l o w r a t e p er u n i t
a rea or v e l o c i t y i s p l o t t e d a g a i n s t i n c r e a s i n g d i f f e r e n t i a l p r e ss u r e a cr os s a
v er y f i n e f i l t e r , t h e r e
i s
a n o t i c e a b l e i n cr e a se i n f l o w r e s is t a n ce a t a
p a r t i c u l a r v e l o c i t y a s shown i n F ig u r e 14. The s h i f t p o i n t
i s
a f u n c t i o n
o f
f u e l t y pe o r l e v e l o f AMK d e g r a d a t io n and has been l a b e l e d t r a n s i t i o n v e l o c i
( V , ) .
I t has been hypo thes i zed t ha t t hese
s h i f t s
or
t r a n s i t i o n v e l o c i t i e s
are analogous t o t r a n s i t i o n
from
l a m i n a r t o t u r b u l e n t f l o w w i t h i n t h e
f i l t e r
P r a t t & Whi tney has found t h i s measurement tech n iqu e t o be a va luab le and
rep rod uc ib l e means o f c a t e g o r i z i n g h i g h l y d eg ra de d AMK f u e l s .
A
d e t a i l e d
l a b o r a t o r y p r o c e du r e
f o r
m ea su rin g t r a n s i t i o n v e l o c i t y
i s
i n c l u d e d i n A ppend
6-2.
T h e l e v e l s
of AMK
deg rad a t i o n recommended by P r a t t & Whi tney
t o
s a t i s f y t h e
f i l t e r a b i l i t y and combus to r pe r f o rmance re qu i r e d
for
t h e C I D program
w i l l
be
assessed
i n
t h e n e x t s e c t i o n of t h i s r e p o r t .
RESULTS AND D I S C U S S I O N
FUEL
SYSTEM
AND E N G I N E OPERABILITY
P r a t t
&
Whi tney ass i s t ed
N A S A
i n d e t e rm i n i n g th e s a f e t y and m i s s i o n s u i t -
a b i l i t y o f t h e m od i f ie d f u e l
s y s t e m
f o r t h e p r o p o s e d e n g i n e t e s t s a n d
s ub se qu en t f l i g h t s . T h i s s t u d y re v i ew e d an d a n a l yz e d i n f o r m a t i o n and t e s t d a t a
r e c e i v e d from
N A S A / F A A
r e g a r d i n g t h e d e g r a d e r s y st em , h e a t e x c ha n g e rs , e n g i n e
fu e l sys tem and subsequent e f f e c t s t o eng ine o i l a n d f u e l a s t h e y p e r t a i n e d t o
operab i l i t y . Recommended l i m i t s f o r f u e l d e g r a d a t io n and e ng in e c o n d i t i o n
( 5 )
were de termined and presented t o
N A S A / F A A .
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The f i 1 e r a b i
1
i y c h a r a c t e r i s t i c s of a l l t he f u e l
system components were
su rveyed t o a s s e s s c l o g g i n g for s u b s e q u e n t e n g i n e t e s t s .
A summary o f t h e
J T 3 C - 7 b i l l - o f - m a t e r i a l f u e l s y s t e m f i l t e r s and s c re en s i s t a b u l a t e d i n T ab le
11. These f i l t e r s w ere i n c l u d e d i n t h e as se ssm en t e x c e p t fo r t h e f u e l p u m p
i n t e r s t a g e w h i c h was r e p l a c e d by a
G E
5-79 metal f i l t e r o f s m a l l e r a r e a b u t
s l i g h t l y c oa r se r mesh s i z e
( 4 4 m i c r o n s ) . Based o n known f i l t e r c h a r a c t e r i s t i c s
( a r e a , m esh s i z e , f u e l flow r eq ui re m en ts ) and t h e f i l t e r a b i l i t y e x p er im e nt s
per fo rmed under
NASA
c o n t r a c t NAS3-22045 and documented i n
R e f .
1 , t h e
pressure and dump ( P & D ) , a n d f u e l
c o n t r o l s er vo f i l t e r s were ju dg e d t o be
most
s u s c e p t i b l e t o cl og g in g . The c l og g in g phenomena due t o g e l f o r m a t i o n was f o u n d
t o
b e a f u n c t i o n
of
i n c re a s e d f u e l
flow
o r v e l o c i t y , d ec re as ed f u e l t e m pe r at u re
a n d c u m u l a t i v e
t i m e
(Ref. 1 ) . T h e r e f o r e , i t was p r o j e c t e d t h a t f o r s h o r t
d u r a t i o n s , low a l t i t u d e f l i g h t s and e nv ir on me nt al c o n d i t i o n s f o r t h e
C I D
program, AMK degraded t o f i l t e r r a t i o s o f a p p r o x i m a t e l y 1 . 2 or t r a n s i t i o n
v e l o c i t i e s a t l e a s t 2-3 cm /sec.,
w ou ld pr e cl u de c l o g g i n g i n t h e e n gi n e f u e l
system. Based on f u e l no zz le sp ray q u a l i t y and subsequen t combus t i on t e s t s
( R e f .
1 > ,
t h i s l e v e l
o f
de gr ad at io n was judged
t o
b e a c c e p t a b l e
for
e n g i n e
c om bu st or r e q u i r e m e nt s as w e l l . I n a d d i t i o n , t h e e n g i n e two stage gear pump
c o u ld p r o v i d e f u r t h e r d e g ra d a t i o n m ar gi n t o t h e AMK f u e l
d e l i v e r e d from t h e
d e g r a d e r s ys te m. I n
t h e ev en t t h a t s i g n i f i c a n t c l o g g i n g o f t h e se r v o f i l t e r
ta ke s p la c e , t h e f u e l c o n t r o l c o ul d be g in t o r e a c t s l u g g i s h l y , e s p e c i a l l y a t
low power . Comp le te b l ock i ng o f t h e s e r vo f i l t e r w o ul d c au se
loss
o f s e r v o
p r e s s u r e w i t h s ub se qu en t f u e l
flow
r e d u c t i o n
t o
a min imum set t ing . The min imum
flow l e v e l
for
th e JT3C-7 eng ine i s 640 pph which i s be low i d l e . Remova l of
t h e s e r v o
f i l t e r
was n o t p r a c t i c a l b eca use c o n ta m i na n t s c o u l d a f f e c t t h e
v a r i o u s s e rv os r e s u l t i n g i n u n p r e d i c ta b l e m e t e r i n g and g o v e rn i n g e f f e c t s . For
r easons
o f
s a f e t y ,
i t
was s t r o n g l y recommended t h a t f i l t e r s l s c r e e n s w i t h o u t
p r o v i s i o n s for a u t o m a ti c b yp as s, ( f u e l c o n t r o l s e r v o a nd f u e l n o z z l e s ) be
m o n it o re d on a l l f o u r e n g i n e s
for
p r e s s u r e r i s e .
I t
was a l s o recommended th a t
a p p r o p r i a t e f u e l samples be a na ly ze d f o r d e g ra d at io n l e v e l b y f i l t e r r a t i o and
t r a n s i t i o n v e l o c i t y t e s t s .
I n f o r m a t i o n was s u b m i t t e d
to
NASA Ames-Dryden F l i g h t R es ea rc h F a c i l i t y i n t h e
areas o f e n g in e and com ponent o p e r a b i l i t y and d u r a b i l i t y , a i r b l e e d , p lu m b in g ,
i n s t r u m e n t a t i o n , e t c . T h i s s e c t i o n summarizes o n l y t h e more c r i t i c a l a re a s
t h a t r e qu i r e d s i g n i f i c a n t s tu dy or ana l ys i s . One o f t h e f i r s t a reas o f
i n v e s t i g a t i o n con cern ed t h e a v a i l a b i l i t y and e f f e c t s
of
e ng in e b le e d a i r
r e q u i r e d t o d r i v e t h e a i r t u r b in e motor d r i v e f o r t h e d e g r a d e r . A i r b l e e d
f l o w s a nd p re s s u r e l e v e l s p r e d i c t e d
for
d e g r a d e r o p e r a t i o n
(G.E.
computer
model) were compared
t o
t hose av a i l a b l e fr om th e JT3C-7 eng ine . Tab le
I11
shows t h e r e s u l t s
o f
t h i s c om pa rison w hic h i n d i c a t e s t h a t t h e a i r b l e e d
r eq ui re m en ts were o n l y s l i g h t l y h i g h e r t ha n t ho se a v a i l a b l e
f rom
a t y p i c a l
i n - s e r v i ce JT3C-7 eng ine .
I n r eg a r d
t o
t h e p o s s i b i l i t y
of
l o c k i n g e n gi ne b l e e d op en o r c l o s e d ,
i t was
con vey ed t h a t t h i s c o u l d be d e t r i m e n t a l t o e ng in e t r a n s i e n t o p e r a t i o n . I n
p a r t i c u l a r , t h e JT3C-7 e n g in e t h r u s t l o s s when t h e a u t o m a t i c su r g e b l e e d s a r e
opened on a
low
p ow er a p pr oa c h c o n d i t i o n a t 30 00 f e e t an d 15 0 k n o t s t r u e a i r
speed was es t i m at ed
t o
be ap pr ox im at e l y 327 pounds
or
10%.
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TABLE
I11
AND
TEMPERATURES
V S . P R E D I C T E D
QUANTITIES
AVAILABLE JT3C-7 BLEED FLOWS, PRESSURES
P R E D I C T E D
-
G . E .
MODEL
C A S E ( 1 )
C A S E
( 2 )
( i d l e ) ( m a x )
6 3% 98%
( T a m b ( O R ) 550
565
565 550
( B l e e d P r e s s u r e
((Bleed Temp ( O R ) ) 725 725 1181 1181
)
44.9 44.9 174.9 174.9
7;;;;
Flow)
1
.o
1
.o
1.9 1 .9
(Bleed Rat io ) 0.027 0.027 0.012* 0.012*
p s i a )
A v a i l a b l e
HPC
Bleed Pressures and Tempera tures
( f r om
JT3C-7 eng ine a t t he
above b leed
flows)
PTX 30.5 30.5 16 8.3 17 1.9
a t
B leed
P o r t
Blee d Temp. a t
)
737 737 1243 1228
B leed
Port
( O R )
TTX
* =
S l i g h t l y e xc ee ds JT3C-7 s p e c i f i c a t i o n
l i m i t o f
0.012 f o r
HPC
b le ed a i r
f o r maximum cont inuous
to
t a k e o f f p o w e r
Seve ra l recommendat ions were made by P r a t t
&
W h i t n e y r e l a t i n g
t o
f u e l
p r e s s u r e , f u e l t e m p e r a t u r e a n d
o i l
t e m p e r a t u r e
l i m i t s
fo r th e JT3C-7 en gin e.
D u r i n g e ng in e o p e r a t i o n s , f u e l p r e ss u re a t t h e e n gi ne f u e l pump i n l e t s h o u l d
be m a i n t a in e d a t n o t l e s s t h a n 7 .5 p s i a bov e t h e t r u e v a p o r p r e s s u r e
of
t h e
f u e l
to
p reven t vapo r
l o c k a n d /o r pump c a v i t a t i o n
from
o c c u r r i n g a t e l e va t e d
f u e l t e mp e ra t ur es . F u el p r e s s u r e s h o u l d be k e p t b e lo w 55 p s i g d u r i n g e n g i n e
o p e r a t i o n and s h o u l d n o t be a l l o w e d t o e x ce e d 8 5 p s i g a f t e r s hu td ow n when t h e
f u e l p ressu re may i nc r ea se due
t o
t he rma l expans ion o f t h e f u e l . The e n g i n e
f u e l
system
c a n. to le ra te s h o r t d u r a t i o n ( m i l l i s e c o n d s ) p r e s s u r e e x c u r s i o n s
or
s p i k e s o f 10 0 p s i a bo ve t h e pump i n l e t p r e s s u r e . The l i m i t i n g a r e a i s a
s e c t i o n
of
t h e f u e l c o n t r o l w h ic h s ee s pump i n l e t p r e s s u r e an d
i s
capab le
o f
s u s t a i n e d o p e r a t i o n o n l y up
t o
1 1 5 p s i a .
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F ue l t e m pe r at u re l i m i t s w ere e s t a b l i s h e d w i t h t h e a s su m pt io n t h a t l o n g
descen ts from h i g h a l t i t u d e s were b ey on d t h e s l o p e o f t h e f l i g h t t e s t s p la nn ed
so t h a t e x t r e m e l y h i g h t e m p er a tu r e r i s e s t hr o ug h t h e f u e l pumps c o u l d b e
avo ided .
I t
was recommended t h a t pump i n l e t t empe ra tu re be l i m i t e d
t o
160F
w i t h o v e rs h o ot s
t o
170F
for
s h o r t p e r i o d s
o f
t i m e o n l y . T h i s
l i m i t
was se t
because
o f
t h e u n k n o w n c o n d i t i o n of t h e l o w t e m p e r a t u r e e l a s t o m e r s e a l s t h a t
w ere p r e s e n t i n t h e e n gi n e f u e l pumps and f u e l c o n t r o l . P r a t t
&
Whi tney
recommends mai n t a i n i ng eng ine o i 1 i l e t tempe ra tures be tween 176 and 21 2F for
e x t en d e d s e r v i c e l i f e . H ow ev er, o i l t e m p e r a tu r e s w er e p e r m i s s i b l e to 270F
w i t h o v e rs h o o ts t o 290F
for
10 m in ut es f o r b o t h g ro un d and i n - f l i g h t
o p e r a t i o n s .
FUEL C H A R A C T E R I Z A T I O N TESTS
AND
ANALYSES
The purpose
of
t h e
l a b o r a t o r y f u el c h a r a c t e r i z a t i o n t e s t s was t o v e r i f y AMK
f u e l b l e n d e d
f o r
t h e C I D p r o gr a m r e a c t e d i n t h e same ma nn er as t h e p r e v i o u s l y
e v a l u a t e d AMK (Ref.
1 ) for f i l t e r a b i l i t y and c om bu st or p e rf or m an c e, a n d t o
a s s e s s t h e d e g r a d a t i o n l e v e l a c h i e v e d by the degrader sys tem
f o r
subsequen t
e n g i n e t e s t s . Two s e t s of f i l t e r r a t i o and t r a n s i t i o n v e l o c i t y mea su r in g
e qu ip me nt we re f a b r i c a t e d b y P r a t t & Whitney for NASA Ames-Dryden F l i g h t
R ese arch F a c i l i t y and t h e F A A Techn i ca l Cen te r . A l i s t o f t he equ ipmen t
c o m p r i s i n g e a c h
o f
t h e
flow
m e as u ri ng d e v ic e s i s p r o v i d e d i n T a bl e C-1
o f
Appendix
C .
Degraded AMK was o b t a i n e d from t h e
F A A
f o r u se i n c a l i b r a t i n g t h e n ew ly
f a b r i c a t e d e qu ip m en t a g a i n s t e qu ip me nt used i n e a r l i e r p ro gra ms a t P r a t t &
Whitney . The f ue l was f u r t h e r deg raded us i ng a Ga u l i n D i s pe r se r or homogenizer
f o r
one pass a t
8000
p s i
( N A S A
CR - 168081 ) be fo re compara t i ve expe r imen ts we re
conduc ted . Resu l t s o f t h e c a l i b r a t i o n s i n d i c a t e d go od a gr ee me nt be tw e en t h e
equipment fo r t h e h i g h l y d eg ra de d
AMK
t es ted . Tab le I V i s a t a b u l a t i o n o f t h e
d a t a r e c or d e d and subsequ ent c a l i b r a t e d f i l t e r r a t i o s . The t r a n s i t i o n
v e l o c i t i e s f o r t h e t h r e e u n i t s o b t a i n e d fro m t h e p l o t s shown i n F i g u r e s 1 5, 1 6
and 17 ar e shown i n Tab le
V .
Tab le I V
FILTER R A T I O S
n i t J e t A T i m e
AMK
Time F i 1 t e r R a t i o
# 1 ( P r a t t
&
Whit ney) 5.33 sec 5.86 1 . 1
#2 ( N A S A Ames-Dryden) 5.41 sec 5.9 3
1 . 1
#3 ( F A A Tech Ce nte r) 5.13 sec 5.68
1 . 1
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r
2
P
15
2
I
I
u-
g
10
2
5
u
U
u.
LL
5
0
0 5 10
15 2
25
VELOCITY, CMiSEC
F i g u r e 15 D e t e r m i n a t i o n o f T r a n s i t i o n
V e l o c i t y . U n i t 1
0 15
20
25
VELOCITY, CMlSEC
F i g u r e 1 6 D e t e r m i n a t i o n o f T r a n s i t i o n
V e l o c i t y . U n i t
#2
24
P
2
8 1 5 ,
4
I
$
u-
a
g
10
5
U
kk
Y
n
5
0 5
10
15
20
25
VELOCITY, CMlSEC
F i g u r e 17 D e t e r m i n a t i o n
o f
T r a n s i t i o n
V e l o c i t y . U n i t 3
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TABLE V
T R A N S I T I O N
VELOCITY
T r a n s i t i o n V e l o c i t y
# 1 ( P r a t t
&
Whi tney) 10.5 cm/sec
#2 ( N A S A Ames-Dryden) 10.7 cm/sec
#3 ( F A A Tech Ce nt er ) 10 .5 cm/sec
The f i l t e r r a t i o and t r a n s i t i o n v e l o c i t y m easurement e qu ip m en t w ere d e l i v e r e d ,
s e t
up and demonst ra ted f o r b o t h
NASA
Ames-Dryden F l i g h t R e se a rc h F a c i l i t y a nd
F A A T e c h n i c a l C e n t e r p e r s o n n e l for t h e i r s ub se qu en t u se o n - s i t e .
A
sample
o f
AMK
f u e l , t y p i c a l
of
t h a t u sed i n t h e
C I D
t e s t , was t e s t e d
t o
e s t a b l i s h t h e f l o w c h a r a c t e r i s t i c s and f i l t r a t i o n p r o pe r t ie s as a f u n c t i o n o f
d e gr a da t i on l e v e l a nd t o compare t h e f i l t e r a b i l i t y c h a r a c t e r i s t i c s
o f
t h e
r e c e n t l y b le nd ed f u e l w i t h f u e l t e s t e d d u r in g e a r l i e r
N A S A / P & W
p rog rams . Two
b a tc h es o f f u e l were t e s t e d as a r e s u l t
o f
a bn or ma l l y h i gh f i l t e r r a t i o s f ou nd
i n t h e f i r s t b a t c h
o f
AMK f u e l . I n i t i a l t e s t i n g
o f
t h e f u e l t o d et er mi ne i t s
f i l t e r r a t i o showed u n u su a l l y h i g h
l e v e l s o f f i l t e r r a t i o ( o v e r 5 00 ) . A
p o r t i o n
o f
t h i s f u e l was d e gr ad e d t o a t r a n s i t i o n v e l o c i t y o f 4 .5 and t he n
s u b j e c t e d t o f i l t e r a b i l i t y t e s t i n g . Immediate f i l t e r c l o gg i ng o cc u r re d , even
a t t h e l ow e s t
f l o w
r a t e s . The u n u su a l l y h igh f i l t e r r a t i o s o b ta in e d p r i o r
t o
t he f i l t e r a b i l i t y t e s t i n g was a s cr ib e d t o c on ta m in a t io n from a sample be ing
d ra wn f r o m t h e b o t t o m
o f
a s t o r a q e t a n k . E v a l u a t i o n
of
t h e i n i t i a l b a tc h o f
AMK
f u e l was d i s c o n t i n u e d an d a
e v a l u a t i o n
o f
th e AMK fu e l . The
I m p e r i a l C he mic al I n d u s t r i e s I
A second ba t ch
o f
AMK
fue l samp
c o n s i d e r e d t o be a no rma l l eve l
d i v i d ed i n t o two p o r t i o n s w h i c h
l e v e l s
of
2.0 and 2.7 cm/sec. F
t h e p r e s s u r e d r o p a c r o s s a 1 6
m
i e w
f u e l sample was req ues ted to c o n t i n u e t h e
r e m a in d e r o f t h e c o n t a m i n a te d f u e l w as s e n t
t o
1) f o r a n a l y s i s .
e recorded f i l t e r r a t i o s
o f
57 w h i c h
i s
f o r
unsheared o r v i r g i n AMK. The sample was
were degraded t o t r a n s i t i o n v e l o c i t y ( V T )
l t e r a b i l i t y t e s t s were conduc ted t o measure
c r o n s t a i n l e s s s t e e l s c re e n as a f u n c t i o n
o f
~ ~
AMK
f u e l
flow
a t a m b ie n t t e m p e r a t u re
( R e f . 1 ) .
The f i l t e r t e s t i s de sc r i b ed i n
NASA CR-168081.
Tab le
V I
p r e s e n t s t h e r e s u l t s
o f
t he f i l t e r a b i l i t y t e s t i n g
c o n d u c t e d o n t h e
AMK
f u e l d u r i n g t h i s prog ra m. T a bl e
V I 1
p r e s e n t s t h e d a t a
r e co r de d u nd er c o n t r a c t NAS3-22045. I n t he t a b l e s , f i l t e r c l o g g i n g i s
i n d i c a t e d
fo r
t h o s e v e l o c i t y e n t r i e s w here t h e p r e s s u r e dr o p i s shown as a
r a ng e , r a t h e r th a n as a s i n g l e v a lu e .
R e s u l t s o f t h e f i l t e r a b i l i t y t e s t i n g conducted on t h e second b a t ch
o f AMK
f u e l
i n d i c a t e d t h a t t h e c l o g g in g c h a r a c t e r i s t i c s o f t h e o n - l i n e b l e nd e d
AMK
made
f o r t h e
C I D
p ro gr am a r e v e r y s i m i l a r to
t h e
b a t c h b l e n de d f u e l u n de r
NASA
c o n t r a c t NAS3-22045. T h is t e s t i n g e s t a b l i s h e d t h e c r i t e r i a f o r f i l t e r a b i l i t y
a nd c om b us to r r e q u i r e m e n t s d u r i n g t h e C I D program. Fue l samples ta ke n
downstream
o f
a de gr ad er , w h i l e t h e e ngine o p e r at e d a t i d l e , r e s u l t e d i n
t r a n s i t i o n v e l o c i t y l e v e l s
o f
2 .9 and 3.2 cm/sec whic h was co ns ide red
s a t i s f a c t o r y
for
t h e p l a n n e d m i s s i o n s
o f
the
8-720
a i r c r a f t .
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V T
= 2.0
c l o g g i n g
V T = 2 . 1
c l ogg i ng
TABLE V I
FILTERABILITY
T E S T ( 1
6 /J m ABSOLUTE
SCREEN)
1984
A P
psi
0 . 20
0 . 4 0
0 . 6 0
0 . 80
0 . 90
1.30-1 .40
1.60-1.80
2.10-2.30
3.00-3.40
4.00-4.40
5.80-9.40
0 . 10
0 . 3 0
0.50
0 . 80
1 . 10
1.20-1.30
1 .50-1.60
1.90-1.20
2.10-2.60
3.60-4.60
F low Rate
c c l s e c l
1 . o
2 .0
2.7
3.6
4 . 1
5 . 4
6.0
6 . 5
8 . 0
8 . 8
10.4
1 .o
2 . 0
2.8
4 . 0
5.6
6 . 1
1.7
9 . 0
10 . 0
13.4
S u p e r f i c i a l (
V e l o c i t y , c m l s e c
3.1
6 . 3
8.4
11.3
12.8
16.9
18.8
20.3
25.0
21.5
32.5
3.5
6.3
8 . 8
12.5
11.5
19.1
24.1
28.1
31.3
41.9
T r u e V e l o c i t y ( )
cmlsec.
141
210
241
290
312
367
392
406
463
49
1
551
141
210
251
31 3
380
398
455
502
331
665
.............................................................................
I ) S u p e r f i c i a l v e l o c i t y i s b as ed o n p i p e c r o s s - s e c ti o n a l a r e a i n w h ic h t h e
( )
T r u e v e l o c i t y i s based on flow c o e f f i c i e n t c o r re c t ed f l o w a re a from a
f i l t e r
i s
p l a c e d .
J e t
A
c a l i b r a t i o n
for
t h e f i l t e r b e in g te st ed .
TABLE
V I 1
1981 FILTERABILITY T E S T ( 1 6 p m ABSOLUTE S CRE E N) 1981
TEST #45
AP F lo w R a te S u D e r f i c l a l
I
T r u e V e l o c i t v ( )
psi c c l s e c l
VT
=
1.9 0 .30 1 .6
0 . 52 2 . 1
0.69 3.0
c log g ing 0 .94-1 .10 3 .8
1.21-1.49 4.1
2.43-3.80 5.8
v e i o c i ty, cm lsec
5.0
8 . 4
9 . 4
11.9
12.8
18.1
Tes t #34
cm lsec
179
290
303
350
366
44 1
VT
=
2.5 0.65
1.03
c logg ing 1 .28-1 .61
1.62-2.48
2.9-3.1
4.2-5.5
6.9-9.9
12.2-15.6
15.6-1 8.2
3.5
5.3
4.2
8.2
9.4
11.1
13.6
16.4
18.0
10.9
16.6
19.4
25.6
29.4
3 4 . 1
42.5
51.3
56.3
32
1
41 5
451
533
516
643
1 2 0
802
853
.............................................................................
S u p e r f i c i a l
v e l o c i t y i s based on p i p e c r o ss - s e c t io n a l a r e a i n w hi c h t h e
( * ) T ru e v e l o c i t y i s b as ed on
flow
c o e f f i c i e n t c o r re c t ed flow a r e a from a
I )
f i l t e r i s p l a c e d .
J e t A c a l i b r a t i o n for t he f i l t e r b e i n g te st ed .
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ENG I NE PERF O RM ANCE
The B-720/JT3C-7 s im u la t io n
for
t h e C I D f l i g h t p l a n s u p p l ie d b y NASA
Ames-Dryden F l i g h t Resea rch F a c i l i t y was rev i ewed and assessed t o be
s a t i s f a c t o r y
from
a n e n g i n e o p e r a b i 1
i
y s t a n d p o i n t . E ng in e s im u l a t e d p a r t
power and t akeo f f power pa rame te rs
w e r e
compared w i t h s i m i l a r p ow er c o n d i t i o n
d a t a f rom in-house and FAA T ec h C e n t e r g e n er a te d g r o un d t e s t d a t a a nd t h e
agreement was good.
I t was n o t e d t h a t t h e r e was some e n g i n e o p e r a t i o n i n t h e
c om pr es so r " b l e e d s o pe n' ' po we r r e g i o n d u r i n g a i r c r a f t a p p ro a c h .
F i gu re 18 shows t y p i c a l JT3C-7 eng in e perfo rmance da ta used as a ba se l i ne
r e f e r e n c e t a k e n
f o r
s tanda r d day a t sea l e v e l s t a t i c c o n d i t i o ns . I n F i gu r e 18,
N ,
r e p r e s e n t s t h e low rotor speed, and N 2 t h e h i g h
rotor
s pe ed , i n RPM,
c o r r e c t e d
t o
sea l e v e l s t a t i c s ta n da r d day c o n d i t i o n s a s a f u n c t i o n
of
e n g i n e
p r e s s u r e r a t i o , P T 7 / P T Z . F igu re 18 p resen t s t he eng ine exhaus t gas
tempera tu re i n deg rees Rank ine , and W F r e p r e s e n ts e ng in e f u e l
f l o w ,
i n
l b s / h r , w i t h b o t h p a ra m et er s c o r r e c t e d
t o
sea l e v e l s t a t i c s t a n d a r d day
c o n d i t i o n s .
h
pc
SLTO
97
N2
EPR
I
2.672
N2 9670
12,000-
1o.ooO
-
a
I,
9
8000-
2
5
v
B
I-
a
a
ImJO-
V
4000-
SLTO
104.8% N 1
IDLE 235
4000 A 1 1
1
1 o
1.5 2.0
2.5 3.c
Y ENGINE
PRESSURE
RATIO, PT~ /PT:
Fi gu re 18 Ty p i ca l JT3C-7 Eng
W
ENGINE PRESSURE RA TIO,
PT7/PT2
ne Per fo rmance (S ta nda rd Day Sea Leve l S t a t i c )
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T h e s i g n i f i c a n c e
o f
t h e e n g i n e f u e l flow, exhaus t gas t empera tu re , and t he
ro to r speeds i s t h a t t he s e pa ra m et er s d e f i n e t h e p er fo rm a nc e c h a r a c t e r i s t i c s
o f t h e e ng in e and a r e t h u s an i n d i c a t i o n
o f
e n g i n e " h e a l t h " .
For
example, i f
t h e f u e l flow a nd e x h a u st ga s t e m p e r a tu r e s a r e h i g h e r t h a n n o rm a l a t a g i v e n
e n g i n e p r e s s u r e r a t i o ,
i t i n d i c a t e s a l o s s i n en gi ne e f f i c i e n c y . The b e h a v io r
o f
t h e low and h i gh p res su r e compressor
ro tor
speeds, N , and
N Z ,
p r o v i d e s
an i n d i c a t i o n w h et he r t h e l o s s
o f
e f f i c i e n c y
i s
i n t h e lo w o r i n t h e h i g h
s p o o l .
The expe cted rang e
o f
va lues above and be low the ave rage
of
each
o f
t h e f o u r
per formance
pa rame te rs for a new pr od uc t i on JT3C-7 eng in e has been es t im at ed
t o be as f o l l o w s a t a g i v e n e n gi ne p r e s s u r e r a t i o :
Low
Rotor Speed,
N , -
1.2%
H i g h
Rotor
Speed,
N 2
-
1.2%
Exhaust Gas Temperature
-
30"R
Fuel F low, W F - 2.5%
I t
ho
I d
be n o te d t h a t t h e a bove v a r i a t i o n s r e l a t i v e
t o
a n a v e r a g e p r o d u c t i o n
e n g i n e ar e f o r a n u n i n s t a l l e d e n g in e and do not r e f l e c t a i r f r am e i n s t a l l a t i o n
e f f e c t s , p ower e x t r a c t i o n , e n g in e sy ste m a i r b le e d , and e n gi ne d e t e r i o r a t i o n .
The f o l l o w i n g d i s c u s s i o n c o v e rs t h r e e g ro u ps
o f
p e r f o r m a n c e r e s u l t s :
o b s e r v a t i o n s f o r g ro un d e n gi ne t e s t s a t t h e F A A T ec hn ic al C en te r, f l i g h t t e s t
made
on
September 18, 1984 w i t h bo th
J e t
A
and AMK, and
C I D
o f
December 1,
1984
w i t h A M K o n l y .
FAA Technical Center T e s t s
I n o rd er
t o
e v a l u a t e t h e e n g i ne p e r fo r ma n ce t h a t c o u l d o cc u r i f h e f u e l
d e g r a d e r s h u t down d u r i n g f l i g h t , a JT3C-6 e n g i n e t e s t was c o n d u ct e d w i t h J e t
A
and undegraded AMK f u e l s a t t h e
F A A
T e c h n i ca l C e n t e r . D u r i n g t h e t e s t , f u e l
was
s u p p l i e d from a tan k us in g s tan dar d 6-707 boo s t pumps.
A s
p r e v i o u s l y
d e s c r ib e d , t h e JT3C-6 f u e l c o n t r o l was m o d i f i e d to i n co rp or a t e f i l t r a t i o n
f e a t u r e s m o r e i n l i n e w i t h t h e JFC25-10 C-7 c o n t r o l u s e d i n t h e JT3C-7 e n g i n e s
i n t h e
C I D
a i r c r a f t .
The engine appeared to p e r fo r m s u r p r i s i n g l y w e l l on AMK
t h a t was o n l y s l i g h t l y deg raded (F .R .=30 ) by t he 6-707 boos t pumps. S teady
s t a t e pe rfo rm an ce a t
EPRS
o f 1.5
t o
2 .5 a nd t r a n s i e n t re sp on se c a l i b r a t i o n s ,
w h i l e b u r n i n g AMK, i n d i c a t e d no s i g n i f i c a n t d i f f e r e n c e s f rom b a s e l i n e t e s t s
c o n d u c t e d w i t h
Jet A
f u e l . The o n l y o p e r a t i o n a l a b n o r m a l i t y n o t e d was t h e
immedia te p ressure r i s e i n c re a s e a c ro s s t he i ns tr um e nt ed f u e l f i l t e r l s c r e e n s
up
t o
a s te ad y, l i m i t e d v a l u e ( 5 ) as t h e f u e l was sw i t ched from J e t A to
undegraded AMK.
A s e c o n d t e s t was pe r fo rmed w i t h t he JT3C-6 eng ine us i ng a JT3C-7 f u e l c o n t r o l
s i m i l a r t o t h a t used on t h e C I D a i r c r a f t to e v a l ua te t h e o p e r a b i l i t y of t h e
JT3C-7 c o n t r o l s o n t h e t h e 6 -7 20 t e s t a i r p l a n e when o p e r a t i n g o n u nd e gr ad ed
AMK f u e l . NASA Ames-Dryden F l i g h t R es ea rc h F a c i l i t y r e p o r t e d t h e e n g in e
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o pe ra te d s a t i s f a c t o r i l y fo r 41
minutes on undegraded AMK f u e l . P os t t e s t
i n s p e c t i o n
o f
t h e f u e l c o n t r o l
s e r v o
f i l t e r
r e v e a l e d s i g n i f i c a n t a m o u n t s o f
s o f t ge l on t he downs t ream s i de o f t he sc reen . F i l t e r r a t i o m ea su re me nts o f
t h e f u e l i n d i c a t e d l e v e l s
o f
40
f rom
t h e
f u e l
tank and
1 1
f rom
l o c a t i o n s
downstream of t h e boost pumps.
F l i g h t T es ts
F l i g h t
t e s t
da ta was an a lyzed
f rom
t h e 6-720 a i r c r a f t o p e r a t i n g a l t e r n a t i v e l y
w i t h J e t
A
and
AMK
du r i ng f l i g h t 9 on Sep tember 18,1984 . F i g u r e 19 shows Je t
A
a nd de gr ad ed AMK t e s t p o i n t s p l o t t e d w i t h
a
t y p i c a l b a s e l i n e JT3C-7 e n g i n e
pe r fo rmance cu rve
f o r
a s t a n d a r d d ay a t s e a l e v e l
s t a t i c c o n d i t i o n s . The
per fo rmance o f t h e f o u r f l i g h t
t e s t
p o i n t s i n te rm s of t s p e e d , f u e l
flow
W F ) , and exhaus t gas tempera ture ( E . G . T . )
i s
h i g h e r t h e n t h e t y p i c a l J T 3 C - 7
sea l e v e l s t a t i c (S.L.S.) per fo rmance. Th is d i f fe re n ce was expec ted because:
1 )
t h e f l i g h t t e s t d a t a a re a t a pp ro xi ma te ly
0.3
Mn r a t h e r t h a n a t
S . L . S . ,
2)
t h e f l i g h t e n g in e s h ad un d o ub t ed l y d e t e r i o r a t e d due t o age and h igh-eng ine
t imes and
3)
t h e f l i g h t e ng in es c o u l d d i f f e r due t o i n s t a l l e d e f f e c t s ( a i r
b l e e d , p o we r e x t r a c t i o n e t c . ) . H ow ev er, t he s l o p e o f t h e f l i g h t t e s t d a ta
a gr ee s c l o s e l y w i t h t h e t y p i c a l
eng ine s l ope and t he re i s e s s e n t i a l l y n o
d i f f e r e n c e i n p e r fo rm a nc e b etw een
AMK
and Jet
A
f u e l .
12,000
10,000
a
I,
5
8000
2
5
2.
8 6000-
u
4000
2000
0
4
160
M
a
u
;
400-
3
Q:
5
2 1200-
v
c1
1.5
2 0 2 5
3.0
ENGINE PRESSURE RATIO, PT,/PT,
1 o
-
-
-
-
-
FLIGHT
TEST
DATA 9~18-84
ET A
MN=.3
A AMK MNZ.3
0 0 0 ~.5 3.0
I 1 0 1 5 2.0
ENGINE PRESSURERATIO. PT,IP~,
F i g u r e 1 9
F l i g h t T e s t Data Compared
t o
B a s e l i n e P e r fo r m a nc e
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C I D T e s t
Data taken f rom t h e 8-720 t e s t a
t h e C I D
t e s t
on December 1 , 1984
be fo re q round impac t . Th ree da ta
r c r a f t o p er a t in g
were ana lyzed
t o
p o i n t s r e p r e s e n t
s e l e c t e d f o r each o f t h e f o u r e n q i n es . The D o i n t s
w i t h AMK d u r i ng f l i g h t 15 o f
e v a l u a t e e n g i n e p e r f o r m a n c e
n g t h r e e p ow er l e v e l s w ere
r a n g e d from Mn 0.15 t o 0.25
a t a l t i t u d e s o f
2000
to
4500
fee t . The lowest p ow er p o i n t s e l e c t e d was r e c o r d e d
t h r e e seconds b e f o r e g ro un d i m p a ct . The r e s u l t s a r e p l o t t e d i n F i g u r e 20 and
were compared t o t h e d a t a ta ke n d u r i n g f l i g h t 9 and t o a t y p i c a l u n i n s t a l l e d
b a s e l i n e
for
a JT3C-7 en gin e. Th is
c om pa ris on showed n o s i g n i f i c a n t d i f f e r e n c e
i n e n g in e p er fo rm a nc e f o r C I D f l i g h t s 9 and 15.
The f o u r f l i g h t e ng in e s us ed
d u r i n g t h e
C I D
pe r fo rmed as expec ted .
NPICA L JT3C-7 ENGINE
PERFORMANCE (STANDARD
DAY SEA LEVEL STATIC)
10.000
U
FLIGHT TEST DATA
9-18-84
ET A MN I O
A MK MN= 0 3
v
m
V
6
CID FLIGHT 15
12-1-84
MN
0 15 TO 0
5
NG NO 1
NG NO 2
h NG NO 3
6 NG NO 4
I I
I -I
2 0 2 5 3 0
1 5
5000
10
ENGINE PRESSURE RATIO, P T ~ / P T ~
l 2 * O o 0 r
FLIGHT TEST
D A T A
9-18-84
/
PERFORMANCE (STANDARD
ET A MN 0.3
A
MK
MN o 3 WPICA L JT3C-7 ENGINE
I
DAY SEA L EVEL STATIC)
10,000
CID FLIGHT 15 12-1 84
MN 0.15 TO 0.25
v)
9 8000 ENG NO. 2
ENG NO. 3
0 ENG NO. 4
-
U
U
8 6000
I,
5
4000
I a
3
SECONDS
RFFORE IMPACT
600
/
YPICAL JT3C-7 ENGINE
PERFORMANCE STANDARD
DAY SEA LEVEL STATIC)
I
I 1
2 0
2 5
3.0
1 0 1.5
ENGINE PRESSURE
RATIO,
PT,/PT12
F igu re 20
F l i g h t a n d C I D T e s t Data Compared to Base l i ne Pe r fo rmance
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CONCLUDING
REMARKS
f u e l c h a r a c t e r i z a t i o n s and a re v i e w
o f
JT3C-7 eng,ne pe r form anc e a r e
documented for a B-720 t e s t a i r p l a n e o p er at ed on an a n t i m i s t i n g k er os en e
AMK )
f u e l .
The f o u r e n g i n e s w e r e m o d i f i e d b y a dd in g a f u e l d e g r ad i n g s y st em t o
i m p r o v e t h e
f l o w
q u a l i t i e s
o f
t h e f u e l i n t h e en g in e . These e v a l u a t i o n s w e r e
made
fo r
a g r o u n d t e s t e n g i n e a n d
for
t h e f l i g h t e ng in es , c u l m in a t in g i n th e
C o n t r o l l e d I m p a c t D e m o n s t r a t i o n ( C I D ) December 1 , 1984 . The fo l l o w in g r e s u l t s
w e r e o b t a i n e d :
o
Flow
c h a r a c t e r i z a t i o n t e s t s on de gra ded
AMK
f u e l sa mples i n d i c a t e d l e v e l s
o f d e g r a d a t i o n s a t i s f a c t o r y
for
t h e p l a n n e d s e a l e v e l
e n g i n e t e s t s a n d
s h o r t f l i g h t t im e, low a l t i t u d e m i s s i o n s of t h e 8-720 a i r c r a f t .
o
T h e o p e r a b i l i t y a n d p e r f o r m a n c e
of
t he JT3C-7 eng ines op er a t in g on
degraded
AMK
were comparable
to
r e s u l t s w i t h J e t
A
f o r
t h e f l i g h t
c o n d i t i o n s a s s e s s e d d u r i n g t h i s p r o g r a m .
o
The per formance
of
t h e f o u r f l i g h t eng ines d u r i n g f l i g h t and
t o
ground
i mp ac t was s a t i s f a c t o r y f o r t h e
C I D
m i s s i o n .
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APPEND I X
A
JT3C-7 ENG I NE
32
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v
v
m
.
3
l
.
-
a
L
L L
a
.
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- a . .
ORGDNAL PAGE IS
4 O
POOR
QUALITY
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ORlGlN L
P GE
IS
OF
POOR QU LITY
tu
Y
n
n
Q
aJ
aJ
>
I.
aJ
U
m
aJ
L
r
LL
35
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7
ORlGlM L
P GE
IS
O
POOR
QU LITY
m
W
a
_
c
-c
m
In
a
a
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A P P E N D I X
B-1
d r a i n o u t o f t h e t u b e . The t i m e r e q u i r e d for t he men i scus o f t h e f u e l
t o
pass
between the two r e f e re nc e marks on t he t u be was rec o rded . Th i s p roced u re was
PROCEDURE
FOR D E T E R M I N I N G
FILTER
R A T I O
38
I
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a i
39
a
U
.-
I
m
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A P P E N D I X 8-2
1 .
2.
3.
4.
5 .
6.
7.
PROCEDURE FOR D E T E R M I N I N G TH E T R A N S I T I O N VELOCITY
( A
Measure
o f AMK
D e g r a