NASA Contractor Report 179447

///-o/

/ 7:7¢0

The Effects of Compressor Seventh-Stage

Bleed Air Extraction on Performance of the

F100-PW-220 Afterburning Turbofan Engine

Alison B. Evans

Contract SA 258-21February 1991

NASANational Aeronautics andSpace Administration

https://ntrs.nasa.gov/search.jsp?R=19910010772 2020-05-18T00:29:05+00:00Z

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NASA Contractor Report 179447

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The Effects of Compressor Seventh-StageBleed Air Extraction on Performance of the

F100-PW-220 Afterburning Turbofan Engine

Alison B. EvansSan Jose State University Foundation1640 Holloway AvenueSan Francisco, CA 94132

Prepared forAmes Research Center

Dryden Flight Research FacilityEdwards, CaliforniaUnder Contract SA 258-21

1991

N/ ANational Aeronautics andSpace AdministrationAmes Research Center

Dryden Right Research FacilityEdwards, California 93523-0273

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ABSTRACT

A study has been conducted to determine the effects of seventh-stage compressor bleed onthe performance of the F100 afterburning turbofan engine. The effects of bleed on thrust,

specific fuel consumption, fan turbine inlet temperature, bleed total pressure, and bleed total

temperature were obtained from the engine manufacturer's status deck computer simulation

for power settings of intermediate, partial afterburning, and maximum afterburning; for Machnumbers between 0.6 and 2.2; and for altitudes of 30,000, 40,000, and 50,000 ft. It was found

that thrust loss and specific fuel consumption increase were approximately linear functions of

bleed flow, and, based on a percent-thrust change basis, were approximately independent of

power setting.

INTRODUCTION

Bleed air is often extracted from a jet engine's compressor for various applications during

aircraft flight. These applications include fuel tank pressurization, environmental control

system use, anti-icing systems, aerodynamic blowing, and driving compressors and suction

pumps. This extraction of bleed air introduces a performance penalty on the engine. Bleed

usually causes thrust to decrease, specific fuel consumption to increase, and engine turbine

temperatures to increase. All of these parameters have a strong effect on aircraftperformance.

For laminar flow control systems, bleed air from the engine compressor may be required for

powering suction pumps. The effects of such bleed need to be considered during the

conceptual design of laminar flow control systems.

Therefore, a study has been conducted at the NASA Ames Research Center's Dryden Flight

Research Facility to determine the impact of various levels of compressor bleed on the

performance of the F100-PW-220 afterbuming turbofan. Interstage bleed taken off at the 7th

stage was considered in this study, although 13th stage bleed is also available on the F100

engine. The Pratt & Whitney steady-state mathematical model, reference 1, was used to

determine the response of the F100-PW-220 engine to the various levels of interstage bleed

for this study. Bleed flow was varied from 0 to approximately 2.6 percent of compressor flow,and the changes in thrust, specific fuel consumption (SFC), engine temperatures and

pressures and engine turbine temperatures were examined.

This paper presents the results of the interstage bleed effects for a range of Mach numbers

from 0.6 to 2.2, for intermediate (maximum nonafterburning) power, partial afterburning, and

maximum afterburning for altitudes of 30,000, 40,000, and 50,000 ft for standard dayconditions.

NOMENCLATURE

DEEC

FN

FTIT

h

digital electronic engine controlnet thrust, lb

fan turbine inlet temperature, °Faltitude, ft

M MachnumberPLA power lever angle,deg

PCTBL compressor air flow used for bleed air, percentPTBI total pressure of interstage bleed, PSIA

S FC specific fuel consumption, lbm/hr/lbfTrBI total temperature of interstage bleed, °F

WBI seventh-stage compressor bleed air flow rate, lb/sec

Jl

111

DESCRIPTION OF EQUIPMENT

Engine Description

The F100-PW-220 engine, figure 1, is a two-spool low-bypass ratio-augmented turbofan

engine, built by Pratt and Whitney, West Palm Beach, FL. This engine consists of a 3-stage

fan, 10-stage compressor, combustor, 2-stage high-pressure turbine, and a 2-stage low-

pressure turbine. A mixed-flow augmentor exhausts through a balanced-beam nozzle. The

F100-PW-220 engine is equipped with a digital electronic engine control (DEEC), reference2.

For the F100-PW-220 engine, the compressor bleed may be extracted from the 7th stage

(interstage bleed) or 13th stage (customer bleed). The bleed source varies with Machnumber and altitude. At high power settings and speeds typical of supersonic aircraft, the 7th

stage bleed would normally be used. For this report all bleed air is assumed to be from the

7th stage (interstage) of the compressor, as shown in the inset in figure 1.

FI00 Engine Simulation Program (Status Deck)

Pratt & Whitney Aircraft Customer Computer Deck (CCD 1148-0.0) is a steady-state

mathematical model of the Pratt & Whitney F100:PW-200 engine, equipped with a DEEC

which utilizes DEEC PD 2.3 logic. This computer simulation closely approximates the F100-PW-220 engine that powers the F-15 and F-16 airplanes.

The function of this simulation program is to predict engine performance by using the

characteristics of the engine's eight components (fan, compressor, primary combustor, high-

pressure turbine and fan turbine, augmentor, exit nozzle, and fan duct). The values for

pressures, temperatures, and mass flows throughout the engine are determined through the

use of aerodynamic and thermodynamic equations. For this report, the amount of interstage

bleed was varied from 0 to the maximum capability, which was approximately 2.6 percent ofthe compressor airflow.

PROCEDURE

The engine simulation program was used to develop the effects of bleed on several engineparameters. Inputs to the engine simulation are Mach, altitude, power level angle (PLA),

and bleed flow rate. The Mach and altitude, along with the inlet recovery of the F-16 airplane,specified the engine face pressure and temperature for standard day conditions.

2

A baseline set of results were obtained from the engine simulation with no bleed. Computer

runs were then made with increasing levels of bleed, and the results were ratioed to the no-

bleed parameter values. Altitudes of 30,000, 40,000 and 50,000 ft were used. Mach numbers

appropriate to each of 3 power settings were used: M = 0.6 to 1.0 for a PLA = 83 °(intermediate power); M = 0.6 to 1.6 for PLA = 110 ° (partial afterburning), and M = 0.6 to

2.2 for PLA = 130 ° (maximum afterbuming).

Data are displayed with calculated data points shown with symbols and straight lines drawn

in between; some uncertainty may result as to where points should lie in between data

points.

Since the results are presented as percent changes, the results are applicable to other

airplanes powered by the F100 series engines.

RESULTS AND DISCUSSION

The effects of compressor interstage bleed flow (WBI) on the bleed pressure (PTBI) and

temperature (TI'BI) and three engine parameters are presented. The engine parameterswere net thrust (FN), specific fuel consumption (SFC), and fan turbine inlet temperature

(FTIT). These parameters were plotted as a function of Mach number and percent ofinterstage bleed (PCTBL) for flight conditions between 30,000 and 50,000 ft at PLA's of 83 °,

110% and 130 °. PCTBL values ranged from 0 to maximum bleed of approximately 2.6 percent.

Compressor interstage bleed flow rate values in lb/sec at various PLA, Mach number, and

altitude conditions are presented in the Table. The compressor airflow was computed by the

engine simulation and used to generate the percent bleed flows. These values can be used to

convert the percentage bleed flows to absolute mass flows if desired.

Fan Turbine Inlet Temperature. FTIT

Figures 2, 3, and 4 display F'ITr as a function of Mach number, PCTBL, and altitude at a PLAof 83 °, 110% and 130 °, respectively. At the lower Mach numbers, the DEEC compensates for

the bleed extraction by increasing FTIT to maintain the scheduled fan airflow. This increase

in FTIT is approximately 20°F for each additional percentage of bleed until the FTIT limit of

1720°F is reached. Once the temperature limit is reached, fan airflow, and hence thrust, will

decrease, as will be shown in later figures.

_ompre_or Interstage Bl_¢d Pressure

Figure 5 shows the effects of Mach number and bleed flow on PTBI for altitudes of 30,000,40,000, and 50,000 ft at PLA = 83 °. Increasing Mach number results in an almost linear

increase in PTBI. The first 1 percent of bleed results in a reduction of approximately 3 percentin PTBI, but the second percent of interstage bleed causes about an 8-percent reduction in

PTBI. For maximum bleed cases, approximately 15 percent of compressor interstage

pressure is lost.

Figure 6 showsthe effects of Mach number and altitude and PCFBL on PTBI for a PLA =

110 °. Results are very similar to the PLA = 83 ° data from figure 5.

Figure 7 shows the effects of Mach number and altitude and PCTBL on PTBI for PLA = 130 °.At the lower Mach numbers, the results agreewell with the data from the 83 ° and 110 °

PLA's, while at the higher Mach numbers above M = 1.8, PTBI increases less with increasingMach.

8

.C9mpressor Interstage Bleed Temperature

Compressor interstage bleed temperature, TTBI, is shown in figure 8 as a function of Machnumber, altitude, and PCTBL at a PLA of 83 °. TrBI increases with Mach number, and

decreases slightly with altitude, mostly due to the change in engine inlet temperature. As

can be seen, PCTBL had only a minor effect on TI'BL, at most approximately 10°F.

Effects at a PLA of 110 ° and 130 ° are shown in figures 9 and 10, respectively, and show the

same trends shown in figure 8. At altitudes of 50,000 ft, P_L effects TI'BI by only

approximately 2°F. Figure 10 shows that at high Mach numbers, "I'TBI values become high;at Mach 2.0, TrBI is above 700°F.

Net Thrust

The effect of Mach number, PCTBL, and altitude on change in net thrust (FN) is shown in

figure 11 at a PLA of 83 °. At flight conditions where the engine is operating below the FT_

limit (M = 0.7 at h = 30,000 ft, fig_ 11 a; M - 0.9 at 40,000 ft, fig ! 1 b; and M = 1.0 at 50,000 rft, fig 11 c), increasing bleed has only a small effect on thrust (approximately 0.2 percent loss

in thrust per PCTBL). Once the FTIT limit is reached, the effects of the engine control

system are quite significant and thrust decreases rapidly. For altitudes of 30,000 and 40,000

ft, reductions of over 6 percent are shown for maximum bleed cases-_ However at 50,_ ft,the FTIT limit is never reached and a decrease of only 0.5 percent occurs for maximum bleedcases. : _ ::_

Figure 12 shows the effects of Mach number, PCTBL, and altitude on FN at PLA = 110 °.

Results are somewhat similar to the PLA = 83 ° results. However, the afterburner fuel pump

uses engine bleed air, which results in an increased loss of thrust. This loss below the FTIT-

limiting Mach number is as high as 1 percent, and above the FTIT limiting Mach number, itexceeds 6 percent.

Figure 13 shows how FN reacts to Mach number, PCTBL, and altitude, at full afterburning,

PLA = 130 °. Results are similar to those in figure 12, except in the Mach 1.4 to 1.8 range,

where some augmentor segment changes occur. Again, the afterburner fuel pump requires

more bleed air so an additional reduction of FN occurs. FN is reduced up to 7 percent formaximum bleed cases.

Figure 14 displays percent change in _ as a function of PCTBL at h = 40,000 ft and PLA =

110 ° and 130 °. From this figure it can be seen that FN decreases linearly with increasing

4

=

g

Ib

v

bleed, and that the thrust loss is much greater at supersonic Mach numbers. At maximum

bleed, approximately 6 percent of net thrust is lost.

Percent change in net thrust was found to be almost independent of PLA setting. This can be

seen in Figure 15 where percent change in net thrust is plotted as a function of Mach number

at an altitude of 30,000 ft and a bleed extraction of 1 percent for a three power settings. The

values for percent change in net thrust are found to correspond fairly closely for each PLA

setting.

Specific Fuel Consumption. SFC

SFC is analyzed as a function of Mach number, PCTBL, and altitude in figures 16, 17, and 18.

Figure 16 shows that at a PLA of 83 °, SFC increases, on the average, 1.5 percent for each

percent of increased bleed. The largest percentage increase in SFC for this power setting

was approximately 4 percent, and this always occurred for maximum bleed settings.

In figure 17, the FTIT limit is found to affect the results again. Below this limit (about M =1.2) SFC increases approximately 0.7 to 0.9 percent for each percentage of bleed extraction,

and above this limit, SFC increases approximately 1.2 to 1.4 percent per percent of bleed

extraction. At 50,000 ft, SFC increases approximately 0.8 percent for each percent increasein PCTBL.

At full afterburner (fig. 18), SFC reacted similarly for altitudes of 30,000 and 40,000 ft. In

both cases, bleed had the biggest effect on SFC at M = 1.4, where each percentage increase

in bleed increased SFC by approximately 1.5 percent. Maximum bleed settings at this point

caused a 4.2- and 3.8-percent increase in SFC at altitudes of 30,000 and 40,000 ft,respectively. At 50,000 ft, bleed had a smaller effect on SFC. The most sensitive case is M

= 2.2; SFC increases by approximately 1 percent for the first percent of bleed, and by

approximately 1.3 percent for the second percent of bleed. The biggest increase in SFCoccurs at this Mach number for the maximum bleed setting, in which case SFC increases by

about 3 percent.

Figure 19 displays percent change in SFC as a function of PCTBL at 40,000 ft and PLA's of110 ° and 130 °. It can be seen that this relationship is linear, with a greater increase in SFC

for larger Mach numbers. An approximate 3.8 percent increase in SFC occurs at higher Machnumbers.

CONCLUDING REMARKS

A bleed study was performed on an F100-PW-220 engine using a Pratt & Whitney status

deck as a mathematical model. Interstage bleed pressure, interstage bleed temperature, net

thrust, specific fuel consumption, and fan turbine inlet temperature were examined as afunction of percent bleed at several flight conditions.

The DEEC was found to compensate for bleed extraction by increasing FTIT to hold a

constant fan airflow. This increase in FTIT was approximately 20°F per percent of bleed.

As Mach increased,aF'ITr limit of 1720°Fwasreached,after whichFTIT remainedessentially constant, and thrust decreased.

It was determined that compressor interstage pressure was decreased_ by approximately 3

percent for the first 1 percent of bleed, and decreased by approximately 8 percent for the

second percent of bleed. Maximum bleed settings resulted in about a 15 percent decrease inPTBI.

Compressor interstage bleed was found to have little effect on TTBI. For the most severe

cases (with maximum bleed), TTBI only had 10°F changes.

The reaction of FN to interstage bleed was found to be sensitive to the F'TIT limit. Below

this limit, FN had little reaction to bleed (about 0.2 percent decrease in FN per percent

increase in bleed). Above the FTIT limit, decreases in FN exceeding 6 percent occurred. For

the afterburning power settings, a larger decrease in FN, up to 7 percent, was seen.

For SFC increases, at PLA -- 83 °, SFC would increase on an average 1.5 percent for each

additional percent of bleed. For a PLA setting of 110% SFC is seen to increase 1 percent per

percent increase in bleed. Finally, for PLA = 130 °, SFC would increase on an average 1.2

percent for each additional percent of bleed.

Both thrust loss and SFC increases were approximately linear with bleed flow. On a

"percent thrust change" basis, thrust loss was found to be approximately independent of

power setting for the three power settings studied.

REFERENCES

Pratt & Whitney Aircraft Group, F100 Engine Model Derivative Program, Preliminary JTF

22B-36 Status Deck Users Manual for Deck CCD 1148-0.0, prepared for the U.S. Air Forceunder Contract 33657-79-C-054i by Pratt & Whitney, West Palm Beach, FL, March 1980. :

Burcham, F.W. Jr., L.P. Myers, and K.R. Walsh: "Flight Evaluation of a Digital Electronic

Engine Control in an F-15 Airplane," AIAA-83-2703, Nov. 1983.

v

b

6

Amount of Intersta__e ComDressor Bleed

v

v

PLA Bleed

(deg) %(PCTBL)

1%8 3 2%

2.61%1%

1 10 2%2.60%

1%130

0.61 0.;,I 0.81059 063 068118 127 1361.54 165 1770.591.181.54

WBI (Ib/sec)M

0.91 1.o1 1.2I0.73 0.781.46 1.541.89 2.00

0.681.361.77

0.77 0.881.53 1.731.97 2.23

1.4] 1.6J 1.61 2.2

0.99 1.o51.96 2.092.54 2.71

2%2.60%

0.591.181.54

0.77 0.99 1.10 1.101.52 1.96 2.16 2.181.97 2,53 2.79 2.83

(a) h = 30,000 ft.

PLA

(deg)

83

110

130

Bleed

%

(PCTBL)1%2%

2.61%1%2%

2.61%1%2%

2.61%

0.6I0.370.750.980.370.750.980.390.781.01

0.7I0.400.811.06

o.6I0.440.881.150.440.881.15

WBI (Ib/sec)M

o.91 1.ol 1.210.48 0.530.96 1.051.26 1,37

1.4] 1.61 1.61 2.2

0,53 0.59 0,66 0.711.04 1.18 1.31 1.411.35 1.52 1.70 1.83

i

0.53 0.66 0.75 0.761.04 1.31 1.47 1.511.35 1.70 1.90 1.95

(b) h = 40,000 ft.

PLA

(deg)

83

110

130

Bleed%

(PCTBL)1%2%

2.62%1%2%

2.62%1%2%

2.62%

0.61 0.71 0.81022 024 026045 049 053059 0.6,=0690.230.450.59

WBI (Ib/sec)M

0.91 1.0] 1.2J 1.4J 1.6I0.29 0.310.57 0.62

o.7,5,, o.810.26 0.31 0.36 0.40 0.430.53 0.62 0.71 0.80 0.85

0.69 0.81 ,0.93 1.04 1.11

1.61

0.23 0.32 0.40 0.450.47 0.64 0.80 0.890.61 0.83 1.03 1.16

2.2

0.460.911.19

(c) h = 50,000 ft.

Table- WBIasa functionofMach, PCTBLand PLA.

o

v

w

1720

l?OO

1680

1880

164.0

1620

1600

1580

......... : ......... : ......... : ......... : ......... : ......... --. .... ....: ......... .;

......... i ......... i ...... _,-!.f ...... _-..: ..... _ ...... i ......... i ......... •: : I ._ / : _ i : :: :f b": • : / : " : :

!// ,/./ ,,.." • .........] _

/ _/ .i" Y i ! :: i i

• .._ ....... ;,,- .... !. • _- ..... .: ....... : ......... : ......... :• * "o : : : : : : :

• • . . . . :s : ......

.... ;*"*: ........ : ......... : ......... : ......... i ......... i ......... ! ........../ : i _ : : :

/ ! ! :'-- ..... _BI..P'E_ -- IX/ : _ i .... _BLEEC_- 2X" ] _ _LEEC_, I NRX 13. fill)

(a) h = 30,000 ft

FTIT

(DEG 17)

1720

1700

1680

1660

1640

1620

1600

1580

1560

154-0

1820

1500

........ .__'_Y E_'[_." :-:" "O'X ..................._ , ,i ......... _I........._ _,.-" _--;._"l...... " "_'J

.-_...--..---..-_7BLEF--O,.,-,..2_ ........... , ......... t .... "- "'t',a,." L.,e :J*"_"i

._ ......... _ ......... _'/., . _. ...................._................., , :'*"- _-- _ .........i

........ i ......... i ......... I ......... I ",_"' ""j_ .... _ _" ""* V3'f ...... I" ........ !/ ,. i Ii | "_ ,

......... ; ......... _ ......... _ .... ;,, r. • i_, ..... ; _...'

• ,_.- .• .' ¢. _ ........ i........ I........................_ IoJ _-" ;.,_q-.... _ i !

I I / _, o I / i I !

.. .... i......... i•,_ ....... i ! t I I I• _ I I I I i i

(b) h = 40,000 ft

FTIT

(DEGF)

1700

1680

1680

164.0

1620

1600

1_80

1_60

15_0

1520

1500

Figure 2.

......... : _1_E£C_" "--'""OX" ' ......... : ......... :......... !......... ' ............... "..'BLEEC_, -- tli ; ; ;

""'--""'VBL-E_'[_. -- M_X t2. I_) : .'_......----"_..

..........".........i.........i.........J---_..---:, .........j.... ".•'_"...... i

......... ;......... i ......... i7:" "':i ......... ! ........ _'-'_.... ".'......... :i i ,,¢ ./ i _ ..... i i _2i _ / b/ _.. ..... .: ...i .....

......... _......... !'"'_" "_ .... .-_ i ........ __.---._'-T: ....... i

......... ; ...... ,,,,_. -..... ...... _,,r .... _ ...... ; ......... ;i _ .k" /i _ _ ,.' ,," .; i

....... _ _ - _ t _ !/_• " .: / i i i i i

....... _ .... P .... t ....... t ......... ; ......... I ......... t ......... I ......... I_" : o" _""

..... •.¢..i ....... i ......... i ......... i ......... ; ......... i ......... ; ......... ;

,.," • ! ; I ! ! l l

, .... , .... ! ; ; ; ;.E_ .68 .70 .75 .80 .85 .60 .S)5 t. O0

(c) h = 50,000 ft

The effect of Math and bleed air flow on FTIT,. PLA = 83 °.9

1740

1720

1700

15B0

166O

164-0

1120

1800

I.........!.........i.........i.........i.........i.........i.........i.........i.........i.........I i ......i.........i......i.........i,,....! ! .... -_Y- ......:_

::::14?:/F.........i.........!.........+.........!.........+.........+.........+.........i

•-/..... i......... i......... i......... i......... i......... i ....... _....... _....... " ""_

F ..... :.............................................................. I)t:E'EO" I,,_X la. 8Z)

(a) h = 30,000 ft

FTIT

(DEG F)

174-0

1720

1700

16eo

166o

164o

162o

1600

1580

1560

154.0

1520

I ......... t ......... ! ......... _ ......... ! ......... ! ......... I ......... ! ......... _ ......... ! ......... !

I I I ! I I I i

n i i )....; ;'"T,:',-:-" ; ! 1I

i i t__ _/)_ ) i : ) l s !

I I I _, _ /1 ! I I i i I I

i......... I......... i_'--r V'/ ..... I" ........ I......... !......... I......... l......... l......... I! • /I : | : i ) l i

I I / :(_ • _ ! ) s ) ) : il......... _...... I'_ .... "'/i ...... V ........ I......... I......... I......... I......... i......... ._

: ru • : 1 u s t ! t :I ., /,;," /i I ) _ ,: :/ : l | : l t ! :I......... ,-/I .+ ..l--.l ......... l......... _......... _......... , ......... )......... _......... ,i _ . I I ! s ;i : l i

-- I : : ; I t '; t z :I ....... _'I"_ "-_/-' ..... I......... l......... , ......... .,......... ) .................. _.........• i : 1 I s l ; :I /I ,, / I ; , , , , ,

-- i : l l I +. t l :+ lI.... ¢,z_..... _ .... + ....... ;....................................... ,......... _......... +11/-_" / i i i i I ! I i iI -- / l-- ": l 11 Is I s t l I i_ _ . _,,..,.._,'__ ....., ......... .;......... )......... ,......... _.........., ......... ,.........

: i I t : i 1 l IL'." t I l I , , , I , ,_'. • - 'r" ..........."__ _""II......... I ........................I"" I ......... _ _I. ,HI _0 ..am. -_OJl" .... ,I: l i i . ./," / i l i ; , 1-.... -.- BLEIO - IXI, / i I I I , p- .... gl_£1_O - ._Ir+ '/-"_ .... ";" ...... V" : r--'----- B_E'EO -. Mo_ ,_I / ! | + I ! I ! -- V "7 ...... ?

(b) h = 40,000 fl

IK)

+;

i

i0

FT[T

CI::)EGF)

1750

1700

1_50

1600

1550

1500

I ......... :' "I_.'EIZO' ' "_: • 01_'" ": ......... : ......... : ......... : ......... : ......... : ......... :..... :- - 6LI_E:D -. : s. :i[ : : : : : : :-----:--o___*'o : =z • : _ := _ _

I • . . _ .. - ..------':._....... =...... : -......... !......... ]....;_._: ._...._..._...: ........ _.._-.-: ......... !......... :..........

| , .,._- , _" . . ,._ , , : _..

I . /_, . .--. . _:: ;:

I ! /,I! .-"!'" L-.--""Y- : : : : :........... / ..... ,.,% ................................. : ....... : .... - . .

I 1:I ,"_ : : : : : ! : :/" # ...... "

V,"/ .....!:.........!.........!:.........i.....: : : :

• 6 .7 .8 .0 1.0 1.1 1.2 1 ..3

MIqCt,4

(c) h = 50,000 ft:_:=.-_

Figure 3. The effect of Mach and bleed air flow

1.4- 1.5 1.6

on b-TIT; PLA

-i

lI0°.

: i

ii

V

!

FTIT

(DEGF)

,7=0 ......... ! ......... !.... "

...........................

I /f/,'/ _ -: :" !I /._ ,'/ .: :" :" _ !

I," / ,.r/ i ::• " : ............... i ........................ 4.,.i......

1660 / i _ !

/ :: i-_ ..... BI-EED : IX :--_ .... BI..EEO -_ 21(

1620 ..... "........ " .......................... "-"B_.I='_'O ' " _ MAX (3.

1600

(a) h = 30,000 ft

FTIT

(DF.nF)

174-0 ......... , ......... = ......... : ......... ' ......... ! ......... ! ......... _ .........

I 720

1700

1880 ...........

I _/,;I _ i _ .... i ......... !

161S0 II ......... //_/" .'..'i_' i : _ ; ; =

I .. -/,/,__''" ........ ":

le2o I"/;" ; ................. .............................................

I#/

,.oop;... i i "5eo .............. g___ _ o_"IXI • / ; _ i -< .... BL-EEO ;

• " ._X ....

l_,eo [_L_EE Oi i " i i '_MAX (:R_. eli154-0 ; ; , , . r

(b) h = 40,000 ft

FTIT

(DEGF)

175o

172_

1700

167_)

1650

162_

1600

1575

1550

Figure 4.

......... ;......... i......... i......... !......... i- ...... i......... i......... i

; ____..-:........."......... : ....... ,: ......... ! ......... i ................ : ......... : ......... "

I.........i,.,'__: ......iI ,/./j / :- _, i i i !I ...... /,_,._'-'! ..... i

I /,/,_ / _ _ _ i i iI f,,'" "/'"'_'_: ......... : ......... : ......... : ......... " ......... ! .................. :!

P,I ,"/:.:,_.i i i i !Ix..;/. __' ._,.,,_l_ . ,,. .oz. '.

VI i • '- "''-"'................i....................... _ ......... _ ......... _..---...-_...-_._._._.g_ .-. _Rx

.8 .8 1 .O 1.2 1.4 1.6 1.0 2.0 2.2Ml=lr_ I-I

(c) h = 50,000 ft

The effect of Mach and bleed air flow on FTIT; PLA = 130 °.

11

PTBI

(PSIA)

....... BL..EEO ,- 2X :Bt..EEO -- _/lt :

-- NiqX (_l. lit) ::....... iIgl_.'* E I_ D

60 ...... . : : : . ; • ... ,.:• . . . - . . 06" •

: . : : : ...: ,-.:: .... : ......... :55 ......... : ......... : ......... : : ---_,,,v ._.- : _,

: : . _ s_ • :_,.- --: as _ : : _" .

• . : ea a . #.pe _.

tso ......... :" • __" "_ _"_ _ _ ,V, _ - :

4.o : :. .'_.. . . i ..... ..... ._,......... : ......... : ......... : ..............................

35(a) h = 30,000 ft

t_

it

i2

PTBI

(PSIA)

PTBI

(PSlA)

........ :_EL-t:_ ................

4O

_tS

:36

_4

32

_0

2B

26

24.

22

...... '- BLEED.' -- 1.1[ ._ l _ ; ;

.... .:-t_LE_D! -- :_Z : .. _......... : ......... i ......... i ....... _-"• _ ; #or. .; : : : : :

i ........ ! ......... ; ................... ! ......... : ........ :;,_:"'!• : : : _ ..." !

........................... • ; _"i -'-1-_

: ' : _'"-_ " - _ f ; _._ _"7.-......... ;.: . _ .. .;. ,, .._ .... _ .............................._.........:._._.,.. ........., : ___ .........

......... i ......... _.." ...... _...... _ !

........ . '.J ......... d. • _r : : •' " _' ' l i t !

"......... ..k.,,*. _ .... i • • - _._. r':-.• i ......... i ......... ! ......... .t......... ._''', ..... |

..... _ .' ........ • ; l ; t ;,..-" r l ! , • t " :, ; ! ! . : . .; _ l, i | l , l

(b) h = 40,000 ft

25 .......... "B_ EEO:" '--: ' "0_"" ......................................................... BLEED: -- tl :

8LEED_ m _I -BLEE[:_: -- MiqX |t. II¢1

2-_ .......... ' ...................................... iii_: ......... : ......... : ...... :

: : : : _.__._.'- -.'.t ° ! __.

'" i i __'-i ........ :.

_..._.- ....... :.

1 _ ," ...... • _-_;,--*'" • " : : : :

13.60 ._SE5 .70 _ .?'5 .80 .J5 .1_ .0_ I ._)0

I.t1_c I-4

(c) h = 50,000 ft

Figure 5. The effect of Mach and bleed air flow on PTBI, PLA -83 °.

|

!

i ti

• |

-___:

ie-

i

,,r')

PTBI

(PSIA)

90

I10

7O

8O

_0

30

......... : .... St.:F'I_D"W:" OX"" ": ......... : ......... : ......... : ......... ! ......... i ........ -_--et.EtZO --: tX : ! ! ! : _,,I ,__--.-.-;-- BLEED .-: :tit : • • • : _ ,,"- :

• . 1- • , . a,a" •------- ,t.Erso -:,Ax (_,.== : : : .,_..:_ ............. :......... ......... _......... _......... _......... i......... i.._'_1-" - _:;>°_i

......... :......... :......... :......... :............. __-! ...... !

: : ! i: " _2,__ ....... :.........•:......... .:......... _i/*:i........ .'_ ....... :_ _,,,A• : ..jr__.."" : _"'- :_I _ " : i !:

: - Im--_ ._.- : .: _ !

•.'*_' " I : : ; : " . .. ,..._ ....... : .........

...........................................................

(a) h = 30,000 ft

PTBI

(PSIA)

60

5_

50

4-5

4.0

35

30

25

2O

........... _r_'E_-o- 'or'"'! ......... !......... !......... _......... !......... V"_

..... :.--BLE_£D --- tic ! ! ! i _ "_"_.,"i_-_--gL.ISE:D --_ 2Z ! ! : ; _'_. ,,"- !

.... +_B,__-D..--_,_X C:a.era! ......... !......... i......... .::_t"-;_ ........

: : • : _.,_._ ..... _....... : ......... : ........................... : ......... : ...... _,'r.';_'"":.'_,,.- : _I-!

........: " i i:: ............. _..... _ .... i......... i

...... : : : .,/-._'.- ...,*" -.._- • ii :: : _" .: ,.."_ -I _ ! _ : .: : ,,f_. _...: ........ :

• . ; ......... : ...... , ....... _. ...... ,.t,_' ": ......... : ......... ,"......... •

...... !......... :

-'_.I _s : : : :. : : : :_1: I- _ " i i i _. _ : :_.:__ ......... "............ ! _ _ i ;

(b) h = 40,000 ft

PTBI

(PSIA)

3_

Figure 6.

3O

2_

2o

IO

............. t_r.:EEo ""- :'o_ ............. : ......... : ......... : ......... : ......... !_-!

.... _t.._,.-t:, -: == • : : : "-_,..:_.-_"----,,,_--_, -.,,A,, ,:.-=,: : : /_....-- _i--.: : ! : :-." : ..--_: .... 2......... : .... _._'- _ t_':• "...... i'" • • - • ..,,_,, . _-" . _,.- •

• : : : : :__-'" !f" :i I-:: : : : : t:_.-"j._ ..__- !: . . :j,_",,':_," :_I : ! •. . ; _ ...... : ......... :

........ :......... :......... :......... :"_ ........ i........ :

: : • .....,._¢,,': ...I _- : : ! i :

.........!........ .... .........

,,._ • i _ _ ; - ......

._ ......... : ................................................. ] ................... : ......... ]

._ .7 .8 .0 1.0 1.1 1.2 1.3 I ._" 1.5 1.6HI_Ckl

(c) h = 50,000 ft

The effect of Mach and bleed air flow on PTBI: PLA = 110 °.

13

PTBI(PSIA)

110

I O0

90

BO

?0

60

50

4-O

30

o,0 ..... oo,.,0..,o.t,,_,.. "0.I* .... *'''t*'''°°°'°t "°' ...... t ..... "'''t .... "°'*°

......... i ......... !......... i ......... ! ........._! ......... .:......... ! :...:_." " ! i ! ! o..i- --° i

............... =. • ; ..._ _..... : ..... : • .... 0.oo: ............ d_#t .. : ........ ,_ak .d. ,._._ r'. • •

......... : ......... : ......... : ..... _'_ ........ .

......... ; ......... . ..... __ .._ ...... ..• , j • ; : : . .

......... _...... _-.-i ......... !

,.... __'o" •_ -o_" •• it_E=EoL-.' t_x !i¢,__----et_E_E_O _ mt "_. _., ._.. i ......... i ......... i ......... : ..._----..t..=-.....x c2..x,.......

(a) h = 30,000 ft

_.qr

PTBI

(PSIA)

?o

e_

80

55

5o

4.o

35

30

2t5

20

.................. _......... ' ......... ! ......... ! ......... i _!......... ! ......... _". . ; ; ; ; •

......... ; ......... i ......... _.......... ; ......... _ ........ 2..;---_" _' ;.'; t"" • - • • • - -:

• .1 .... , . . . ! ........ ,a_', • _ ........ ._ .,.e_. ..... ;

....... : ; : #, : _°,_a_ ," :

..... : ......... ; ......... ; ......... _f- ........ i

......... :......... ......... ............ i

......... ......... .... ..... ,

• ., ,, . . • ; • ;

.__. . ._i........ __ . ._- ._. . . . _

. j ! : ; : --_ ..... Or-ErgO -_ tX i

,_ ...... i ......... i "i ...... i ....... :_-_."'"'-'eLEE[: ;.i'M_X (2. _X_

, . : ,, ; ; ; .; . ; , i. ;

(b) h = 40,000 ft

14

PTBI

(PSIA)

; i .: i ;

! ! ! .: !

......... ! ......... : ......... : ......... ! ......... : ......... i ....... ! _; ,.- "" ".'

......... : ......... : ......... . ......... : ........ _ ...... _..._ ........... ._ ._.,. •

: : ." "t -." _ i _ : :

20 ...... .t¢_ .... .."......... ::.:_\.LS_a"- 0=

• _.._ : ! ! -...... ._t._-r'i. t_," I _ ! ! ! ! ! .... '.-tst__,[_ - _,z

"l_, _ ....... : ............................. : ........... _ '-,-*.'-'l_t:._ i_Ca •,m MI=IXi ;

_ ! :

'10

.O .8

(;L 6x}

.0 1 .2 5,4 i .8i_ iml_ I.,,i

(c) h = 50,000 ft

1.1 2.0 2.2

Figure 7. The effect of Mach and bleed air flow on PTBI; PLA = 130 °.

TTBI

154.0

1130

82O

510

500

490

4110

4.70

4.60

450

........................... i .................. !......... :.................. i

......... I .................. l ......... _......... t ............... ._.'_._.z_'._4

................... : ......... : ......... i ......... : .... ,,C,._, ,",_ .,,¢T.... ;......... .;! [ : : ! ._.'f |

......... :.......... •.......... ,'-........ _ .... I ...... t

......... _......... " ........ __ .... ;." ....... I

: : o • • : •

: _< .......... ; ......... | ....... i ......... ; ......... : ......... :......... "Jr ._-'P ..... i/ _I.. .. %f i i i _ i i i"" __...:', ........ i

- • ..... : ......... : ......... :' ----'--+'.-BLEED' "--" ,MI_D_-,-Io'. • @ 4..Jl/.) ....

i i

(a) h = 30,000ft

s2o ......... !_'L:.i_i_6 "'--'""O'X'"i ............................. ! ......... : ......... :....... :BI_EI_I_ -- IX : : i J...... :_I_E:E:O -- 2_ : : : j,_j_.

500 .... :BL_E£O- _I:IX: t_.,_,:,} : :_"_'i_,,,_. i........._.........!.........!.........!....,.! .........!.........! .....}

,,o ..................._........._......... i..........._..-_ ......... :

,_o .........i.........!.....'"'i ......__ ...... i

4,,o ,__.._ i ........ i;_ .....................................i..............................

4.00

(b) h = 40,000 ft

490

4.80

4"70

,I.l$0

450

4.4-0

430

420

4-10

400

........... _....'1_"1.2I_' I_1_ "0'Ill ...................................................

-- -..,-__.-_,."_1.:.I L_[:)_"w,M f:tX tl. I1111 ........ : ......... " ......... _"!

......... i ......... : ......... _ ....... _ ........ _ ......... _.... .. ,.i ..... i....

......... i" ......... .,_:'_"_ ..... ii ......... i_......... i" ......... i" ......... i" ......... i.........i__ i .........i.........i..........i....... i........ i......

•60 .65 .TO .75 .80 .B5 .I)0 .I)5 I .O0M_ctCl-.l

(c) h = 50,000 ft,

Figure 8. The effect of Mach and bleed air flow on "Iq'BI: PLA = 83".

15

TTBI

(DEG F)

70O

eT_

eSO

625

eO0

575

525

500

4"7_

450.

| __L_Di**'I*'°'""" 0.*0,..,.i.,,o,ll. 0_I[ .... .;1'''''"'" ] ° °"''°'* !" °°'°''**l''''°'°''l°" °°''''*| | ! "'"''''" I

I .... ,'----BLEED '4' iX i i I i i iI .... ,-.,-.,-,.m.,IEE.D .. ,y, .,_Z. q ........ d ......... | ......... i ......... I ......... i ......... iI _t_. BLEED .,_ MAX! (_. 60Z) i ! | 1 ..,;

I.........,.........,.........;.........i.........;...................l.........I.........l...f_.,I i i i i i I , ! _ t

......... i ......... i ......... l ......... _..': ..... ; ......... i ......... , ......... ,..,,,:., ... i ......... *I i i i , i i ..... !i i ....... i ......... i ......... ! ....... i .... i _,P"..,.i.._.,.I ......... i

!......... i......... r • , i ! i _,."_-'i'" ...... iI ! i ' _.. i ..... i........ i'. ........ ; ......... l ......... ; ......... ; ......... l ......... ; ...... ; ......... l ......... s.........

l ; ; l ; i i l ; i

......... ; ......... : .......... . .... . ..........i i " _ i i i !"_'"..... i "

......... i.-_-"i ...... !I_1 1 t i ! i ! i i

_ i t i 1 i _...; ......... i

i I I I l I I I l

i i ; i i ; ; ; l ;

(a) h = 30,000 ft

TTBI

(DEG F)

650

62_

600

5"/5

55O

525

475

4,50

.4.2_

400

........ '",_L_D l :_t : • ,, : • • :• i ;

..... • -BLEED l _ I X I ] { I : ;

_ pl_._ % _. , ._ . : _ . . l l II I I Ill l l . l I ......... : l t . l i i l l , : ......... i ......... : ......... "

""---4- BLEED -- _MI:IX (_'. 6111¢) I ! I ! -,_:i , i _ _ t l i I l

........ i ......... i ......... i ......... i ......... i ......... i ......... i ......... i ........ : ....... i; ; ; i l ; ; ; _ ;l i l ; l i l ; ; ;

........ ; ......... ; ......... i ......... _......... i ......... l ......... l ................ ; ......... ;; ; ; ; i l ; i ; ;

; ; , , ; ; " l ; ;; i , ! ; ; ; i ; ;

; ; ; ; ; ; ; ; ;v ; ; " ........ i ......... ; ......... " ......... ;

.... 0,.,0,,.°.,....0 ........ . ......... , ......... . 0 • | .I I 1 1 i t ! I I

; ; ; _ i i ; ; i

........ ; ......... ; ......... ; ............ ; ......... ; ......... ;......... ; ......... ; ......... ;l ; ; , i l ; ; ;

: l I : 1 : : :........ , ......... I ................ I ......... I ......... I .... . .... 1.o.. ..... I ...... ...1 ......... I

; i i ; l ; ; i i l

........ ;.............. i ......... ! ......... i ......... i ......... ! ......... i ......... i ......... i

l i i ....... i ..... ; i ; ; ;

i ; ; I l l ; ; ; ;; ; :; ; i ; ; i ; ;

(b) h = 40,000 ft

16

TTBI

(DEG F)

e25 ............. B'L'E ED"" "-:-";."O= .............................. """ .............................

600

57_

550

525

500

4"/5

450

4_2_

4.00

Figure 9.

• 6 .7 .a _ .0 1.0 1.1 1.2 1.3 1.4 1.5 1.6

(c) h = 50,000 ft

The effect of Mach and bleed air flow on TTBI: PLA = 110 °.

J

85O

DO0

750

700

eO0

BSO

5OO

45O

. : ! ! !

..... _--BLEED -- Z_ . • ; : _-----_-BL.EEtD -, _X .: ! . _ !

.--...-...-:..,:,,_,:,,,p.... ,,_x.,_,. _o,, .... ;......... . ...._ .... i

........ _ ......... "......... _......... i ......... : ...... : ......... _ ......... ;

......... i ......... i ......... _ ...... : ......... " ......... _ ......... : .........

......... i......... !....... _......... !......... !......... !......... !......... .i

(a) h = 30,000 ft

TTBI

0BEG F_

800

750

700

650

600

850

BOO

450

4-00

.-.-..,-,.-.-.--_: 01_ E t_D ",," 'OX ................ _.-_o- tx ....................... _......... _......... i

--_-_ ;ig____

......... _......... _......... _ ...... :.......... • ......... ; ......... _ ......... i

......... _....... . ........ _ ......... _ ......... : ......... _ ......... : ......... . iiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiii(b) h = 40,000 ft

TTBI

(DEG F)

750

700

650

(_00

600

4.50

400

• " ............................ '--'---''-"-...,-'B'IL;.WEI_. _ M_X (2. 13X)

• 6 ,11 1.0 1.2. 1 .d_ I ._5M_CI-I

(c) h = 50,000 ft

1.8 2.0 2.2

Figure 10. The effect of Mach and bleed air flow on TTBI: PLA =130 °.17

PERCENT CHANGE

INFN

O

--2

_3

_B

_e

--7

i!i!!i!iiiiiiiii!iiiii iiii!ill(a) h = 30,000 ft

PERCENT CHANGE

INFN

0

--2

--3

_4

--E5

--6

--7

i " -:

_'.c,e_-i_ .......i........._:........i..............................PC'rBL -- M_X (2. eZ) i !

(b) h = 40,000 ft

PERCENT CHANGE

INFN

0

i1

--2

--3

_4

--E>

_e

--7

18

Figure 11.

.........!.........!.........:.........!.........i.........!.........i.........r.........., ...... ! ......... i ................... i ......... i ......... ! ......... - ......... i ......... i

: !

......... :.,,.,_..: ................... !................... _ ..............................

............. *'"I=¢ ........ i ......... _": ...... :.......... _ ................... i

-._x (=_Lsx) ! . _ ! !

.60 .6S .70 .75 .80 ,85 A)O .95 1.00MImC_

(c) h -50,000 ft

.05

The effect of Mach and bleed air flow on FN: PLA 83 °"

_v

PERCENT CHANGE

INFN

0 ......... : ......... _....................................... !......... _......... : ......... : ......... : ......... :

i iiiiiiiD6

--7

(a) h = 30,000 ft

PERCENT CHANGEINFN

--2

--3

--4

--5

--6

--7

• .4,) •_ v ",K

_P_TDU.. !-- 2 :pc'ru-- :- M_x c2_. az) i i

(b) h = 40,000 ft

o ........._........._........._........._........._........._....._.___!........._. .........

--2

PERCENT CHANGE -

INFN

--_ _ P'C: T_'l.;" • "_"" •1"X" : ......... : ......... :......... :......... :......... : ......... : ......... :_PC_'Bt- ,;- 2x _

--7• 6 .'] .8 .0 1.0 1.1 1.2 1 ...3 1.4- 1 .5 1.6 1,7

MF=i(:b4

(c) h = 50,000 ft

Figure 12. The effect of Mach and bleed air flow on FN: PLA = I10 °.

19

0

ml

--2

PERCENT CHANGE -3

IN FN _.

_6

--7

................... ::......... :_......... -;,_-t_---_ BI_E[Et__ _L:.IEI_"" '-;". X_X_t........ ! ......... iBLEED -- MI:I× (2 "_ St)

-iiiiii iiiiil(a) h = 30,000 ft

PERCENT CHANGE

INFN

(b) h = 40,000 ft

PERCENT CHANGEINFN

0

01

_2

--25

_4

--6

--'7• 6 .8 1.0 1.2 I .4. 1.6 1.8 2.0 2.2 2.4-

1_4mC I-I

(c) h = 50,000 ft

Figure 13. The effect of Mach and bleed air flow on FN: PLA = 130 °.

f >.,---

i

: !

2O

PERCENT CHANGE

INFN

O .............................................. :......... :......... : ......... :......... :......... :......... :......... _......... !......... i

_4

_5

m7

M 1. 2 : : : .......... : ......... :............... :•_'F_'" "'-"':"'Z":"'B ..................................... : _ "

(a) PLA = 110 °

ml

--2

PERCENT CHANGE -2INFN

D4

_6

_7

........i.........i..........i........_ .............i .......!

iiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiiilli!!!!!!!!!!!!!!!!!iiiiiiiiiiiiiiiiiIiiiiiiiiiiiiiiiiii!iiiiiiiiiiiiiiiiiiiiiiiiiiiM - i.4 ! : " : :......... _............

0 .2 .'¢ .6 .8 1.0 1.2 1.,4 1.(5 1.8 2.0 2.2 2.4. 2.6 2.BI=C-l-m L_

(b) PLA = 130 °

m Figure 14. The effect of bleed and M on FN: h = 40,000 ft.

21

PERCENT CHANGE

INFN

_'t .0

D1 .5

2O°

0 ....................................... 0 .... : "r>'t;.'_"" "-:-"" "a'S" 0_._ ....................

............................................. : ................... : ......... : ..........

Figure 15.

:5 :

: .... Y:_2: .......

The effect of PLA on; _icent change in FN;

h - 30,000 It, PCTBL - I%.

22

i

i

_=

i!

|

i

i

4-.0

,3.0

2.5

PERCENT CHANGE =.o

IN SFC : :1.5 ...... .... .:.'_:_._ ................ _')_ ..............................

_.o _.P_.'r._...-. izPeTroL -- H_X C_. eX) _

: ! :: ; ; : : •

.5

(a) h = 30,000 ft

_eoO ............................ :'," ...... : ........ : ................... : ......... : ......... :

2.5

PERCENT CHANGE _,.o ............................ ::......... ............................... :IN..,. SFC _"_ : _ _.... o - _ _ _

iili iiiiliiiiiiliiiiii i iilliiiiiiiiillii i iiiii1.0 • •

C i Pc'r@L M_x (:_. 6x) " i ......... : :

: . - :O

(b) h = 40,000 ft

PERCENT CHANGE

IN SFC

Figure 16.

..o ..................i.........;........_ ........::: .....g_ ........._._ .................. _......... "....................................... i ....................

: :

! : !3.o

0

2.5 ............................ : ............................................................

1._ ........ : ......... :. ......... : ........ _;_ ........ : ........ _).- .......... ) .... _ .........

_.o ...................................... i ................... ! ..............................!

!.5 .... O" "_" ' PCTB)" "_"'I_X ....... : ......... : ......... : ......... : ....... _ .........

:: OCTBL -- HRX (_J. 6_]o

• 60 .(55 .70 .75 .80 .05 .GO .95 1.00 1 .O5

(c) h = 50,000 ft

The effect of Mach and bleed air flow on SFC: PLA = 83 °.

23

4.0 ...................... .,,, ....................... 0 ....................... *''*" ." ......... : ......... : ......... :

iiiiiiii3.0

2.5

2.0

PERCENT CHANGE _._

IN SFC

.5

0

_,P'=_"_" _="_'I .........i............................._.........!........................ C) PCTBL :'O PCTBL i. ---MI::IX ("J. 6X)

! ! ! : :

(a) h = 30,000 ft

);

PERCENT CHANGE

IN SFC

4.0 ..............................................................................................................

i!!!!!!i_.0

1.5 ....... 7..............

,o i........!........ ........5 ...... O_ ..... P_TBE"!II'" "I'X! ......... ! ......... " ......... ,"............................. ! ..........

I"1' I::>CTBL !-- 2X_ : : :C_ PCTBL 11" M_,X 'i i i -: E

0

(b) h = 40,000 ft

_°_) ..,, ......................... : ............. , ................................................................. r

PERCENT CHANGE _.o

......... i ......... _......... i ......... _......... " ......... : ........ : ....... ! ......... ."......... _..........

; 0 0

.5 ...... (:7!..... p_'r_v-'r_'"rx! .... •.... g", .................................... !................... !C:]: I::)CTSL. !-- 12X! : : :-C?. I:)CTBL ;-- M_ F (12:. GR) i :

O.& .9 8 ._> _ .o _._ _ .2 _ .3 i._. _ ,5 _ .6 _ .7

MIMIC I.,I

(c) h = 50,000 ft

Figure 17. The effect of Mach and bleed air flow on SFC: PLA = 110 °

24

||

|I

w

PERCENT CHANGEIN SFC

*'" ......... ' ......... =......... i......... _......... i......... _......... _ ..................

3.5

!

I _PCTBL - 2X

(a) h = 30,000 ft

PERCENT CHANGE

IN SFC

.,.o ......... - ......... _......... _......... •......... _........................................

,.3..5

_.0

2.5

2.0

1.5

1.0

.5

0

_PG:'TE)IL"_"_¢ ....... ! ....................................... : ..........Pc'rBL ,- QXPCTBL - M, mx {_. 6X} !

(b) h = 40,00O ft

4"o0 ......... : ......... : ......... t ......... _..., ..... , ........................................

.._.0

2.5

PERCENT CHANGE =.o

IN SFC'iiiiiiii

• . : : •_,_ _..!......_...; ......... _................... ; ......... i ..........

_.o ........ i ......... _......... :......... i ......... ! ......... i ......... _...

"_ ..... 0 ..... mCT_"_"_X ....... ! ......... ! ....................................... ;-_e-----mCTBL _X : :

; _CTeL :• . _mx c_. sx) ;0

.6 .8 1.0 1.2 I .4 t .6 1.8

(c) h = 50,000 ft

2.0 2.2 2,,(.

Figure 18. The effect of Mach and bleed air flow on SFC: PLA = 130 °.

25

PERCENT CHANGE

IN SFC

PERCENT CHANGE

IN SFC

4-.0 ................... :......... :..................................................................... _................... :-................... !

M ,,: O. _;

_._ -----e-_-ia._ i ! _ i

2.0

1o5

1.0

.S ""il

0

(a) PLA = 110 °

4.O .2..;;.: ......... : ................... : ............ ;y.:.;,..,.._ ............................... • ..... •.............. _......... _..........

,_ M-o. 8 ; : /

2.0

1.0

05

00 .2 ._ .6 • B 1.0 1.2 1.4- 1.6 1.B 2.0 2.2 2.4. 2.6 2.8

Pc:'r'BL

(b) PLA = 130 °

#

%

Figure 19. The effect of bleed and M on SFC: h = 40,000 ft.,ip

J

26

_I,_/__.=A Report Documentation Page

1. Report No. 2. Government Accession No. 3. Reciplent's Catalog No.

NASA CR-179447

4. Title and Subtitle

The Effects of Compressor Seventh-Stage Bleed Air Extraction on

Performance of the F100-PW-220 Afterbuming Turbofan Engine

7. Author(s)

Alison B. Evans

9. Performing Organization Name and Address

San Jose State University Foundation, Inc.

1640 Holloway Avenue

San Francisco, CA 94132

12. Sponsoring Agency Name and Address

National Aeronautics and Space Administration

Washington, DC 20546-3191

5. Report Date

February 1991

6. Performing Organizalion Code

8. Performing Organization Report No.

H-1679

10. Work Unit No.

RTOP 533-02

11. Contract or Grant No.

SA 258-21

13. Type of Report and Period Covered

Contractor Report-Final

14. Spoosodng Agency Code

15. Supplementary Notes

This report was prepared during a summer intern program. NASA Technical Monitor:

EW. Burcham, NASA Ames Research Center, Dryden Flight Research Facility, Edwards,California 93573-0273.

16. Abstract

A study has been conducted to determine the effects of seventh-stage compressor bleed on the

performance of the F100 afterbuming turbofan engine. The effects of bleed on thrust, specific fuel

consumption, fan turbine inlet temperature, bleed total pressure, and bleed total temperature were obtained

from the engine manufacturer's status deck computer simulation for power settings of intermediate, partial

afterbuming, and maximum afterbuming; for Mach numbers between 0.6 and 2.2; and for altitudes of

30,000, 40,000, and 50,000 ft. It was found that thrust loss and specific fuel consumption increase were

approximately linear functions of bleed flow, and, based on a percent-thrust change basis, were

approximately independent of power setting.

17. Key Words (Suggested by Author(s))

Engine bleed

Engine performance

F100 engineThrust loss

18. Dislribution Statement

Unclassified-Unlimited

19. Sectary Claesif. (of this report)

Unclassified

20. Security Classif. (of this page)

Unclassified

21. No. of Pages

29

Subject category 07

22. Pd_

NASA FORM 1626 OCTU For sale by the National Technical Informaffon Service, Springfield, Virginia 22161-2171

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