Preliminary Evaluation of Turbine Performance with Variable-Area Turbine Nozzles in a Turbojet Engine

Copy RM E52J20

NACA

RESEARCH MEMORANDUM

PRELIMINARY EVALUATION OF TURBINE PERFORMANCE WITH VARIABLE-AREA TURBINE NOZZLES IN A TURBOJET ENGINE By Carl E . Campbell and Henry J. Welna Lewis Flight Propulsion Laboratory Cleveland, Ohio

NATIONAL ADVISORY COMMITTEE

FOR AERONAUTICS

WASHINGTON

Ma y 20 , 1953

Declass i fied A ugu st 19, 1960

r

NACA RM E52J20

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS

RESEARCH MEMORANDUM

PRELIMINARY EVALUATION OF TURBINE PERFORMANCE WITH VARIABLE-

AREA TURBINE NOZZLES IN A TURBOJET ENGINE

By Carl E. Campbell and Henry J. W e lna

SUMMARY

The performance of a two-stage turbine with variable-area first-

sta ge turb i ne nozzles wa s determined in the NACA Lewis altitude wind

tunnel over a range of s i mulated altitudes from 15,000 to 44,000 feet

and engine speeds fro m 50 to 100 percent of rated speed. The variable-

area turbin e nozzles us ed i n this inves t igation were primarily a test

device for compressor re s earch purposes and were not necessarily of

optimum aerodynamic des ig n. The results of this i nvestigation are indica-

t i ve of effects of t urb i ne-nozzle-area variati on on turbine performance

within the operating ran ge allowed by the engine. The variable-area

turbine nozzles wer e f o und to be mechanicall y reliable and to have negli-

gible leaka ge l o ss e s. Increasing the turbin e -nozzle-throat area from

1.15 to 1.67 square fee t increased the corrected turbine gas flow or

effective turbin e nozzle area about 10 percent. At a given corrected

turbine speed and turbin e pressure ratio, chan g ing the turbine nozzle

area fro m 1.30 to 1. 67 square feet lowered the turbine efficiency

3 or 4 percent. The eff e ct of increas i ng the t urbine nozzle area from

1.15 to 1.67 square f ee t (decr e as i ng the turnin g angle about 7~O) would

be to lower the turbin e e fficiency abou t 5 or 6 percent.

INTRODUCTION

Analyses such as that g iven in reference 1 i ndicate the performance

and operational advantages to be gained by utilization of variable-area

turbine nozzles in turbo j et engines. When combined with a proper speed

control, the variable turbine nozzle can greatly i ncrease the thrust

capability of superso ni c turbojet engines because of increased flexi-

bility in matching of the compressor and turbine over a wide range of

flight cond i tions. Furt h ermore, potential improvements in specific fuel

consumption, particularly at thrust values below rated thrust, are possi-

ble for engines equipped with both variable-area turbine nozzles and

variable-area exhaust nozzles (reference 1). In both these analyses, it

was assumed that turbine efficiency was not affected by changes in the

area or angle of the turbine nozzles. However, aside from analytical

treatment of the problem, there exists at the present time a lack of

NACA RM E52J20

experimental data on the performance of variable-area t urbine nozz l es

operating as integral components of full-scale t urbojet engines. Com-

plexity and mechanical reliability have been the main deterrent factors

in obtaining experimental data and in the utilization of variable tur-

bin~ nozzles in present turbojet engine designs.

During a study of the surge characteristics of a turbojet engine

fitted with variable-area first-stage turb i ne nozzles in the NACA Lewis

altitude wind tunnel, it was possible to obtain some preliminary data

on the effect of these nozzles on the performanc e of the two-stage tur-

bine. The effect of the variable-area turbine nozzles on the efficiency

and g as flow characteristics of the turbin e are presented herein. The

variable-area turbine nozzles investigated in this study were intended

pr i marily to provide a variable compressor p ressure ratio independent

of engine speed and turbine-inlet temperature f or compressor research

purposes; therefore, the aerodynamic design of the nozzles was not

necessarily optimum. Furthermore, the turbine ro t ors and t he second-

sta ge stator were designed for fixed-area first-sta ge nozzles. The

experimental results obtained in this investigation, therefore, do not

represent the best turbine performance obt a i nable wi t h variable-area

tur bi ne nozzles, but serve instead as a preliminary indicator of general

performance and mechanical proble~s.

Corrected turbine gas flow and turbine e ffic i ency are presented as

fu n ctions of corrected turbine speed and turg ine pressure ratio to show

the e ffects of turbine nozzle area and nozzle an g le on turbine perform-

ance. The turbine efficiency obtained with the o ri g inal fixed turbine

no zz l es is compared with the turbine efficiency obtained with the vari-

able turbine nozzles at a position correspond i ng to approximately the

sa me throat area and turning angle . All turb i ne performan ce data obtained

wit h the variable turbine nozzles are present ed in numerical form in

table I.

INSTALLATION AND INSTRUMENTATION

Engine

The engine was mounted on a wing sect i on w hich extended across

t he 20-foot-diameter test section of the alti t ude wind tunnel (fi g . 1).

Dry refr i gerated air was supplied to the en g in e fr om the tunnel make-up

a i r system through a duct connected to the en gine inle t . Manually con-

trolled butterfly valves in this duct were us e d to adjust the total

pressure of the refrigerated air at the en g ine i nlet to correspond to

the desired flight condition , while the static pressure i n the tunnel

test section was maintained to correspond to the desired altitude. A

slip joint with a frictionless seal in the duct permitted the measure-

ment of thrust a nd installation drag with the tunnel scales.

NACA RM E52J20

The engine used in this investigation was a J40-WE-6, which had a

sea-level rating of 7500 pounds of j et thrust at an engine speed of

7260 rpm and a turbine-inlet temperature of 1425 F. At this rating,

the compressor pres sur e ratio was about 5 .0 and the engine air flow was

140 pounds per second. A cro ' ss-section of the engine is presented in

figure 2 showing the main components of the engine which included an

eleven-stage axial -fl ow compressor, a single-annulus basket-type com-

bustor, a two-stage turbine, and a clam shell -t ype variable-area exhaust

nozzle. The engine was equipped with an electronic control that varied

engine fuel flow and exhaust -nozzle area to maintain a schedule of

turbine-outlet temperature and engine speed.

The original J40-WE-6 engine was modified before the investigation

reported herein by replacing the compressor-outlet straightening-vane

assembly with a two-element mixer-vane assembly, by using a slightly modi-

fied combustor basket, and by replacing tbe first-stage fixed turbine noz-

zles with a variable turbine-nozzle diaphragm. The original control was

also modified to permit independent control of engine speed and exbaust -

nozzle area.

Turbine

Both first- and second-stage turbine disks were solid steel and had

an outer diameter of 21.90 inches. The first-stage rotor disk had

62 high-temperature-alloy blades fitted into its outer rim (fig. 3(a))

and the second stage contained 32 blades of the same material (fig. 3(b)).

All turbine rotor blades were 5.50 inches in length; the turbine tip

diameter was thus 32.90 inches and the hub-tip radius ratio was 0.666.

The radial tip clearance for the turbine rotors was 5/32 inch.

The first-stage or variable turbine-nozzle diaphragm consisted of

56 high-temperature -all oy vanes which could be rotated between an inner

and outer.shro~d (figs. 4 (a) and 4(b)). All vanes were rotated simul-

taneously by an actuating mechanism similar to the one shown schematically

in figure 5. The single actuating shaft extending through the engine

outer skin was actuated by an externally mounted worm-gear drive. Chang-

ing the turbine-nozzle vane angle varied the nozzle throat area and also

the angle that the fluid is turned in passing through the nozzles. Mid-

vane cross sections of two adjacent turbine nozzle vanes are shown in

the open and closed positions in figure 6 . The solid-line section shows

the vanes in the open position corresponding to a geometric throat area

of 1.67 square feet and a turning angle at the throat of approximately

54.5 • The dashed-line section corresponds to the closed position with

a throat area of 1.15 square feet and turning angle of about 620. The

original fixed turbine nozzles, for which the turbine rotors and second-

stage nozzles were designed, corresponded closely to the variable turbine-

nozzle setting that provided a throat area of 1.30 square feet and a

turning angle of about 59 •

4 NACA RM E52J20

The second - stage or inter stage stator consisted of 60 high-

temper a ture-alloy vanes welded to an inner and outer shroud with a fixed

nozzle - throat a rea of approximately 1.81 square feet. The annular

passage through the turbine from first-stage nozzles to turbine outlet

had approximately constant inner and outer diameters; the unblocked

annular area was about 3.4 square feet.

Instrumentation

Stations at which instrumentation was installed within the engine

for measuring pressures and temperatures are shown in figure 2. The

number of total and static pressure tubes, static pressure orifices, and

thermocouples installed at each measuring station is shown in tabular

form in this figure. Schematic sketches of the instrumentation at the

cowl inlet (station 1), compressor outlet (station 4), turbine inlet

(station 5), and turbine outlet (station 6) are shown in figure 7. Fuel

flow was measured by calibrated rotameters and engine speed was measured

by a stroboscopic tachometer.

Procedure

Data were obtained at altitudes of 15,000, 30,000, 40,000, and

44,000 feet at various flight Mach nQnbers from 0.14 to 0.62. Extensive

performance data were obtained at an altitude of 30,000 feet and a flight

Mach number of 0.62. At this flight condition, the variable turbine

nozzles were set at five different positions and at each nozzle position

the engine was operated at six different speeds from 3630 to 7260 rpm

(rated speed). At each turbine-nozzle setting and engine speed, the

exhaust nozzle was varied from the wide-open position to full closed,

or until limiting turbine temperature was approached, to extend the range

of turbine pressure ratio and corrected turbine speed. The ranges of

turbine pressure ratio, corrected turbine speed, turbine nozzle area,

and engine speed covered at this flight condition are shown in the follow-

ing table: Engine speed, . .

rpm . . . . . .

. . . 3630 to

Measured turbine-nozzle-throat area, sq ft

. 1.15 to 1.67

Turbine pressure ratio

1.57 to

3.00

Corrected turbine

speed, rpm . . .

2663 to 4407

The symbols and methods of calculation used to determine the turbine

performance a re given in the appendix.

NACA RM E52J20

RESULTS AND DISCUSSION

Inasmuch as the primary object is to show the effect of turbine

nozzle area on turbine performance, curves are shown only for an alti-

tude of 30,000 feet and a flight Mach number of 0.62 where the most

extensive investigation was made. Data obtain ed at all of the flight

conditions investigated are presented in numerical form in table I.

Corrected Turbine Gas Flow

The variation of corrected turbine gas flow with corrected turbine

speed for all five turbine nozzle areas is shown in figure 8 for an alti-

tude of 30,000 feet and a flight Mach number of 0.62. Although turbine

pressure ratio is not a dire ct function of corrected turbine speed, lines

of constant turbine pressure ratio have been superimposed to indicate

approximately the gene ral increase in turbine pressure ratio with in cr eased

corrected turbine speed at each turbine nozzle area. For each of the five

nozzle areas, the corrected gas flow increased with corrected turbine

speed to a maximum value and was unaffected by further increases in cor-

rected turbine speed or turbine pres sure ratio. Failure of the corrected

gas flow to increase at high c or rec ted turbine speeds (and high turbine

press ure ratiOS) is attributed to choking of the flow at some station

within the turbine. The turbine pressure ratio for choking varied from

about 2 . 6 at a turbine noz z le area of 1.1 5 square feet to about 2 .2 at

an area of 1.67 square feet . Ho we ver, these values of turbine pressure

ratio at the transition po int between choked and unchoked flow a re very

approximate because of the d ata inaccuracy in the low range of turbine

pressure ratios.

The m~ximum corrected turbine gas flow (choked conditions) obtained

at each nozzle area is shown in figure 9. This curve is also a measure

of effective turbine-nozzle throat area inasmuch as corrected turbine

gas flow is directly proportional to effective area when the nozzles are

choked. Over the range of actual turbine nozzle areas frO"TI 1.15 to

1.67 square feet, the effective tur bine nozzle area varied from 1.13 to

1.25 square feet for an ef fective area range of approximately 10 percent .

It is apparent that the effective and measured areas are nearly equal at

small area settings of the nozzles but the effective area is considerably

smaller than the measured area at large area settings. This indicates a

reduction in nozzle flow coefficient (defin ed as the ratio of effective

area to measured area) from about 0.98 to 0.75 as the nozzles are opened.

This large reduction in indi cated flow coefficient may be caused by chok-

ing at so~e station within the turbine other than the inlet nozzles.

However, inasmuch as interstage pressures and tempe ratures were not meas-

ured, the location of the choking station within the turbine could not

be determined with cer tainty.

NACA RM E52J20

Turbine Efficiency

The turbine efficiencies obtained with all five turbine nozzle areas

at an altitude of 30,000 feet and a flight Mach number of 0.62 are shown

in figure 10 as a function of corrected turbine speed. The maximum tur -

bine efficiency obtained was 0.87 with the smallest turbine nozzle area

and a high corrected turbine speed. The minimum turbine efficiency was

about 0.70 with the largest nozzle area and a low corrected turbine speed.

In general , turbine efficiency increased with corrected turbine speed for

all turbine nozzle areas and was lowered by increasing the turbine nozzle

area (decreasing the nozzle turning angle) at a given corrected turbine

speed. These general effects, however, are not clearly separated in fig-

ure 10 because the effects of turbine pressure ratio have not been accounted

for.

In figures ll(a) and (b) to 15(a) and (b), operating lines of turbine

pressure ratio and turbine efficiency are shown as functions of corrected

turbine speed for each engine speed and turbine nozzle area. Although

turbine efficiency is not a direct function of engine speed, lines of

constant engine speed have been faired for the turbine efficiency data

for the purpose of obta ining cross plots. The cross plots of turbine

efficien cy against corrected turbine speed for constant values of turbine

pressu re ratio obtained from parts (a) and (b) of figures 11 to 15 are

shown in parts (cl of these figures. At a constant t urbine pressure ra tio , turbine effic iency increased with increased corrected turbine speed.

This tr end occurred at all values of constant tur bine pressure ra tio for

which cross plots could be obtained at each turbine nozzle area. The

maximum range of corrected turbine speed obtainable at a constant turbine

pressu re ratio was about 200 rpm and the average increase in turbine

efficien cy for this increase in corrected turbine speed was about 4 per -

cent . However, the rate of increase in turbine efficiency with increased

corrected turbine speed was great er at the lower values of constant tur-

bine pre ssure ratio. At a given correct ed turbine speed, turbine effi-

ciency increased with reduced tu rbine pressure ratio, but the corrected

turbine speed could be maintained constan t only for a very small range

of turbine pressure ratios.

The effect of changing turbine nozzle area and turning angle on tur-

bine effic-iency at a given corrected turbine speed and turbine pressure

ratio is shown in figure 16. The symbols, which represent cro ss - plotted

data points rather th an actual data points, have been included to indi-

cate the accuracy of the cross-plotted data as well as for distinguishing

betwe en turbine nozzle areas. In all cases where a comparison could be

made at the same turbine pressure ra tio and corrected turbine speed, the turbine effi ciency was lowered by increasing the turbine nozzle area.

Changing the turbine nozzle area from 1.30 to 1.67 square feet at con-

stant values of corrected turbine speed and turbine pressure ratio

NACA RM E52J20 7

lowered the turbine efficiency by 3 or 4 percent. It is probable that

the reduction in turbine efficiency over the complete range of turbine

nozzle areas (decreasing the turning angle about 72 ) would not be more

than about 5 or 6 percent in the region of high corrected turbine speeds

and turbine pressure ratios.

I

j

A comparison of turbine efficiencies obtained with the original

fixed turbine nozzles and with the variable turbine nozzles at a corre-

sponding area setting and at the same flight conditions and engine speed

is shown in figure 17. 1he slightly lower turbine efficiency of about

1 percent (which is less than the data accuracy spread) obtained with

the variable turbine nozzles indicates that the leakage losses with the

variable nozzles were very small.

Mechanical Reliability

The variable-area turbine-nozzle diaphragm was installed in the

engine during approximately 240 hours of engine operation and only minor

mechanical difficulties were encountered during this period. Although

the turbine nozzle area was not varied frequently during the part of the

engine investigation reported herein, a great many changes in nozzle area

were made during other parts of the investigation. The nozzles were at

low physical loading conditions most of the time because most of the

investigation was conducted at high altitudes, but inasmuch as a large

part of the total operating time was at military speed and temperature,

it is felt that these tests were a good indication of variable turbine

nozzle life. Calibrations of turbine-nozzle-throat dimensions versus

indicated nozzle setting showed good reproducibility of turbine nozzle

areas.

CONCLUDING REMARKS

The variable-area turbine nozzles were found to be mechanically

reliable and to have negligible leakage losses. It was possible to

achieve a variation in corrected turbine gas flow or effective turbine

nozzle ~rea of about 10 percent by use of these variable turbine nozzles.

At a given corrected turbine speed and turbine pressure ratio, changing

the turbine nozzle area from 1.30 to 1.67 square feet lowered the turbine

efficiency by 3 or 4 percent. The effect of increasing the turbine noz-

zle area from 1.15 to 1.67 square feet (decreasing the turning angle

about 72 ) would probably lower the turbine efficiency about 5 or 6 percent.

Lewis Flight Propulsion Laboratory

National Advisory Committee for Aeronautics

Cleveland, Ohio

8 NAC,. __ " E52J20 APPENDIX - CALCULATIONS Symbols The following symbols are used in this report: A cross-sectional area, sq ft g acceleration due to gravity, 32.2 ft/sec H enthalpy of air or gas mixture, Btu/lb N engine speed, rpm P total pressure, lb/sq ft absolute p static pressure, lb/sq ft absolute R gas constant, 53.4 ft - lb /l b-oR T total temperature, oR Ti indicated temperature, ~ V velocity, ft/sec Wa air flow, lb/sec W fuel flow, lb/hr f Wg gas flow, lb/sec ~ thermo c ouple impact recovery factor, 0.85 y ratio of specific heats for gases 5 pressure correction factor, P/2ll 6 (total pressure divided by NACA standard sea-level pressure) ~ adiabatic efficiency

I

e temperature correction factor, rT/(1.4)(5l9), (product of y

and total temperatu re divided by produ ct of y and temp era- ture for air at NACA standard sea-level conditions)

i

p density, slugs/cu ft -----_ . _- --

- - -- -- - - ---~ .-- -- -~ - --- -- - -- ~ -

NACA RM E52J20 9

Corrected parameters:

corrected turbine speed) rpm

N/..J85

8 corrected turbine-inlet temperature) oR

T5/ 2

W -y'e5

g

corrected turbine-inlet gas flow) lb/sec

°5(Y5/1.4)

J

corrected turbine enthalpy drop) BtU/lb

~/85

Subscripts:

a air

g gas mixture

t turbine

cowl inlet

2 compressor inlet

4 compressor outlet

5 turb ine inlet

6 turbine outlet

Methods of Calculation

Total temperatures were calculated from thermocouple indicated

temperatures with the equation

T = (1)

NACA RM E52J20

Air flow. - Air flow was determined from pressure and temperature

meas urements at the cowl inlet (station 1) by use of the equation

Gas flow. - Gas flow was calculated from fuel-flow measurements and

cowl-inlet air flow as follows:

(3)

. Turbine-inlet temper a ture. - Turbine-inl et temperature was deter-

min ed from the enthalpy and fuel-air ratio at the turbine inlet by use

of temperature-enthalpy tables. Turbine-inl et enthalpy was calculated

from the following equa tion which assumes that the turbine enthalpy drop

equals the compressor enthalpy rise:

(4)

Turbine efficiency. - The turbine a diabati c efficiency was deter -

mined from the following equation: T6 1 -- T5 = .~ . J,:

Tl (5)

t

l

Yt-

--

1 - (::) ;y

where is the average value of Y between stations 5 and 6.

--~ -- ~ .--- -- --- -- --~ --- ----

NACA RM E52J20 11

REFERENCES

1. Silvern, David H., and Slivka, William R.: Analytical Investigation

of Turbines with Adjustable Stator Blades and Effect of These Tur -

bines on Jet-Engine Performance. NACA RM E50E05, 1950.

t-' N

~ ;J:> ~ tr:l (Jl N Y N o

3 3 9 8 5 9 36 76 44 3 6 19 03 T5 T6 262 245 26 22 21 25 224 215 205 211 186 225 106 214 190 176 199 164 161 161 151 139 098 219 214 ----- 1 . 1.25 1 . 1 . 2 3 1 1 . 1 . 2 4 1 1 . 2 1 . 1 . 1 . 1 . 23 6 1 . 1 . 1 . 1.190 1 . 1.192 1 . 1.1 1.169 1.167 1.15 1.157 1.148 1 . 1 . 0 9 8 1 . 0 9 8 1 . 2 1.224 1.221 1.209 1 . 1 . 1 . 1 . 1 .

1.2 1 . 2 1 . 240 1.201 1 . 1.221 1.181 1.176 1 . 1 . 1 . 1.137 1 . 1.100 1 . 1 . 23 0 1 . 1 . 1 . 2 3 2 3 3 4 3 f 600) 90 39 W 11 010 0126 0140 0085 0125 0105 0138 007 0086 0100 012 0068 0080 0097 0118 0122 0058 0065 0075 008 009 0059 0074 0097 0130 0105 0115 0134 0078 0094 0112 0129 0148 0111 0130 0062 0082 0090 0094 0119 0125 01 .0115 . . . . . 0 . . . . . .0109 . . . . . . . . . . . . .0068 . . .0110 . . 0 0 . . . . . . . . .0068 .0082 . . .0068 . . .0078 .0094 . . .0060 .0111 . . .

------ 0 .

a , 1{ 3 W

~

6.

0 9 - 7 ) 42 15 88 76 13 15 95 45 15 25 42 78 72 l.4 86 55 28 51 47 51 31 39 59 44 3 7 50 41 48 91 81 20 44 ( 1'5 .3 . 53 . . . . 34 .39 . . . . . . . . . . 75 . . . . . . .3 . 21 . . 64 . 74 . . . . . . . 73 . 2 3 .33 .3 . .9 . .

, 5 1 ~ ( ----- 56 56 56 57 55 56 ----- g 5 56 56 51 55 55 56 55 55 54 56 55 53 58 55 54 54 53 . 53 . 52 51.91 51.42 60 ----- 61.02 60 60 60 60 60 60 60. 60.14 60 60.85 60 60 60 60 58 59 58 ---- 55 54 63.35 63 63.37 63 W 49 30 00 42 T5 808 'G2 393 02 ("R ) ---- 1640 1745 1 1944 1479 16 1694 1805 1895 1372 1473 1647 1144 1114 ll68 1241 1310 1058 1591 1677 1849 1615 1710 18 1397 13 1 1570 1225 1395 1515 1655 1736 1374 1005 1128 1500 1512 1652 1779 1910 1409 1502 1640 1782 1156 1233 13 1439 1 1191 1682 1715 1776 1874 -

)

. 7 . 2 .9 .9 . 2 . 6 . 7 . 5 . 5 . 9 . 1 . 0 . 6 . 1 . 1 . 7 . 4 . 7 . 3 . 1 . 9 . 0 . 0 . 5 . 7 . 7 . 6 . 7 . 5 . 6 . 6 .1 . 6 . 3 .3 .9 . 6 . 9 .4 . 2 . 5 . 0 .3 --- tlHt rs- 30 . 2 29 29 27 30 . 4 28 28 27 26 28 27 27 . 0 25 25 21.6 25 23 23 22 19 19 18 18.7 18.3 12 12 12 28 28 26.7 28 27 . 2 26 25 . 4 25 25 24 23 22 24 23 22 21.9 20 18 18 17 17 17.4 12 11.5 27 26 26 25

(W'

2 3 1 6 3 56 05 51 51 59 59 3 1 268 022 800 157 651 583 286 19 045 991 215 N 000 ---- 4 41 4095 39 4 39 4071 4 3 4080 39 3 83 6 3 3 39 3718 3 34 33 335 3 3 311 3 2717 2652 2574 4392 4243 4070 4239 4096 3 3860 4041 390 3746 3622 3510 3829 3702 3594 3449 3319 3302 3 3096 3041 3 2699 2514 4268 4182 4139 40 ,fl5 ( r pm) 9 3 2 3 2 3 56 82 34 --- 905 795 740 61 965 168 686 564 514 86 722 514 615 61 789 739 501 653 --- 43 573 282 141 183 100 003 563 486 516 49 268 488 364 256 082 102 794 .39 .3 .1 -- Ps/P 2 . 2 . 2 . 2 . 2 . 2 . 2 . 2 . 2 . 2 . 2 . 2 . 63 8 2 . 2 . 2 . 2 . 2.404 2 . 2 . 2 . 2 . 2 . 1.935 1.932 1.670 1. 1 . 2 . ----- 2 . 2 . 2 . 2 . 2 2 . 2 . 2 2 . 2 2 . 2 . 2 . 2.159 2 . 1.984 ----- 1.866 1.842 ----- 1.5 1.750 -- ----- 3. 2 .

7 3 3 31 83 -- 30 3 4 t - n 877 873 8849 8407 8540 8801 81 8289 8259 8252 84 6996 7896 7895 8215 8540 7534 7853 8053 8424 8069 7258 72 7795 8782 8364 8477 8716 8803 8080 8318 8490 8548 8494 8160 8332 8384 8123 8112 8178 7082 7459 .863 . . . . .8613 . . .

. . . . 8 3 . . . . . . . . . . . . . . .8394 . . . . . . . . . . .8363 . .8004 . . . .,8563 . . .6386 . .

------ 0 --- ------ ------ ------ ------

)

, 5 56 79 65 02 59 15 62 88 99 96 77 55 40 51 12 41 47 34 43 37 80 67 19 69 83 29 79 22 89 49 94 95 .3 . . . . . 2 3 . . . . . . . . . . . . . . . . 71 . .

. 8 3 . .39 . . 64 .

g W B!~ 4.33 3. 3.

( -----

9 6 96 . 96.93 96 94 . 93 94 . 94 94.32 85.46 84 8 8 82 14 73 70 66 69 52 52 51.18 50 49.65 3 7 . 0 3 3 6 . 36 97.90 96 97 93 . 93.39 93 . 93.35 86 86 85 84 8 76 75 74 73.14 52 52 52 51.67 51.80 37 36 97.43 95.32 95 6 2 8 7 ) 0 8 6 RMANCE 46 2 3 0 4 11 72 88 73 28 99 71 10 80 70 19 17 20 96 29 11 61 61 21 50 54 00 39 17 06 32 36 .7 . . 67 .9 . 84 . . . . . . .1 . . . . . . . . . . . . . 77 . .34 .3 . 5 3 . . . . .3 a , l W s!~ 3. 3. 3. 3. 3.4 6.81 ( ----- 95 . 40 95.4 95 95 9 93 . 54 92 9 92 84 84 8 82 81 7 7 70 . 65 68 52 52 50 49 49 3 3 6 . 36 96 95 96.18 92 92.42 92.73 92 86 85 84.45 83 82 75 15 73.53 72 70.28 71.20 52 52 52 51 51 37.71 36 96 94.20 95.40 96.60 94 . 64 PERFO 1 3 3 3 R) 39 25 0 3 94 86 3 6 3 0 3 2 3 1 33 T6 966 898 938 850 902 961 9 98 868 (O 119 12 13 1382 15 1116 1251 12 1 3 1486 1258 10 1128 121 1280 1369 1082 1191 1290 1386 1005 106 1124 1190 1289 14 115 13 1446 1083 1180 1301 1412 15 1007 1103 1194 1310 1437 1080 1137 1168 1009 1279 1348 1384 1480 9 4 3 3 3 47 35 59 -- 80 TURBINE b ---- P 2210 23 70 24 265 2016 225 2316 25 2669 1822 1968 2070 22 23 1669 1742 2029 2142 1314 1420 1500 1602 1628 1211 128 1384 2124 - - 2558 2027 2238 2373 2562 1855 2051 2256 2425 257 1665 1823 1933 207 2195 1410 ---- 1576 1630 ---- 1282 1192 ---- ---- 1920 21 ~

e

.

3 3 10 0 0 30 30 27 T5 940 990 955 (OR) ---- 1563 1660 1720 1850 1410 1560 1600 18 1630 1050 1095 1055 1480 1593 14 30 1540 1627 13 1433 1800 1230 1147 1704 13 1394 1485 1555 1650 1150 1310 1,420 15 1165 12 1290 1743 1748 1563 1680 132 1410 1540 1673 1083 1243 129 1330 1108 1573 1643 1680 1780 - 6 3 3 0 21 94 79 84 85 77

ft) 4 0 31 51 3 9 64 00 3 2 2 3 13 61 90

005 13 004 VARIABLE-AREA P5 ---- 64 6625 67 6964 5 9 62 63 65 6 710 5218 5 3 5462 5621 57 43 4482 4546 4631 45 2869 2982 3 31 314 20 2069 216 5924 ---- 6359 555 5767 5935 6 49 51 5316 5501 5616 4144 4310 4 3 44 4570 2798 --- 2941 3 ---- 1967 2086 5797 5820 5 60 .~b - ( 8 9 3 3 3 3 3 3 I.

39 33 43 37 855 85 866 871 880 83 7 8 781 763 650 815 164 775 785 794 799 724 727 7 7 644 643 646 T4 824 849 862 78 801 802 809 676 736 743 748 651 657 66 668 580 584 588 812 836 844 803 82 831 75 653 65 57 582 81 827 824 8 ("R ) 2 3 3 9 3 3 TABLE T2 499 495 494 494 495 491 490 490 496 49 491 491 490 491 488 487 486 480 488 489 486 487 487 488 485 485 485 48 493 489 495 495 494 496 49 492 491 490 48 491 487 488 488 487 486 483 481 482 480 484 48 485 497 491 49 ("R ) 0 2 3 5

rt) 79 79 72 75 69 70 97 74 72 75

85 17 75 81 81 83 75 2 34 374 374 P 1 1379 1 3 138 1 3 13 13 1384 1 3 1385 1 3 1374 1 3 1377 13 1375 13 1370 1371 1 3 1372 1388 1371 1377 13 1 3 1 3 71 1 3 13 79 1369 1377 1376 1374 1377 1371 1375 1 1374 1375 1 1 3 74 1376 1372 13 1 3 1375 1 3 1378 1374 1374 13 1375 1318 1364 137 136 .~b ( 5 5 95 65 90 f 55 40 35 90 15 95 250 785 885 840 W ~) 525 855 000 015 879 96 855 814 ( 3 1 40 3 39 2 351 37 22 3 1095 1229 3370 3005 3495 3 4450 2400 2890 3 4390 1865 2230 2500 2890 3295 1175 1295 1530 1022 3 43 47 4195 4610 25 3 3 3 6 1800 2115 2455 27 1365 1511 1639 3785 4495 33 1655 1740 4040 4310 4720 0 0 9 9 1 53 53 353 353 719 630 N 7260 7260 7260 7260 7260 6897 6897 68 6897 68 63 5 3 63 5 3 6 6 63 53 5808 5808 5808 4719 4719 4 4719 3 63 0 363 363 7260 7260 7260 6897 6897 6897 6897 63 5 3 63 63 63 53 6353 5808 5808 5808 5808 5808 4719 4719 471 4719 3 3 630 7260 7260 7260 7260 5808 5808 4719 4719 (rpm) 5 5 0 0 0 ft) 15 1 5 30 30 30 3 0 30 67 67 67 a zzle 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.30 1.30 1. 1.30 1.30 1.30 1.30 1.30 1.30 1.3 1.30 1. 1.30 1.3 1.30 1.30 1.30 1.3 1.30 1. 1.30 1. 1. 1. 1.67 re 1.1 1.15 1. 1.15 1.15 1. 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.1 1.30 1. 1.

.q a Turbine no (

)

7 3 3 0

l't 00 92 85 85

1189 1191 1195 1180 1177 1192 1187 1187 1190 1186 1185 1188 1188 1186 1181 1188 1187 11 1184 1185 1190 1186 Po 1185 1189 1196 1188 1199 1 2 1198 1188 1191 11 1186 119 118 1186 1176 1186 1188 1176 1182 11 1182 1186 119 1183 1192 1184 1188 1185 1184 1186 1184 1183 118 1183 .~b ( .

0 4 2 2 3 3 24 64 64 60 67 5 9 55 51 56 6 9 75 62 74 72 62 64 67 59 67 63 63 46 456 467 457 471 47 460 485 47 467 460 46 464 463 46 464 462 460 464 464 461 471 464 466 470 460 457 . 4 . . . 4 . . . 4 . 4 63 . . . 4 64 . . . . . .4 .4 . .

.4 .4 . 4 .4 .4 .4 .4 .4 . 4 5 3 .46 . . .4 . . .4 . . . .455 . 4 . .4 . .4 . .48 . . .459 . .463 .4 .4 . .4 Me t) ( f 15,000 Alt1tude 2 3 5 6 7 9 1 4 8 10 11 1 2 13 14 15 16 1 7 18 19 20 2 1 22 2 3 24 25 26 27 2 8 2 9 30 3 2 33 3 4 35 3 6 3 7 38 3 9 4 0 41 42 43 44 4 5 4 6 47 48 49 50 51 52 5 3 54 55 5~ 3 1 Run

~ !J> ~ tzj (J1 [\) y [\) o

t-' Ul 5 4 3 - - 35 28 - - T5 14 Ts 168 164 148 12 084 085 255 250 238 232 219 182 215 198 166 ---- 1.200 1.220 1.214 1.204 1.195 1.188 1.206 1.198 1.186 1.181 1.167 1.188 1.179 1 . 1 . --- 1 . 1. 1.1 1 . 1 1 . 1.092 1 . 1 . 1.08 1.267 1.259 --- 1.228 1.245 1.229 1.268 1 . 1.243 1.205 1.270 1 . 1 . 1 . 1 . 1.257 1.233 1 . 1.203 1 . 1.192 1.190 1 . 1.172 1 . 1.125 1.111 - 1.106 1.248 1.2 O) f W M O 0146 010 0123 0135 0148 0088 0120 Oi49 0075 0092 0122 ---- 0079 0090 0110 0103 0086 0096 0083 0124 0147 0072 0079 0085 0093 0098 0070 . . . . 0079 0062 0072 0100 0109 l{ .0114 . .0103 . .0136 . . . . . .0071 . . .0097 . .0066 .0072 .0080 . .0111 . .0104 .

.0122 .0138 .0094 . . . . . . .0060 . .0080 .009l .0099 .0055 .0063 .00E9 . .0090 . .0065 . . .

0 . -- 0 . ------ ------ a , W

~Cft/

'Y5 ) r.4 21 34 53 66 97 35 98 67 - - 39 08 33 42 78 20 54 23 86 38 53 00 .72 . . . . 00 ( . . 71 . 76 . . . . . . . . . . .

. . .

, 5 1 !~c -- -- 3.

( g 63 62.92 63.14 63.45 63.24 63 63.03 62.51 63 62.69 62.68 62.36 63 64.02 6 - 59 60.36 59 59.68 63.52 56 56 56 55 56 56.13 56 56 --- 56.49 56.64 57.11 57.37 57 55.70 56.26 55.85 56.02 56.08 56 58 59.34 60 53 54 ----- 58 55.56 54.70 53 55 55.94 54.55 58.15 58 .

W -- T5 ~ 884 913 (OR) 1949 1552 1650 1811 ---- 1713 1898 1425 1538 1675 1783 1868 1332 1467 1622 1720 1164 1240 1305 1368 1474 1049 1100 1175 1208 1672 1770 1867 2010 ---- 1521 1613 1735 1893 2067 1387 1449 1491 1550 1577 1251 1352 1439 1529 1616 1050 1120 1173 1276 1357 -- 1006 1658 1760

)

. 8 t . 8 . 8 . 8 . 4 . 0 . 6 . 3 . 6 . 8 . 1 . 8 - - . 3 . 4 --- 6H 24.9 26.3 25.8 25.1 24.4 23 24 24.3 22 22 21.5 21.6 21.9 20 ---- 16 -es 21.1 17.2 17 16 15.8 1l.3 10.4 10 10.4 30 30.0 29 27.7 -- 30.2 29.7 28.7 27.5 25 29.6 28.1 27.5 27.2 26.8 27.3 25.9 25.3 24 24.2 21.4 20.8 20.3 14 12.8 - 19.8 19.6 12.8 29.1 28.6

(~

m) 3 5 3 2 978 881 850 707 221 --- N 3 3964 3 3785 41 4048 3983 3 3 3601 3516 3854 36 3470 33 ---- 3 3152 3084 3010 2929 2661 2612 2521 2493 4392 4216 4125 4007 ---- 4289 4055 3901 4175 3754 4125 4029 3983 3902 3874 3951 3816 3711 3605 3518 3493 3407 3323 3204 3113 2937 2899 - 2767 4405 4286 -fo5 (rp 692 --- 855 665 749 583 483 178 072 9 933 827 610 510 496 870 776 683 628 999 904 793 650 971 810 722 823 564 468 406 211 151 077 870 ---- P&,P6 -- 2 . 2 . 2.674 2 . 2.538 2 . 2.478 2 . 34 4 2.235 2 . 2.421 2.328 2 . 2 . 1. 1.974 1 . 1 . 1 . 1.675 1 . 1.568 1 . 1 . 2.995 2 .

2 . 2 . 2 . 2 . 2 . 2 . 2 . 2.527 2 . 2.873 2 . 2 . 2.680 2 . 2.669 2 . 2 . 2 . 2.268 2 . 2 . 2 . 2.046 1.717 1.663 - 1.654 2 . 2.8 3 - - 40 20 - - - - nt 7661 747 7487 7868 8377 8123 7664 8037 8296 7527 8772 6918 6696 8635 8562 8410 8379 8454 8319 8319 7947 7939 --- 7371 8197 8289 . .7696 . .7689 .7729 . .8054 . . .7488 . 76 .7944 .8 . .7844 . . . . . .7415 . .8693 -- . . . . . .8497 . .8413 .8191 .8067 .8182 .7938 . .8162 .8033 .8017 .8130 . .8130 .8180 .8216 . . .7528 . . .8294 - 0 . ------ 0.8541 ---- - -

)

,5

~ 80 79 10 12 72 81 18 21 66 37 31 55 62 --

84 39 27 51 96 32 14 35 84 17 -- 75 . . . .

. . . .20 . . . . . . .

g - - - . . . . . . . 76 .

- s! 1.

W

(

96 9 93 . 93 93 92 86 86 85.50 84.63 84.08 77 . 76.07 75 74 -- 49.50 49.54 49 - - - 51.13 52.04 37.94 37.80 37.01 36 57 57.44 57.48 56.86 56 56 51.54 51 51 50 51.19 46 46.46 46 45.92 32.52 31 23.90 24.11 -- 23.36 57 30 30 57 48 55 30 -- 51 72 07 -- 33 17 00 87 07 72 60 90 . .33 .49 . 84 . 38 . . 73 . . 69 .

a , l . . . . . . . .

- ---

W s!~) 7.53

(

95.40 90.85 92.05 91.99 92 91.45 85.4 85 84 83.50 82 77.08 75 74 . 73 --- 49.15 50 49.10 48.84 37 3 3 6 . 36.24 57 -- 51 56.49 57.12 56.50 57.19 56.66 57 56 56.25 55.90 56.59 55.57 51 50 51 50.49 50.69 46.04 46.14 46.16 46.53 45 45.47 32.34 31.16 31.03 31.24 30 29 23.75 23.95 -- 23.19 57.19 57.12 3 6 30 3 7 T6 Orl) 34 996 900 944 915 808 853 905 987 711 741 774 820 ( 1448 1525 1235 1302 1370 1536 11 12 1 1442 15 1023 1168 1301 1375 1485 1045 1106 1173 1246 1017 1043 1168 1283 1360 1467 1518 1099 1177 1265 1393 1541 1000 1070 1107 1161 1194 1006 1082 1164 1233 1055 1178 1256

)

t

3 3

\

921 993 750 786 911 668 717 729 820 869 694 P6 2307 ---- 1951 212 2205 2361 1853 2024 2190 2 3 77 2486 1690 1806 2002 2298 13 1428 1528 1624 2138 173 1222 1274 1342 1388 1245 1356 1440 1541 1599 1198 1260 1342 1467 1601 1047 1096 1148 1197 1232 1062 1116. 1155 1259 1 3

s~

(

) 3 - - - T5 983 -- 963 800 823 907 (Orl 1830 1507 1580 1650 1730 1825 1370 -- 1473 1600 1703 1793 1215 1377 1520 1600 1143 1197 1255 1 32 3 1400 1023 110 1130 1480 1615 1693 1803 - 1393 1477 1573 1710 1857 1337 1370 1430 1455 1150 ---- 1270 1240 1315 1400 1477 1015 1070 1157 1230 1470 1560 t) f 3 4 30 b --- P5 ~ 6210 5374 5571 5677 6876 5993 4786 5016 51 5313 5428 4092 4204 4360 2624 2761 2792 2841 1967 44 4504 2903 1997 2027 2076 3729 3892 3997 4135 4202 3593 3659 3748 3888 4045 3111 3149 3226 3258 3302 2600 2650 2723 2754 2779 1701 1738 1764 1805 1864 1147 1154 - 1206 3613 3 73 7 (s T4 830 807 805 813 817 827 762 769 777 789 792 674 722 733 734 676 660 657 658 664 662 574 572 579 579 809 837 844 845 844 801 810 816 826 832 762 770 772 779 781 720 724 730 737 745 638 636 643 793 647 654 562 557 565 564 805 (Orl) T2 Orl) 504 497 500 496 487 487 499 499 497 496 496 498 473 486 483 484 510 501 499 502 493 486 483 488 485 459 473 471 465 463 475 475 471 469 466 475 479 477 479 479 477 474 471 476 474 475 476 473 471 471 470 468 469 468 460 460 ( ) rt 68 62 11 75 65 68 --- 791 797 796 797 797 797 795 799 812 803 800 802 801 804 798 802 802 805 802 800 809 805 804 801 804 797 802 807 803 791 792 P2 - ~ b 1 3 1 3 13 1 3 1377 1365 1374 1381 1 3 1370 1374 1366 1 3 1375 137 1375 1387 1377 13 74 1379 1 3 77 1 3 1370 1373 (s

)

f 70 30 45 23 W 645 595 892 972 997 641 709 773 867 964 526 562 579 605

(M

50 33 3 4065 4480 4890 2695 3160 3 4075 4450 2090 2500 2965 3 2 30 3 1250 14 1595 1705 1910 1060 112 1979 2255 2480 2810 3020 1710 1905 2115 2490 2935 1 3 1567 1688 1445 1786 1169 1333 1498 1614 2060 2250 N 630 630 7260 6897 6897 6897 6897 6897 63 53 63 5 3 63 53 635 6353 5808 5808 5808 5808 5808 4719 4719 4719 4719 4719 3 3630 3630 3 7260 7260 7260 7260 7260 6897 6897 6897 6897 6897 6353 6353 6353 6353 6353 5808 5808 5808 5808 4719 7260 7260 5808 4719 4719 4719 4719 3630 3630 3630 3630 (r pm) ine le ft) 67 67 67 67 67 67 67 67 67 67 zz 1.67 1.67 1. 1.67 1. 1. 1.67 1.67 1.67 1.67 1.67 1.67 1.67 1. 1.67 1.67 1. 1.67 1. 1.67 1. 1. 1. 1. 1.67 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.15 1.20 1.20 ( s q Turb no area

)

rt

605 616 621 614 620 626 619 622 620 615 615 619 618 618 617 615 621 622 624 622 621 616 621 618 619 618 620 620 617 612 611 Po 1188 1183 1186 1186 1186 1181 1186 1187 1181 1182 1191 1183 1186 1190 1188 1184 1181 1195 1188 1188 1184 1186 1183 1186 1182

s~b

(

3 - O 45 455 464 464 459 462 462 471 464 460 632 472 460 459 607 621 618 611 619 621 626 616 621 . .460 . .467 .460 .464 . .457 . . . .462 .459 .460 . .467 . . . .467 . . .469 . .619 . .621 .621 . .611 .610 . .628 .619 .624 .624 .623 . .627 M ---- .616 . .616 .622 . .624 .613 .622 .614 .619 .625 . . .

0 . - ---- IU de tu , i (ft) lt 15 3U,UUU IA 0 2 57 58 59 60 61 62 63 64 65 66 6 7 6 8 69 70 71 72 73 74 75 76 77 78 79 80 81 ~~ 84 85 8 6 87 88 89 90 91 92 93 94 95 96 97 98 99 Run 100 101 102 103 104 105 106 108 109 11 11 107 111 I-' ~

~ ::t> ~ I::>=j I:\l

Ul Y I:\l o I 9 9 9 9 3 2 6 3 5 5 0 6 5 2 - 33 08 5 6 - - 36 20 06 81 74 58 -- 43 19 43 0 9 T5 T6 2 3 8 21 25 2 3 7 22 205 19 2 9 1 25 2 2 17 2 168 11 1 22 2 2 32 22 2 45 2 05 - 2 34 2 226 19 17 174 .17 .1 --- 1.

1. 1 . 2 2 6 1 . 1. 1. 1 . 2 1 3 1 . 1 . 1. 1. 1. 1. 1 . 2 1.2 --- 1.2 1 . 2 1. 1 . 1 1.1 1 1. 1 ----- 1. 1. 1.116 1.106 1.101 1. 1. 1 . 1 . 2 0 8 1.19 1.189 -- - 1. 1. 1. 1. 1 . 2 1. 1 . 2 1 2 1.19 1 . 1.24 1.196 1 . 1 . 1.160 1.17 1.16 1.141 1.1 0) 6 3 9 1 0 9 1 9 9 6 5 2 5 5 2 2 60 26 9 9 90 50 60 62 66 98 77 90 00 26 0 3 11 11 --- 114 11 13 0 06 Wf 0087 00 011 012 0151 0072 008 00 - 0081 0086 0061 0075 00 0060 00 0067 0077 0065 006 0076 008 00 012 008 0100 0088 011 01 00 01 008 0089 006 . 0 1 . OB 5 . . . . . . 0 1 . . . . 0 101 . 0 . . . . . . . . . . 0 0 . . . . . . 0 . . 0 14 5 . 0 15 9 . . 0 . 0 153 . . 0 .0 . . 0 1 . . . 0 . . .011 .0126 .0057 . 0 .0071 . . .

,1(:S -- 0 . 0 ------ a W

)

~

- - ) 0 2 VBs

ri 86 58 97 67 33 54 21 13 57 14 17 64 05 60 66 05 41 39

40 44 34 14 09 65 81 - - 18 87 . . 9 3 .

( . 3 9 . . 9 2 . . . 0 1 . 3 6 . . . . . . . . . . . 3 5 . . 0 7 . . .4 . . . 2 3 . 4 2 . 71 . . . 23 .4 . 5 8 . 63 . 63 . . --- .3 1b sec -- g , 5 ( 57 5 7 . 92 57 5 7 . 73 58 58 58 58 58 56 57 57 57 58 57 -- -- 57 . 2 7 57 57 55 56 57 -- -- 55 56 60 58 58 54 . 73 54 53 . 54 60 60 60 60 60 60 60 60 60 60 60 60 . 2 4 60 60 5 9 . 5 9 60 61 . 62 62 - 5 9 . 63 5 9 . -- 59 5 9 .

W 6

) 4 2 7 3 0 8 9 5 1 4 2 2 10 90 62 3 2 1 6 23 18 - - 91 02 44 4 7 94 40 30 75 14 61 07 T5 ~ 93 52 621 062 8 90 4 91 964 82 943 62 --- 895 (~ 18 18 1 9 15 166 1787 132 3 -- ---- 1 20 208 144 1 1 17 12 13 63 14 14 1 1075 110 117 1271 1021 1 6 90 1 1 2060 21 1585 168 1816 1 9 63 20 14 153 7 1 640 1 2 15 - 1 7 184 1 17 1847 1174 1 2 1 3 64 6 - - 7 ) 6 6 5 . 9 . 2 . 4 . 2 . 7 . 0 . 1 . 0 . 3 . 2 . 0 . 8 .9 . 1 . 9 . 4 . 2 . 9 . 8 . 7 . 5 .1 . 7 . 1 .1 . 5 . 6 . 5 . 4 . 7 . 5 .3 . 1 .6 . 3 .. 8 7.4 9.

0 . 3 -- 8. 6.4 3.

3. 1.

2 8 . 4 2 26 2 28 27 26 25 28 27 26 --- 24 . 2 - llli t "G5 ~ 25 :S 25 27 25 24 20 19 19 19 17 13 13 13 1 2 . 8 12 2 27 27.0 26 25 28 27 26 25 2 4 . 1 2 7 . 1 2 25 2 4 2 26 2 22 2 20 "';--- 16 ---- ---- . 19 1 7 . 1 1 2 . 5 ( 0 3 3 - 3 9 34 99 63 93 -- 75 64 56 20 4 7 71 22 55 66 04 64 86 20 - - 64 23 221 081 75 278 117 006 784 -- 811 762 939 070 400 11 000 010 988 768 662 55 946 N 4 4149 4 433 417 4 0 3 8 3 37 4 4 4 3 8 3 4 - 3 8 77 3 3 3 5 35 3 5 1 6 34 32 48 -- 2 9 2 2 9 4 4 33 28 27 4 24 3 4 3 9 427 41 4 3 8 3 75 9 41 3 38 3 3 3 9 3 6 71 3 34 3348 -- 33 33 ---- 31 21 2 VBs (rpm) 6 4 4 3 4 - 7 4 0 3 3 6 9 9 0 7 P 91 44 52 27 65 -- 3 6 22 6 9 83 2 5 75 62 767 651 43 76 66 49 680 527 510 216 115 6 96 677 65 780 68 43 690 68 44 374 608 050 557 50 336 20 96 .4 .1 py 2 . 2 . 6 2 . ----- 2 . 2 . 2 . 5 2 . 2 . 4 2 . 83 8 2 . 2 . 2 . 5 96 2 . 2 . 7 2 . 2 . 2 . 2 . 2 72 2 . 2 . 1 2 . --- ---- 2 .

2 . 5 9 7 2 . 1. 1 . 1 . 1.6 2 . 2 . 5 94 2 . 4 9 6 2 . 2 . 2 . 2 . 2 . 2 . 2 . 732 2 . 2 . 2 2 . 2 . 63 3 2 . 37 3 2 . 2 8 3 2 . 2 . 1 64 2 2 . 0 2 . 0 4 3 1. 1.9 1.640 1 4 3 6 6 3 8 2 5 41 -- 0 6 08 60 96 24 3 6 65 66 80 08 78 53 51 34 99 78 433 39 15 48 885 510 43 61 439 318 27 06 7 n t 80 8264 8616 82 8106 8217 8210 75 7656 7727 7560 ---- 720 8521 8476 83 8044 85 773 811 80 7599 . 83 . 8 3 . . 8 . 8 . . 83 .9 . 8 . . . . 84 77 . 8 4 . . 7 . . 7 . .77 . . . 7 70 4 . 73 . . 8 3 . 8 . . . 8 3 . 8 .82 . 8 ----- . . 8 .8477 . 8 . 82 4 7 . . 8 2 . . 8 . . .7 . . 78 83 .7719 .

ed ------ 0 . ---- - -- ------ ------

) 3 7 5 2 0

tinu 68 76 72 22 50 70 77 28 06 22 78 07 05 25 -- 67 2 3 70 68 05 58 6 9 52 54 19 09 33 16 47 84 07 . . . . . 5 3 . . 4 1 . 90 . 90 . . . 90 . 92 . . 73 . .7 . 4 0 . 71 . 8 9 .4 g , 5 !~ --- .4 .

s

on W 3. 3. :S 3.91 3. 8. 7. 7. 3. 3. 6.

( 5 7 . 5 7 . 74 57 5 6 . 57 57 56 55 56 5 3 . 1 7 52 52 52 5 4 6 . 32 . 5 9 ---

C 4 7 . 4 6 . 14 4 6 . 33 3 33.49 3 2 2 3 . 95 23 . 2 22 5 57 57 57 57 56 57 5 57 5 53 5 53 . 5 2 5 4 6 46.1 4 6 . 4 5 . 70 4 34 . 3 3 . 2 1 33.3 3 2 . 31. 25

- ) 0

,l 66 71 99 70 77 -- -- 77 - - 02 02 86 85 00 7 9 51 05 72 27 97 68 94 05 89 5 3 62 18 97 92 06 56 . . .99 . 23 . . . 98 .S 3 . 7 9 . 4 3 . 3 7 . . . . 2 7 . .49 .

!~ . . .9 . . 2 3 . 83 . 0 3 . . 4 8 .

a W 4. 3. 6.81

( s

57 57 56 56 56 56 55 5 55 52 5 1 . 52 52 52 46 --- 4 5 . 87 45 4 6 . 38 3 2 . 40 3 2 . 8 7 3 2 . 33 33 --- 2 3 . 75 2 2 3 . 2 3 . 22 57 57 56 56 56 56 56 56 53 4 6 . 1 5 57 5 5 3 . 5 3 . 0 1 5 1 . 52. 4 5 . 71 4 5 . 4 5 . 4 5 . 75 33 3 2 . 9 5 33. 3 2 . 21 3 1 . 2 4 .

ANCE 2 7 9 6 9 M 1 0 3 8 9 5 7 6 0 7 65 9 4 4 0 19 9 9 8 3 71 17 93 08 26 93 27 1 0 21 91 81 26 28 72 T6 91 860 90 1 9 79 80 7 71 7 773 OR 8 3 0 8 97 822 55 20 907 _-- 89 9 2 1 71 ("H) 1 3 0 1 1 3 1422 1086 1196 12 1412 1544 15 1 0 10 11 126 101 106 10 1185 12 1393 149 15 8 2 ... ---- 11 12 13 1447 1 10 3 4 111 1 1 2 1 3 11 1 2 1 3 3 5 141 10 ) - 4 1 4 1 4 4 8 9 PERF 0 0 8 2 0 2 ft' 82 4 5 9 2 9 2 74 6 6 14 60 71 4 7 56 41 94 20 84 47 6 b 62 93 2 9 6 6 05 746 7 782 8 1 8 8 90S 66 68 5 71 73 6 627 657 33 93 5 764 810 8 4 6 897 920 67 P ~ 1509 --- 12 140 112 120 ---- 13 14 14 1595 1 107 12 13 10 1 1102 1258 13 144 1557 1 1 2 1 2 14 15 1 111 1191 12 1 1450 111 119 12 13 15 s ( ) 3 0 0 3 0 3 7 3 3 33 67 77 77 55 -- 43 50 73 93 TURBINE 43 2 3 55 05 10 0 3 10 53 43 T5 080 94 9 9 73 790 800 8 10 8 9 70 285 56 --- 22 795 (OR 1 610 1 67 3 17 13 1480 1590 171 1860 1847 11 1 2 13 144 1530 1 - - 1200 12 1280 10 11 ---- 14 15 1 18 1 8 90 14 1493 16 1 74 3 18 1 1 3 6 7 14 63 1643 113 1 34 7 144 ---- 10 70 - 1543 1 1 6 104 1 ) 9 2 9 3 7 3 8 3 6 4 2 22 07 01 34 66 84 93 - - 33 28 4 9 5 9 80 31 41 8 7 62 2 8 06 39 806 960 575 208 888 880 09 54 731 786 20 886 96 93 222 717 84 P5 ~bft 3 3 3 3434 3 37 3 79 6 3 3 974 3 04 8 3 3 33 34 2 258 26 266 2 7 1 6 95 1 6 16 1 -- 11 11 11 349 3 63 8 37 LE-AREA 1 1174 1 3 3 333 34 36 3 785 3 30 33 31 3 3 2 33 24 26 2 2744 2 1 65 7 1 68 7 17 1 764 1771 110 s ( AB I ) 9 6 3 9 1 7 4 3 5 6 14 19 49 94 06 85 AR 34 44 774 73 T4 80 8 12 815 785 795 80 83 9 81 740 74 6 75 758 686 65 695 70 705 6 613 61 2 6 622 630 5 4 6 54 6 54 6 5 552 778 7 8 81 821 765 7 75 78 79 804 731 73 8 74 6 75 3 75 9 6 705 71 2 720 724 61 3 619 63 1 6 V 615 5 (OR - 3 9 0 0 3 3 3 3 0 2 2 0 3 R) 62 62 60 60 62 60 60 61 60 57 57 60 60 60 60 60 55 56 57 61 62 65 61 I . T2 4 459 458 46 462 4 4 4 7 9 4 4 4 4 461 4 4 4 4 4 4 4 5 9 4 5 8 4 5 6 4 5 9 4 5 8 4 5 7 4 4 5 9 4 5 9 4 4 4 5 3 4 5 4 4 4 4 459 46 46 4 45 46 4 46 46 46 46 46 4 6 2 46 4 6 2 461 46 46 4 461 4 (O

)

2 1 2 4 6 7 2 2 7 7 2 3 9 6 3 3 5 1 89 94 89 93 88 02 794 79 792 790 7 9 7 7 7 79 7 95 78 79 2 79 79 6 -- - 78 5 78 78 6 79 79 5 786 7 7 7 TABLE 2 bft 80 802 80 1 79 3 79 5 789 79 794 78 9 78 789 787 78 796 800 80 8 80 4 801 80 78 801 786 787 791 78 801 806 79 80 19 790 80 P

s~

(

2 6 ) 0 0 90 05 95 65 75 10 95 00 85 50 45 90 25 85 90 90 83 75 50 05 05 00 7 710 735 Wf ~ 39 800 910 9 560 560 5 80 630 660 080 7 791 8 951 5 53 ( 2765 1770 25 13 1 515 1700 1 9 10 30 1 24 5 143 2 25 2020 2 3 2 9 3 0 30 20 111 1334 2020 23 26 2 9 75 3 245 18 2050 2 3 2775 3 1 148 16 19 20 2 3 10 1480 1690 18 2 10 0 9 0 0 8 9 9 9 7 97 9 7 9 7 53 30 60 60 60 53 0 8 N 260 260 897 897 726 726 7260 68 6897 68 68 6897 68 63 6353 63 53 6353 6353 580 5808 5808 5808 5808 4719 4719 4719 4 71 9 4719 4719 3 630 7 7 72 72 72 6 6897 6897 63 53 3 630 3 6 3 630 3 630 6897 6 63 53 63 53 63 6 35 3 5808 58 5808 5808 5808 471 471 4 71 9 4719 4 71 9 3 630 (rpm) 0 0 0 0 0 0 0 0 le ft) 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 20 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 30 z z 1.20 1.20 1.20 1. 1. 1.20 1. 1. 1.2 1. 1. 1. 1. 1. 1.

1.20 1.2 1. 1. 1. 1. 1. 1. 1. 1. 1. 1. 1. 1. 1. 1.3 1. 1.3 1. 1. 1. 1. 1. 1.3 1.3 1. 1.3 1. 1. 1.30 1. 1. 1. ' 1. 1. 1. 1. 1. 1. 1.3 1.3 ar ea sq ( Turbine no L- ~ 8 2 9 7 5 4 0 5 14 12 17 14 05 08 11 21 13 13 10 19 14 --- o 6 61 4 61 6 61 2 6 6 61 5 6 61 2 60 612 607 615 61 606 610 612 60 5 609 609 60 7 60 605 60 60 7 61 6 610 6 607 60 607 622 611 61 6 620 620 620 617 617 605 61 5 6 607 6 60 8 6 61 5 6 6 612 61 2 611 P s~bf ( 1 4 1 4 4 4 4 3 3 3 6 11 14 19 34 14 33 19 2 1 22 14 616 626 62 62 628 --- 62 62 62 62 62 626 622 625 62 61 626 628 627 607 62 61 O . 61 4 . 614 . . . . 6 . 6 1 6 . 63 4 . . 6 . 6 . 6 . . 6 24 . . 6 . 6 . 6 24 . . 6 2 9 . 63 0 . 630 . . 6 23 . . . 62 6 . . 61 6 . . . . 5 90 . 61 3 . 6 . . 618 . 618 .6 .6 . . . . .621 . 6 . 61 6 . 61 9 . 6 34 .616 . 640 . . . 63 6 M --- - - 0 . 61 8 , 0 (rt) Altitude 6 7 5 0 2 3 6 7 8 3 5 5 2 14 20 22 26 33 50 52 57 58 60 65 Run 1B 1 115 11 11 118 119 1 1 2 1 1 1 23 1 24 1 25 1 1 2 7 1 2 8 1 2 9 B O 1 31 1 3 2 1 1 34 13 1 3 6 1 3 7 1 3 8 139 14 141 14 14 14 4 14 14 14 149 1 151 1 15 1 54 15 156 1 1 159 1 1 61 16 1 63 1 64 1 1 66 1 6 7 1 68 ' --- ' '- t.>:.J CJl N Y N o t-' OJ

~ :x> ~

I . I I

1 I

3 3 3 3 9 T5

'l6 214 21 191 108 2141 205 201 205 216 i~~

199 159 .1 .188 .156 : 1 1.102 1.237 1.232 1.220 1 . 1.20 1.23 1.216 1.205 1.197 1.184 1.228 1 . 1.202 1 1.22 1.20 1.176 1.174 1.160 1 1.111 1 . U~i!

1.198 1 . 1.178 1.170 1.108 1.100 1.103 1.214 1. 1 . 1 . 1.225 1.212 1.199 1.195 1.191 1.232 1 . 1.193 1.191 1.187 1.225 1. 1 . 1.184 1.179 i 1 .

bVU, 3 5 Wf 0075 0083 0104 0114 0128 0151 0093 0117 0129 0162 0081 0091 0101 0117 0079 0111 0096 0105 0060 0071 0091 0073 0079 0108 0115 0121 01 0098 0149 0085 0078 0071 . . . . .0139 . . . . .0142 . . . . . . .0068 . .0090 . . . .0062 . .0079 . .0069 . . .0080 . . . .0127 .0151 . .0112 .0139 . . .0072 . .0126 .0099 .0112 .0118 .0128 . .0085 .0093 .0101 .0065 .0067 .

,lP 0 .

a IW

)

~';b/

) .,i 0 2 -A" 60 93 40 17 44 95 93 80

ri 26 25 70 85 07 95 55 70

. .31 . . . .3 . . . . . 04 . . 64 . . . . . . .43

( .9

,5 ik ( ____ g 56 56 61.22 61.42 61.31 60 61.35 61 . 61 61.63 61.21 61.12 60.71 61.05 61 61.36 60 61.25 60.75 61.47 60.63 61.12 ----- 57 60.67 60.86 59.07 58 57.96 57.58 57.56 62 62.26 62 62 62 62 62.53 62 62 62 60 62 62.08 62.41 62.04 61.67 61.84 62.14 62.76 62 61.08 62 62 W 55 ___---.- ) T5 974 922 953 "B2 (OJ!

1038 1693 1779 1882 1960 2037 1589 1782 1872 1978 2111 1447 1527 1625 1703 1747 1290 1397 1472 1544 1614 1106 1124 1194 1282 1349 1062 1741 1797 1865 1947 2042 1628 1746 2026 1435 1605 1831 1293 150 1130 1028 1868 1857 1958 1695 1744 1351 1427 1568 1147 1185 t . 0 . 0 .0 . 4 . 1 .4 . 6 . 4 . 8 . 2 . 8 . 4 . 1 . 3 . 7 . 7 .1 . 6 . 6 . 7 LlH 12.8 12 28 27.8 26.7 26 25 27.2 26 25.3 24.7 24.1 26.0 25 24.8 24 . 0 23 24 23 22.7 22 22.1 19 19.5 13.0 26 es- ~) 18 18.0 13.3 12.8 12 12 27 26 26.1 25.4 25.2 26.6 25 24 24.0 23.9 26.3 24.6 23.9 23.6 22.9 24.6 24.0 23.2 22.2 21.7 19.0 18 18.2 ( 69 73 25 N 28 2748 4327 4226 4118 4042 39 4236 4019 3928 3832 3718 4083 39 3864 3782 3739 3946 379 3 3632 3559 3452 34 3328 3212 3150 2904 2854 2752 2713 4324 4246 4172 4175 4097 4000 4222 4086 3974 3882 3817 4128 3907 3820 3768 3685 3954 3779 3693 3617 3442 3878 3415 3364 (rpm) -vBs 6 0 31 76 00 03 80 58 81 11 496 451 041 582 503 445 326 468 288 505 454 317 272 110 .434 .3 .3 .57 .481 .4 .374 .5 .4 .3 .3 s/P .3 P 1.626 1.596 2.7 ----- 2.559 2 . 2 2.717 2.517 2 . 2 2 2.668 2 2 2 2 2 2 2 2 2.280 2.145 2.120 2 . 2.695 ----- 1.970 1.925 1.646 1.640 1.601 1.591 2.637 2 . 2.533 2 . 2.411 2.554 2 . 2.368 2 . 2.600 2 . 2 2.338 2 . 2 . 2 . 2.386 2 . 2 . 2 . 2.062 2.016 3 6 TIt 8615 8227 8482 8418 8433 8009 8013 8176 7976 8050 7842 7718 7794 8239 8239 8187 8393 8353 8024 7823 7865 7922 7870 .76 .8398 .8535 . .8553 . . . .8513 . .8071 . . . . . .8102 . . .7796 .7792 .7790 . .8072 .6094 .7704 .7597 . . .8167 . . .8088 .7436 .7752 .8435 .8416 .8260 .8536 . .8449 .8112 .8198 .8306 .8333 .8267 . . . .7842 . .

------ 0.7811 ------ 1 7

) 5

,5 62 08 41 33 44 63 05 11 58 14 12 04 85 69 . . .1 .

g .3 . . . . . .9 . . . .

W s!~

(

23 . 23.52 57.54 57 57.48 56 57.02 56. 56.39 57.07 57 52.87 52 52 52.67 53 46.41 46.07 56.52 46.76 46.17 33.52 33.48 32.39 23.87 23 23 23 58 57.89 58.04 57.93 57.67 56 57.01 57.21 57.54 57 53.16 52.86 53.04 47 46.92 46 46.95 46 33.73 3 5 2

)

,l 75 91 44 33 09 31 24 93 52 23 16 81 40 56 52 .44 . .68 .39 . . .

a . . . . .3 . . . .4 . . .

' W s!~ 3.

(-

2 23. 56.95 56 56 55.75 55.57 56.49 55 55.67 56.27 56 52.44 51.70 51 52 52.4 46.09 45.92 46.28 45.66 46 45.69 33.07 33.27 33.31 33 32.14 32.09 32.38 23.71 23.46 22 23.29 57 57 57 57.39 58.12 57 56 56 56.38 56.28 52.86 53.31 52.64 56.50 56.75 52.28 52 52.16 52.83 46.70 46 46 46 46.22 33.51 33.35 33.57 33.15 33.39 T6 778 835 943 841 857 920 995 738 767 939 987 834 857 850 866 900 (OR) 13 1234 1394 1456 1529 1160 1319 1398 1484 1602 1059 1135 1217 1280 1322 1038 l1ll 1171 1224 1083 1239 1302 1359 1359 1427 1507 1178 1277 1370 1448 1506 1031 1185 1257 1296 1365 1123 1179 ) 705 74 3 75.3 95 768 829 862 930 658 677 711 741 33 971 773 777 797 P6 1277 1334 1437 1559 1226 138'8 1471 1568 1697 1104 1174 1255 1095 1482 1326 1371 1027 1151 1185 1287 1337 1384 1430 1471 1553 1238 1 1441 1533 1601 1132 1234 1315 1357 1426 1009 1061 1112 1157 s~bft ( ) 3 T5 86 920 987 820 850 917 945 995 (OJ! 1527 1607 1700 1604 1685 1777 1897 1300 1377 1463 1767 1840 1430 1533 1570 1153 1255 1323 1380 1440 1003 1067 1150 1200 1530 1590 1650 1650 1720 1810 1443 1548 1643 1730 1793 1270 1428 1500 1543 1620 1150 1200 1267 1330 1390 1010 1043

)

tt 88

678 255 P5 1146 ll86 34 ---- 3 3699 3794 3331 3493 3606 3726 3903 2946 3017 3114 3186 3 2459 2524 2607 2660 2702 1615 1628 1110 11.38 ---- 1692 1698 1790 1083 1179 3468 3526 3574 3622 3682 3744 3407 3523 3630 3724 2943 3045 3130 3172 3263 2432 2476 2532 2577 2629 1632 1602 1607 s~b ( ) T4 546 798 769 788 795 730 741 747 750 702 709 787 792 550 809 816 820 824 801 811 751 686 695 704 614 614 619 625 627 546 548 551 553 783 790 796 806 758 766 773 780 787 721 73.3 736 739 745 681 684 686 690 695 607 608 610 (OR ) T2 460 460 468 469 469 468 469 467 467 467 466 466 466 468 467 467 466 464 466 466 464 463 463 463 464 465 462 462 463 46.3 462 455 459 459 458 458 460 460 460 459 458 459 459 462 459 459 459 462 461 461 460 460 457 457 (OJ!

)

f€

P2 791 801 794 787 794 780 781 797 787 788 796 802 --- --- --- --- --- --- - -- --- --- - -- 787 793 801 785 801 776 781 777 798 791 791 793 792 791 789 790 790 795 791 791 794 791 789 794 792 792 794 792 788 790 788 792 784 s~b ( ) 63!j Wf ~ 698 015 35 717 743 851 917 588 617 655 673 790 800 850 ( 2130 2315 2615 2780 3 1890 2 2590 2875 3295 1535 1695 1890 2080 2215 1136 1305 1479 2375 2500 1209 1301 1602 1720 1050 2245 2625 2785 3080 1995 2270 2560 2845 3015 1625 1880 2100 2220 2410 1427 1550 1681 N 353 630 3630 3 630 7260 7260 7260 7260 7260 6897 6897 6897 6897 6897 6353 635 635 3 6 6353 5808 5808 5808 5808 5808 4719 4719 3630 3630 7260 7260 7260 7260 7260 6897 6897 6353 6353 6353 4719 4719 4719 3 3630 7260 6897 6897 6897 6353 '6353 5808 5808 5808 ~808 5808 4719 4719 471"9 ' (rpm) ftl 67 67 67 67 67 67 67 1.37 1.37 1.37 1.37 1.30 1.30 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.37 1.67 1.67 1.67 1. 1.67 1.67 1.67 1.67 1.67 1.37 1.67 1. 1.67 1.67 1. 1. 1 . 1.67 1. 1.67 1.67 1.67 1. 1.67 area Turbine nozzle (sq

)

tt 3

Po ~b 610 610 62 608 618 604 622 616 607 604 610 620 612 605 605 605 612 605 603 605 609 605 608 609 605 603 603 596 605 597 610 608 612 610 608 610 607 608 608 608 614 608 610 610 608 608 609 610 609 609 610 610 610 605 601 .

(.

619 621 622 629 624 629 625 626 626 625 623 623 625 625 625 627 624 621 624 622 .636 .599 .619 .609 .616 .579 . . .628 .629 .618 .616 . . .634 .627 . . . . 634 .630 .619 .625 .647 . .650 . .616 .625 .633 . .616 .623 .627 .621 .623 . . . .619 . .621 .625 . .625 .621 . . . .622 .

MO .624 . .6 0.621 " ..

' ~, (rt) ltitude 30,000 A / .

~~~---{.__ '.J 3 3 5 4 1 169 170 171 172 17 174 177 178 179 lSI 182 18 164 18 186 187 188 190 191 192 193 1 96 197 Run 175 176 "l80 189 194 1 9 5 198 199 200 201 202 203 20 205 206 207 208 209 210 211 212 213 214 215 216 217 218 219 220 22 222 22 ,

.'

~"'--~-

-----

-

~ f) ~ ~ t:rj (J1 N N

t-' (J) Y o

--------

~ - 4 3 4 5 3 5 2 - 14 75 97 127 --- T5 'l6 144 098 092 165 160 151 142 150 1 22 204 1 21 214 212 212 204 20 202 144 16 148 134 .191 1 . 1 . 1 . 1.098 1.091 1. 1.173 1 . 2 3 1 -- 1 1 . 1.200 1.2 1.172 1 . 1 . 1 . 1.164 1 . 1.141 1 .

1.093 1.161 1.175 1.16 1.19 1. 1.20 1.168 1. 1. 1 . 1.195 1.185 1.175 1.157 1.179 1.189 1.143 1.226 1 . 1.197 1.227 1.217 1. 1.208 1. 1. 1. 1 . 1 . 1 . L 1. ---- ) ~---.

3 0 7 2 7 21 39 05 f 154 149 144 135 134 13 13 14 153 14 W 0102 0070 0078 0088 011 0071 0126 0131 0108 0146 0092 0089 0111 0127 01 0112 0118 0095 0111 0129 0148 010 0095 0144 0147 0107 0111 0135 ---- . . . .0073 . . . . . . . . .0116 . . . 0 1 . . .0 . . .0134 . 0 . . 0 1 .0089 . . . .0159 .0122 . 0 . 0 1 . . 01 24 . 0 . .0 1(3600 . . . 0 1 71 .0118 . 0 . 0 . . . 0 . 0 . . .0142 .0156 , 0.0083 - - 0 . 0 g W

-----

)

~V'"

- ) 0 8 8 9 2 - 08 92 21 61 10 47 09 66 95 96 75 70

ri 87 52 56 87 50 50 66 06 87 82 77 52 43

.43 . . 74 . . . . . . . 76 . 84 . . . 64 .9 .4 .11 . 0 1 . . . . . .71 . .39 . . . 0 3 . . . 0 3 . . . . .

( --- --- .3 . 79

,5-vBs --- fu 3.3 3.6 ( g 61 59 59 59 60 59 58 56 - 57 58 58 57.76 55 57 57 57 58 58 59 58.53 58 58 58 59 59 60.28 59.51 63.64 62 62 63 63 62 62 62 6 62 62 59.93 60 59 58 59.96 59 58.85 -- -- 63 6 60 61 . 60 61.16 ---- W 55 2 0 4 - 55 78 3 7 92 4 3 T5 935 949 968 --- ~ (OR) 1279 1435 1019 1102 1746 1 9 - 171 2011 1556 1757 1488 1694 1780 1832 1912 2089 1719 1773 201 1573 1666 14 1671 2131 2222 1845 2081 1619 --- 191 1948 2155 1800 19 1505 1925 1973 2068 2214 1783 16 1940 1989 1652 1730 2107 2060 1813 1895 1898 20 - 6 6 - . 0 . 0 . 8 . 3 .9 .4 . 8 . 7 . 0 . 7 .3 . 6 . 6 . 8 . 4 t . 5 . 0 . 1 . 0 .9 .1 .3 . 5 .4 . 5 . 2 .4 . 1 . 8 .3 . 3 . 5 .1 . 7 . 7 -- 3.

3.3 4.4 -- 6H rs- 16.8 16 12 11 11.6 11.0 11 21.4 27 - 23 20 2 20 24 21.0 19 19.4 18 22 20 20 19 18 22 21.6 2 21.2 27.0 25 25 25 2 23.8 21. 20 22.7 22 18 27 26 25 27 . 2 26 25 25 17 - 26 25 25 25 18.9 20 19.

(~) 3 2 5 3 1 7 4 0 -- 39 08 8 3 02 67 62 - - 00 42 074 088 857 590 224 015 052 816 60 855 787 674 771 095 88 N 3 2 3 2892 2870 2847 2777 267 44 418 -- 4239 3934 4 3 3804 3 434 4311 40 3 8 4 4 3925 4 3948 3 394 4211 4147 3 4192 4013 4083 3 3 39 38 3 3 33 4 4009 3 4071 39 391 3870 391 3843 40 40 4 4017 4015 3879 -- (rpm)

7s

5 3 8 0 1 - - - 53 6& 82 39 00 07 - - 20 618 608 581 869 614 62 645 786 722 642 573 745 652 551 698 600 611 75 622 474 434 586 .78 .4 .5 .49 .44 .541 .4 .441 .14 -- --- Ps/PS --- 1 . 1 . 1.574 2 . 2 2 . 2 .

1.954 1.892 1 . U6~ 2.806 2 . 2 2 . 2 . 2 . 2 . 2 . 2 . 2 . 2 . 2 . 2 . 2 2 . 3 2.6 2 2 2 . 2 . 2.414 2 2 2 . 3 2 2 2 . 54 6 2 . 2.655 2 . 2.567 ----- - 2.718 2.984 2 . 2 . 54 6 2 . 4 24 - 2 . 5 I~:~~~ '"--'"""0.

3 .... - - 01 22 26 26 3 0 06 3 9 7 6 2 4 4 2 -- 604 -- 343 5 3 2 339 202 -- -,-- 7252 7116 721 6688 7050 nt 6904 6167 6612 7000 5969 5802 5722 6122 6190 70 6742 7617 7120 8424 80 67 7953 7144 8228 8078 81 8128 5862 6607 5984 .7 . . . .6994 . . . . . . 63 .77 . . . . .71 . . 63 . . 610c) . . . . . 83 . 8 . .7957 .8131 -- . .819 .6878 . . .7 . . . .81 . . .8 .7719 .7046 . . .6193 . _ --- ---- 0 ------ - - - - - 0.8 ) 1 ,5 98 96 75 __ 41 58 87 88 97 50 07 48 86 66 56 40 49 01 62 08 77 81 33 01 22 24 20 30 77 28 27 75 . . . . .9 . . . . . . . 30 . . . . . . . . 63 . 61 g .93 . . . . .

W s;~ 4.39 1.12 3.21 3.

3.07 1.92 3.

( 32.49 24 2 24.49 23 . 23 . 30 31.04 30 30 . 9 2 31 28 28 24 24 30 32 31 31.47 30 . 74 3 2 . 31. 30 . 28 29 25 24 . 3 31 30 30.56 31. 28 28 28 25 24 23.03 22 22 2 2 2 23 22 2 24 23 23 . 23 . 23.54 2 -_ ) 0 8 8 0 - ,1 22 24 79 10 69 20 62 58 75 23 99 29 99 25 60 67 72 91 91 21 22 80 91 97 68 93 21 39 . . . . . .1 . . . .1 .13 .4 . 4 6 . 54 . .3 .23 . . . . . .97 .

a ~ a;~ 4.

W 0.72 0.52 3. 3.42 2.96 ~- ( 3 2 . 31.65 31.97 24 24.22 24.31 23 23 30 . 30 . 30:52 30.11 30.44 31.41 28 28 24 . 2 30.59 31.67 31.3 30 . 30.40 32 31.44 30 28 28 25 24 . 30.45 30.90 3 30 . 28 28 22 3 30 . 30 28 25.09 23 . 22 22 22 22 22 22 21 . 21 2 2 22 2 23 2 3 ----- ----- 3 4 0 9 2 09 85 11 60 00 Ts 988 753 765 782 825 89 612 (OR) 1121 1251 1335 1351! 1201 1442 1082 126 1028 1207 1306 1 34 0 142 1510 1239 1289 1398 1481 1108 1190 1030 1200 1336 1493 1562 1278 1469 1539 1166 13 1385 1071 1420 14 1 13 14 1440 147 1403 1 2 1177 1 1502 1359 1383 1402 1528 1230 ) ____ 0 1 4 4 _ 34 99 39 65 28 34 856 960 --- 681 691 714 746 695 728 74.7 666 855 61 0 695 54 607 697 752 793 8 689 765 800 8 30 609 670 546 61 3 714 7 834 692 790 8 3 8 6 71 76 69 563 579 62 612 558 535 5 582 4 4 4 7 574 503 558 568 587 63 7 4 Ps s~bft __ ( - 2 3 3 0 22 02 3 7 33 97 10 33 T5 827 840 855 900 975 -- 240 655 560 --- (OR) 1130 1263 1467 1643 - 1430 1680 129a: 1468 1248 1415 1515 1542 1622 1775 144 1500 1608 1690 1 3 1398 1 14 16 1797 1870 1550 1755 182 1370 1515 1 6 1273 1623 1720 180 193 1 1 1740 1810 - 1 6 1427 1480 177 1555 1607 1 6 17 ) 6 6 3 2 4 3 4 6 2 6 - 9 5 60 85 28 47 00 46 44 14 891 99 62 P5 1673 1816 1097 1102 1111 1129 llH 1997 2045 2096 1911 2235 1699 182 1436 1489 1942 20 20 2 1 2029 2061 2053 1643 174 14 14 188 1 2041 1807 1923 202 1 1704 175 136 14 1520 15 1589 1472 1500 152 1571 --- --- - 1560 1501 IH3 14 1479 15 ---- s~bft ( 3 3 9 3 6 3 3 44 -- 43 47 - T4 615 62 54 5 5 42 5 549 680 786 697 707 67 668 670 665 677 667 670 740 66 676 671 672 671 672 661 669 776 785 791 7 765 711 670 671 726 663 670 809 816 781 787 792 79 730 734 799 787 822 67 695 681 673 67 (OR) 2 5 5 5 6 7 6 0 0 5 59 38 T2 458 457 459 4 45B 4 459 436 436 435 434 434 433 434 435 434 44 437 440 441 43 439 437 436 435 43 435 43 438 43 439 439 4 43 43 438 437 438 439 453 453 452 454 454 454 454 448 444 446 446 445 440 44 44 44 (OR) ) l't 6 8 7 7 08 05 07 07 06 08 21 09 09 01 05 05 05 06 07 07 06 08 00 16 17 19 11 12 17 P2 781 795 791 790 792 788 7 92 4 40 4 408 4 4 4 4 40 41 4 428 4 4 41 434 4 2 4 4 4 413 40 4 4 4 4 4 4 414 405 4 4 4 04 4 04 306 3 297 3 317 317 3 313 306 3 3 314 3 317 3 - -- s~b ( - 0 0 0 4 4 ) 91 70 9 8 23 44 4 2 13 Wf ~ 96 610 620 640 670 735 948 7 9 969 804 97 970 854 8 870 90 ( 1160 1252 137 1439 1170 1651 1197 1331 1445 1562 1717 1230 1361 1520 1622 1100 14 1620 1750 1330 1562 1725 1052 1267 1391 1229 10 1180 1370 1072 1126 1172 1319 12 1115 118 13 97 97 97 53 9 7 N 353 353 353 353 7260 7260 7260 6897 68 7260 7260 7260 7260 7260 - 4719 4719 3 630 3 6 30 3630 3 630 3630 6 6 5808 5808 6897 6897 6897 S8 6 6353 5808 5808 7260 7260 6897 6897 68 6 63 5 3 6353 5808 5808 7260 7260 7260 6897 6897 6897 6897 63 6 7260 7260 6897 68 6897 6897 635 (rpm) 0 0 0 0 0 0 ft) 67 67 20 20 67 6 7 67 67 30 30 1.67 1.67 1. 1.67 1.67 1. 1.67 1. 1.20 1.20 1. l.20 l.20 l.2 1.20 l.20 1.3 1.30 1.30 1.3 1.3 1.30 1.30 1.30 1.30 1.30 l.3 l.30 1.67 1.67 1. l.67 l. l.S7 1. l.67 1.67 1.67 1. 1.30 1.3 1.30 1.30 1. 1.30 1.30 1. 1.30 1.67 1.67 1.67 1.67 1.67 1.67 1.67 area

Turbine nozzle (aq

6 8

it) 4 5 2 2

75 75 76 72 75 89 97 12 15 08 08 10 11 Po S0 603 608 610 S07 608 609 37 375 376 378 39 3 375 3 3 375 391 39 386 387 4 0 3 394 383 3 379 36 374 374 373 3 3 375 38 374 377 373 373 373 303 2 295 312 312 312 3 308 303 3 306 3 3 3 3 30 4 s~b -- -- ( 2 3 6 9 27 27 26 27 61 38 S18 642 624 619 629 621 625 3U 31 334 O 341 341 344 344 341 340 28 32 311 338 341 257 118 130 152 152 125 160 16 160 --- . . . . . . .3 . . . . . .341 . . . 3 . 30 3 . . . 3 . . . 3 .351 .381 . . .348 .338 . .341 .338 .338 . 32 9 .3 .338 . 3 .107 . . . . . . 13 6 .125 .152 .152 . . . 14 1 .16 .

M 0 . 0 . 0 -- '-- tude 000 000 000 , t1 (ft) 30, 40 , 44 Al ..--~--...-..-----~~-~ 4 9 6 3 4 6 3 31 32 41 43 46 54 55 77 22 225 226 227 228 22 23 0 2 2 23 3 234 23 5 23 6 23 7 23 8 23 9 24 0 2 24 2 2 24 4 24 5 2 2 4 7 248 24 9 25 0 251 25 3 2 2 25 257 258 25 9 260 261 262 26 26 26 267 268 269 2 Run 2 5 2 265 270 271 272 27 274 275 2 7 6 2 78

-~

___

2: f:i :x> ~ t>::l (]l [\) y [\) o ~ --l

·28935 C tunnel.

wind de tiu a l in engine et j turbo of - tion lla turt1ne a -~ st In area - - 1.

Variable Figure r- .-~~~-~~---

r

-~-~ ~ ~ - t?;j Ul [\) Y [\) o

~ ~ ~

t-' CD CD·2732 installed

~

was - I

I

0 0 6 0 0 10 24 Turbine Tbermo- couples - --- instrumentation static -- 4 4 7 2 0 8 Combustor wbicb orifices Wall pressure ------ - at e 0 3 0 0 0 2 Static pressur tubes stations r esso r sbowing 29 18 23 15 20 16 Comp Total pressure tubes lation al outlet inst let in outlet zle duct utlet inlet o inlet Location t-engine je duct xhaust-noz Inlet-air Compressor Compressor Turbine Turbine Engine E turbo air - of 1 2 3 4 5 7 Inlet Station view Top - 2.

~

e onent flow mp Figur -- Station - Co

Air ----~

------ ---- --- - - -

NACA RM E52J 20

(a ) Fi r st - stage tu r bine rotor .

Figure 3 . - Photog r aphs of turbine rotors .

20 NA CA RM E 52 J 20

j

I

I

i

I

(b ) S econd - sta ge tur bine r oto r .

F igur e 3 . - Co ncluded. Phot ogr aph s of turbine r oto r s .

NACA RM E5 2J 20

(a ) Open .

Figu r e 4. - Photograph s of variable - ar ea turbine n ozzles .

---,--- -. _-

22 NACA RM E52J 20

(b ) Cl osed .

Fig ur e 4 . - Co ncl uded . Ph ot ogr ap hs of var iab l e - a r ea turbin e nozzl e s .

NACA RM E52J 20 23 M ain actua t ing sha ft N ~ zzle actuating rJ.ng

/

" ...-- - -- - --- ;>

Variable-area turbine - nozzle vane ~ Turbine- inlet -ann ulus inner skin F igu re 5 . - Schemati c sketch of variable-area tu r bine -n ozzle act u ating me chanism.

NACA EM E52J20

t Open Closed

l

~

r f1

Tip , I

I

,

i

, I , I , , I , , , , .835" 2 , , , , ,

I

I

I

, , I , , , , I , ,

j

4 1

-;r- , I ,

I

I

I

,

I

, , , ,

I

, . 782" 2 I

I

I

I , I

I

, , \.

"

" J '\ I ,

I

, '\ ,

"

, \ ,

,\

\ \ Hub

"

\ \

L d

\\

\ \ \ \ \ \ \ \ \ \ \j (a) ~d-vane cross - sections of two adj ac ent (b) Side view of vane (actual size) .

van e s (2~ times actual size).

Figure 6. - Sketches of variabl e - a r ea turbine -nozz le vanes in open and closed positions .

\

I

______ J

NACA RM E52J20

(b) Station 4, co mpressor outlet.

(a) Station 1, cowl inlet . Diame- ter, 34 inches; location, 6 inches Passage height, ~ inches; loca- downstream of cowl-inlet flange.

tion, 1/2 inch downstream of trailing edge of fixed vanes.

o Total p r essure

• Static pressure

>< Thermocouple

"'~

(c) Station 5, turbine inlet. Pas - (d) Station 6 , t urbine o utlet. Pas- sage height, ~ inches; location, sage height, ~ inch e s; l o cation, li inches upstream of leading ~ inches downstream of trailing edge of first - stage turbine - nozzle edge of t urbine rotor.

diaphragm.

Figure 7. - Location of instrumentation (view looking downstream).

NACA RM E 52 J 20

Measured turbine- nozzle area (sq ft) 0 1 . 67 ,Q-,O DIAO 0 1.37 ~ ~Of::l

~

;.

1.30 -,..n(;: tv ._ OI

tn..n

ri rL-n 1.2 0 'H (J ~ -AlJ: 1.15 ~ ~~

~ N

til <II

f!: ~

~ n../

oS til bO ........

I .0 ..

D..< I ri

;n ~~

2l

)

.... D.. /'

~

~

~ u·-n

y--

;;: ~8..1

8 ~~ .p(J)ri

1 7 ~

-b

~ ~ N1

~AI\

" ~

/J

<II lf) >-

"" 56

.p ;>:

.....-

LV Zl

U If) I I ~ <10 2 . 8 Turbine pr e s -

~

M

'..1 ,'''- PA sur e rati o

2.4

it

t.l I-' 1 . 6 ,6

to

2600 3000 3400 3800 4200 Corrected turbine speed, N/ ~ , rpm Figure 8 . - Effect of tu r bine-nozzle area and corrected turbine speed on co rrected turbine gas flow. Altitude, 30, 000 feet ; fligh t Mach number, 0 . 62 .

Effective turbine - nozzle area, s q f t 1.2 5

~

1. ~

--

/'" V

1. ~

L tv

1.1 1. 2 1 . 4 1.3 1.5 1. 6 1.7 M e asured turbine-n o zzl e area , s q f t Figure 9 . - Var iation of maximum corrected turbine ga s flow or effective turb i ne - noz zle area with m easured turbine - nozzle area. Altitud e 30 ,0 06 feet; flight Ma ch number 0 62 , . 90 ~

D.. h r:a ;gA

:» (J . "1 o

... ~<>

<II [lJP~ ....

Ll,l.

U

~ ~~

~ Ll<)

~Ll

~ ~

~ .80 z:

"

'H

OLJ

~~

<II

8~

DO 0

Cl)

~! ~

....

'"

D..

f:

O~

~

e:: I I . 70 2600 3000 3400 3800 4200 4600 Cor rect ed turbine speed, N/~, rpm Fi gure 1 0. - Effect of tu rb ine - nozzle area and corrected turbine speed on turbine efficiency . Al t i t ud e, 30,000 feet; flight Mach numb e r, 0 . 62.

_ _ _____ _ _J

NA CA :RM E52 J 20 3 . 2 Engine speed (rpm ) 0 7260 0 6897 <D

~ 6353

p..,

<>

ty.

~

2 . 8 If) A p..,

-----

A 4719

V

Q 3630

--

~ /

oM +> al ~

~rf

Q)

/

~ 2 .4 ;::!

U) U) Q) ~

~

Pi Q) ~

V

'M

6'"

f!

2 . 0 i: £1-

hf

1. 6 (a) Variation of turbine pressure ratio with corrected turbine speed at constant engine speeds.

. 9 0 :1...-.,...

y-O-

-0

rr

A..

~ ~

r

~l:J.

+>

~

~ . 8 0 }1

--- (;)

}

Q V U (b) Variation of turbine efficiency with corrected tur- bine speed at constant engine speeds.

l.- I

I

Turbine pressure ratio 2.8 2.9 2.7 /./

~/ V/

/ ~

c . 8 I

2400 2800 3200 3600 4000 4400 Corrected turbine speed, N/~, rpm (c ) Cross plots showing variation of turbine efficiency with corrected turbine speed at constant values of turbine pressure ratio.

Figure 11. - Effect of various par am eters on turbine pressure ratio and turbine efficiency. Altitude, 30,000 feet; f l ight Mach number, 0.62; turbine nozzle area , 1.15 square feet.

NACA RM E52J20

3. 2 Engine sp ee d (rpm ) to p.. 6353

~ / b

-........

If) 6 2 . 8 p..

P"

LI " cJ 3630

~ A

oM +> aI H

~

(])

~

H 2 . 4 ;::5 If) If) (]) H

~

Pi (]) ~ s:: oM

//

2.0

~

Q kr6l

1.6 (a) Variati on of turbine pressure ratio with corrected turbine speed at c onstant engine speeds .

. 90 , --<>-< b

~

)

i?

+> ,.,.

~ -

.80

A

" >.

1 Lt-"'-

() s::

% ~

(]) ~ oM ()

.d

oM

a

.....

.....

(]) . 70 (]) (b) Variation of turbine efficiency with corrected tur- s:: 'M bine speed at constant engine speeds.

- . 90

I

~ I

I

Turbine pressure ratio

y;;{Y\

~

I"

.80 2400 2800 3200 3600 4000 4400 Co rrected turbine speed, N/~, rpm (c) Cross plots showing variation of turbine efficiency with corrected turbine speed at constant values of turbine pressure ratio.

Figu re 12. - Effect of various pa ramet e r s on turbine pre ssure rati o and turbine e ff ici enc y. Al titude , 3 0, 0 00 fe e t; f light Macb num ber, 0 . 62 ; turbine nozzle ar ea , 1. 20 squar e feet .

NACA RM E52J20 Engine speed (rpm) , .

0 6897

<>

6.

2 . 8 5808 L:I 4719

;/'

<D t:] p.,

10 ~ -

-......

L() p.,

V

~

A ~

.,., 2 .4 +> aJ

wcr

H Q)

/

H ;j IY Ul Ul QJ H

~

P< 2 .0

b""'v

QJ s:1 -rl ~ ~

.... ~

1.6 ....

(a) Variation of turbine pressure ratio with corrected turbine speed at constant engine speeds .

. 90 ~ t. r.....-- ~

~o

op

~

~ 4 ....-1:.6 +> ~ . 80 ~ ~6,..

V6

y >.

()

6'

s:1 ~

QJ -rl () -rl 'H .

'H QJ .70 ( b) Variation of turbine efficiency with corrected tur- Q) s:1 bine speed at constant engine speeds .

-rl . 90

~

I

Turbine pressure ratio 2.6 2.7 2 . 5 ,.,

;r ~V-

~

T

. 80 2400 2800 3200 3600 4000 4400 Corrected turbine speed, N/~, rpm (c) Cross plots showing variation of turbine effic i ency with corrected turbine speed at constant values of turbine pressure rati o .

Figure 13. - Effect of various parameters on tur b ine pressure ratio and turbine ef ficiency. Altitude, 30 , 000 feet; flight Mach num ber, 0.62; tu rb ine nozzle are a, 1.30 square feet.

-- --- ---------- - - - --

NACA RM E52J20

2 . 8

~

I p/

<D ~

P.,

~ ~

-.......

2 .4 If) /-l P.,

~

~ o~ .,; +' Engine speed al H

~

(rpm) QJ 72 60 2 . 0 Ul Lt'~ 6897 Ul QJ

H <>

I'll 5808 b.

QJ

L:l

I'i .,;

LJ

..... lLJC.1

-e 1.6

~ ~ 1.2 (a ) Va riat ion of turbine pressure ratio with corrected turbine speed at constant engine speeds .

. 90 I ~ n ~ 1'-'"'"0'-

a

~

~

.....

<: . 80 v

'2r-

~4 Ll

~

+' kP

<="

a

:>::

" I'i

QJ . 70 .,; (b) Variation of turbine efficiency with corrected tur - .,;

"

'H bine speed at constant engin e speeds .

'H QJ . 90 QJ I'i Turbine pressure ratio .,; 2 .5 2 .3 2 .4 2.6·_

-e

~

V ~·7

V /

1/

. 80

II

~

I I . 70 2800 3200 3600 4000 4400 Corrected turbine speed, N/~, rpm (c) Cross plots showing variation of t urbine efficiency with corrected turbine speed at c onstant values of turbine pressure r atio.

Figure 14. - Effect of various pa rameters on turbine pressure ratio and turbine efficiency.

Al titude, 30 , 000 feet ; flight Ma ch number, 0.62 ; turbin e nozzle ar ea, 1.37 square feet.

I

J

NACA RM E52J20 Engine speed (rpm) 2 . 8 7260

<>

A.

I ~

~

~

<D p.,

LI

A ~

2 .4 "in p.,

~

~

0' .....

+' ., ~ OJ

~

At 2.0 ~ ., ~ (/)

L1./'

OJ ~ P, OJ <=I .....

d1 1.6

o-u

~

1.2 (a) Variation of turbine pressure ratio with corrected turbine speed at constant engine speeds .

• 90

V

~

~ ~

. 80 t:ij

~

V

6"

~ ~ -"" :; . 70 ~ CI >: u <=I OJ .....

U .....

'H 'H OJ . 60 (b) Variation of turbine efficiency with corrected tur- bine speed at constant engine speeds .

• 90 Turbine pressure ratio -2.4 2 . 5 2.6

//

2/

/

. 80 I

~

. 70 1 J.

2400 2800 3200 3600 4000 Corrected turbine speed , N/ ~ , rp m (c) Cross plots showing variation of turbine efficiency with corrected turbine speed at constant values of turbine pressure ratio.

Figure 15 . - Effect of va rio us param ete r s on turbine pr es s ure ratio and turbine efficie nc y.

Al titude, 30,000 feet ; f li ght Mach pum be r , 0 . 62 ; turbine nozzle area, 1.67 square feet.

NACA RM E 52 J 20 Measured turbi ne- nozzle area (sq ft) 1. 67 0 1.37 1.30 [:),.

1.20 1.1 5 ~ . 90 <'} ~

-

~

':%

~

~

~

.80 (a) Turbine pressure ratio, 2 .7 .

. 90 +' . 80

"'"

~ » (b) Turbine p ressure ratio, 2 . 6 .

() q . 90 QJ .,-i () .,-i 'H 'H (' ..0 QJ QJ ~ ) q .,-i

~ ~Jt ~

. 80 ~ ~ (c) Turbine pressure ratio, 2.5 .

• 90 ~

b

g

~ ~

. 80

1 0

~

. 70 I 3800 4000 42 00 4400 3400 3600 Corrected turbine speed, N/~, rpm (d) Turbine pressure rati o, 2 .4.

Figure 16. - Effect of turbine - nozzle area and corrected turbine speed on tur- bine efficiency at constant va lues of turbine pressure ratio. Altitude, 30,000 feet ; flight Mach n um b er, 0.62 .

tJ.l tJ.l t:tj [\) [\) o

!2: f) ~ ~ CJl Y

""\.

..

es

l

T

are;

nozz

0 . 62 ;

les

~

e

ine

4300 nozzle

nozz

-

~

urb

t

number,

Fixed Variabl

....

rpm

turbine

Turbine

fixed Mach

ith

0 0

w

N/,j85, actual

flight

;

an

~ speed,

for feet

obtained

~·I 4100

b

30 ,

nozzles

turbine

~

4000 efficiencies

turbine

of Altitude,

Corrected

.

rpm .

---.'-~ ...

El

feet

Q ~

parison

3900 m

Co

-

variable-area

square

speed, 17 .

with

1 . 30

and of engine

. 80 .70

. 90

Figure

.~.------ ....

+' '; Q) Q) Q

>=" :» () Q Q) ()

' ''; Ct-i Ct-i ...-I -e ~

, g

z ~ > t- '" '{' .. ';' '" w

~ '<

~~~---