Investigation of X24C-2 10-Stage Axial-Flow Compressor 2: Effect of Inlet-Air Pressure and Temperature of Performance Page: 2 of 41
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NAGA RM No. E7H22 .T",3 1176 01425 9684
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
RESEARCH MEMDRANDUM
for the
Bureau of Aeronautics, Navy Department
INVESTIGATION OF 1240-2. 10-STAGE AXIAL-FLOW COMPRESSOR
II - AFFECT OF INLET-AIR PRESSURE
AND TEMPERATURE ON PERFORMANCE
By Harold B. Finger, Harold J. Schum, - and Howard A. Buckner, Jr.
SUMMARY
An investigation was made to determine the effects of inlet-
air pressure and temperature on the performance of the 10-stage
axial-flow compressor from the 1240-2 turbojet engine. The inves-
tigation was conducted for speeds of 80, 89, and 100 percent of
equivalent design speed with inlet-air pressures of 8 and 12 inches
of mercury absolute (424 and 849 lb/sq ft) and inlet-air tempera-'
tures of approximately 5380, 4590, and 4190 R (790, 00, and -400 F)
The results of the investigation of the effect of inlet-air pres-
sure were compared with the results of the previous performance
investigation at a nominal inlet-air pressure of 21 inches of mer-
cury absolute (1485 lb/sq ft) and an inlet-air temperature of
approximately 538 R to give a larger range of inlet-air pressures.
The peak values of adiabatic temperature-rise efficiency and
pressure ratio were found to decrease as the inlet-air pressure
was reduced at constant inlet-air temperature. The effect of
inlet-air pressure on equivalent weight flow was small, the rela-
tive deviation reaching a maximum of about 1 percent. Variations
in inlet-air temperature had only a slight effect on the same per-
formance parameters. All data obtained at various inlet-air pres-
sures and inlet-air temperatures correlated on two curves when the
polytropic efficiency was plotted as a function of the polytropic
loss factor. The only effect of inlet-air pressure was to increase
the minimum loss factor and to decrease the maximum polytropic
efficiency as the inlet-air pressure was reduced. The corre-
sponding effect of temperature was negligible. Peak adiabatic
temperature-rise efficiency and pressure ratio increased with
increasing Reynolds number, The fact that the range of Reynolds
number covered in varying the inlet-air pressure was considerably
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Finger, Harold B.; Schum, Harold J. & Buckner, Howard A., Jr. Investigation of X24C-2 10-Stage Axial-Flow Compressor 2: Effect of Inlet-Air Pressure and Temperature of Performance, report, August 21, 1947; (https://digital.library.unt.edu/ark:/67531/metadc63864/m1/2/: accessed April 19, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.