Effect of Design Compressor Pressure Ratio on Performance of Hypothetical Two-Spool Nuclear-Powered Turbojet Engines Page: 2 of 49
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NASA Tehnicel
NACA RM E55K04 : -
NACA E553 1176 01436 5457
NATIONAL AD ~ AERONAUTICS
RESEARCH MEMORANDUM
EFFECT OF DESIGN COMPRESSOR PRESSURE RATIO ON PERFORMANCE OF
HYPOTHETICAL TWO-SPOOL NUCLEAR-POERED TURBOJET ENGINES
By James F. Dugan, Jr.
SUMMARY
Hypothetical two-spool nuclear-powered turbojet engines with sea-
level static design compressor total-pressure ratios of 20, 15, and 9
and total-pressure losses between the inner-spool canpressor exit and
turbine inlet of 10 and 30 percent are considered. Each engine op-
erates with the outer-compressor mechanical speed fixed at its design
value and the inner-turbine inlet temperature fixed at its design value
of 21600 R. Performance with chemical afterburning at 35000 R and with
the afterburner inoperative is calculated for flight Mach numbers of 0
to 0.9 at sea level and 0.9 to 2.32 in the stratosphere.
The following results are for the engines with a constant 10-
percent total-pressure loss between the inner-spool compressor and
turbine. For operation with the afterburner inoperative, the maximum
equivalent net thrust for the 9:1 pressure-ratio engine is about 30
percent greater than that for the 15:1 pressure-ratio engine, and 51
percent greater than that for the 20:1 pressure-ratio engine. At each
flight Mach number, however, the higher-pres sure-ratio engines have the
lower values of specific power (ratio of reactor power to engine net
thrust) and require the smaller ducts downstream of the compressor exit.
For operation with afterburning at Mach 2.32, thrust for the 9:1
pressure-ratio engine is about 8 and 18 percent greater than the thrust
for the 15:1 and 20:1 pressure-ratio engines, respectively; whereas the
specific fuel consumption advantage of the 9:1 engine is about 8 and 16
percent, respectively. Specific power, however, for the 20:1 pressure-
ratio engine is about 25 and 41 percent less than the specific power
for the 15:1 and 9:1 pressure-ratio engines, respectively.
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Dugan, James F., Jr. Effect of Design Compressor Pressure Ratio on Performance of Hypothetical Two-Spool Nuclear-Powered Turbojet Engines, report, April 10, 1955; (https://digital.library.unt.edu/ark:/67531/metadc61676/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.