Performance of a short turbojet combustor with hydrogen fuel in a quarter-annulus duct and comparison with performance in a full-scale engine Page: 2 of 37
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NACARM E56D16 176 014358478
NATIONAL ADVISORY CoCMITTEE FOR AERONAUTICS
RESEARCH MEMORANDUM
PEFORMANCE OF A SHORT TURBOJET COMBUSTOR WITH YIOGEN
FUEL IN A QUARTER-ANNULUS DUCT AND COMPARISON
WITH PERFORMANCE IN A FULL-SCALE ENGINE
By Robert Friedman, Carl T. Norgren, and Robert E. Jones
SUMMARY
A number of short turbojet combustor configurations for hydrogen fuel
were designed and their performance investigated in a quarter-annulus
duct. The best combustor liner consisted of an annular primary zone and
a secondary zone composed of T-shaped channels sloping from the primary
zone to the combustor wall. The fuel manifold consisted of two concen-
tric spray bars within a V-gutter flameholder with separate fuel connec-
tions to either spray bar for control of the initial fuel distribution.
The distance from the fuel injectors to the instrumentation plane was 19.4
inches.
The quarter-annulus combustor operated at combustion efficiencies of
84 percent or greater at combustor-inlet total pressures as low as 5.7
inches of mercury absolute. Combustor reference velocity had little ef-
fect on combustion efficiency even at velocities as high as 270 feet per
second. At a reference velocity of 80 feet per second, combustor total-
pressure loss ranged from 3.0 percent of combustor-inlet total pressure
at isothermal conditions to 4.7 percent at a combustor total-temperature
ratio of 3.6.
The quarter-annulus combustor for hydrogen fuel was also scaled to
fit a production-type, full-scale engine. This combustor was about two-
thirds the length of the standard combustor for this engine. Combustion
efficiency and total-pressure loss of the full-annulus combustor were ap-
proximately the same as those determined in the quarter-annulus duct.
Desirable outlet-temperature profiles were obtained by controlling the
fuel distribution to separate manifolds of a dual fuel manifold.
INTRODUCTION
HBydrogen fuel offers advantages for the airplane in that (1) the high
heat release per pound of this fuel can greatly increase the operational
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Friedman, Robert; Norgren, Carl T. & Jones, Robert E. Performance of a short turbojet combustor with hydrogen fuel in a quarter-annulus duct and comparison with performance in a full-scale engine, report, July 2, 1956; (https://digital.library.unt.edu/ark:/67531/metadc62663/m1/2/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.