Turbojet combustor efficiency with ceramic-coated liners and with mechanical control of fuel wash on walls Page: 4 of 45
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NACA RM E52125
Combustion efficiency and flame blow-out limit data were obtained
with the standard and the modified combustors at combustor-inlet-air
pressures of 8 and 15 inches of mercury absolute, inlet-air temperature
of 2680 F, and a range of air velocities and fuel-air ratios. Fuel con-
forming to specification. MIL-F-5624A, grade JP-4, was used for all tests.
The results obtained with the various combustors are compared to indi-
cate possible explanation for the effects of the modifications on com-
APPARATUS AND PROCEDURE
Two types of single-tubular combustor, one from a J33 and one from
a J47 turbojet engine, were used for the investigation reported herein.
The installation of the combustors, including air heaters and control
equipment, was similar to that described in reference 3. Air flow and
fuel flow to each combustor were measured by square-edged orifice
plates installed according to A.S.M.E. specifications and by calibrated
rotameters, respectively. A sketch of the two combustor installations,
showing location and arrangement of the instrumentation planes, is
presented in figure 1. Inlet-air pressures were measured by total-
pressure rakes. Inlet-air temperatures were determined by bare single-
Junction iron-constantan thermocouples; exhaust-gas temperatures were
measured by single-shielded chromel-alumel thermocouple rakes (refer-
ence 3). The axial location of the exhaust-gas thermocouples in each
combustor setup corresponded approximately to the position of the tur-
bine blades in the full-scale engine.
Photographs of the inner liners of the two combustors, showing the
shape and distribution of the air-admission holes, are presented in
figure 2. In both combustors the holes provided for cross-fire tubes
were closed. A hollow-cone swirl-type fuel nozzle having a nominal
flow capacity of 40 gallons per hour (at 100 b/sq in. pressure) and a
spray angle of 80' was used for most of the J33 combustor tests. Lim-
ited tests were also conducted in this combustor with a 15.3-gallon-per-
hour 30 -spray-angle nozzle. The J47 combustor was equipped with a
wide-flow-range duplex-type fuel nozzle. Standard ignition plugs, in
combination with 5000-volt, 60-cycles-per-second transformers, were used
in both J33 and J47 combustion tests.
In addition to the J47 and J33 single combustors used for combus-
tion tests, a transparent J33 combustor was used for visual studies of
fuel-spray characteristics under cold-flow conditions. A complete
description of the transparent-combustor apparatus is presented in
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Butze, Helmut F. & Jonash, Edmund R. Turbojet combustor efficiency with ceramic-coated liners and with mechanical control of fuel wash on walls, report, November 24, 1952; (digital.library.unt.edu/ark:/67531/metadc59395/m1/4/: accessed January 16, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.