Turbojet combustor efficiency with ceramic-coated liners and with mechanical control of fuel wash on walls Page: 6 of 45
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NACA RM E52125 5
Test Conditions
Combustion-efficiency data were obtained for a range of fuel-air
ratios at each of the following test conditions:
Condition Cambustor- Combustor- Air flow per
inlet total inlet total unit frontal
pressure temperature area
(in. Hg abs) (OF) (1b/(sec) (sq ft))
1 15 268 2.78
2 8 268 1.485
3 15 268 2.14
4 15 268 3.62
aBased on maximum cross-sectional area of combustor
housing (0.48 sq ft for J47 and 0.267 sq ft for
J33 combustor).
Test conditions 1 and 2 simulate inlet-air conditions encountered
in typical turbojet engines at high altitudes and high flight speeds.
Conditions 3 and 4 represent air-flow rates about 23 percent below and
30 percent above current operation, respectively.
Combustion efficiency was determined as the ratio of actual enthalpy
rise across the combustor to the enthalpy supplied by the fuel and was
computed by the method described in reference 6. In addition to com-
bustion-efficiency data, rich ccmbustor blow-out limits were recorded.
MIL-F-5624A, grade JP-4 fuel was used for all combustion tests
reported herein. Physical properties of the fuel are presented in
table I. The simulated tests in the transparent cambustor were con-
ducted with water in place of fuel in order to obtain more distinct
photographs.
RESULTS AND DISCUSSION
The combustion efficiency and flame blow-out data obtained in the
J33 and J47 combustors at various combustor-inlet conditions are pre-
sented in tables II and III.a-
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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; (https://digital.library.unt.edu/ark:/67531/metadc59395/m1/6/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.