Effect of liner air-entry holes, fuel state, and combustor size on performance of an annular turbojet combustor at low pressures and high air-flow rates

Norgren, Carl T., Childs, J. Howard.

An annular combustor with liquid fuel injection was developed utilizing existing design principles. Operation with heated liquid and vapor fuels gave combustion efficiencies up to 23 percent greater than liquid fuel at severe operating conditions. Combustion efficiency was not impaired by increasing the flow velocity to values 30 percent above current design practice. At a still higher velocity, however, the efficiency decreased markedly at high fuel-air ratios. The combustion efficiency was higher at severe operating conditions than the efficiencies of 14 turbojet combustors previously investigated; evidence is presented which indicates that this high efficiency may be due to the large size of the combustor.

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