High-altitude performance of an experimental turbojet combustor having variable primary-air admission
Description: Report presenting an investigation of 47 experimental tubular designs embodying variable primary-air openings to control the fuel-air ratio in the combustion zone at simulated high-altitude operating conditions for a representative 5.2-pressure-ratio engine. The performance characteristics considered were combustion efficiency, operating range, and pressure loss. Results regarding the effect of fuel injector design, effect of primary-air baffles, and performance characteristics of the best models are provided.
Date: April 11, 1955
Creator: Straight, David M. & Gernon, J. Dean
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Partner: UNT Libraries Government Documents Department