Abstract

This paper describes how the effect of inlet flow distortion to a turbojet can be evaluated by a distortion model of whole engine, which is based on mass, momentum and energy conservation, and has been proved to be a valid tool for evaluating the effects of inlet flow distortion on turbofan.

In this model, pressure (or temperature) distortion is quantified with coefficient which associates the pressure (or temperature) in the spoiled sector with the value in the clean sector. Detailed computation and analysis under different overlap phase and distortion intensity are conducted on the stability of turbojet after the representation of combined distortion index. It can be concluded that there is a maximal loss of stall margin when total pressure distortion sector laps over total temperature distortion sector completely. The reduction of stall margin arising due to combined inlet distortions can be minimized through the optimization of a disturbance overlap phase.

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