关键词: 燃气涡轮发动机;进气道;畸变;气动稳定性

Abstract: A coupled compressor-diffuser flow model was developed for predicting the response of a twin-spool turbine engine to inlet pressure distortion. A new method was presented to analyze the performances and aerodynamic stability of the engine with the presence of a circumferential total pressure distortion. Analytical results showed that large static pressure non-uniformities could exist at exit of high pressure compressor due to the effect of the flow coupling between the high pressure compressor and a downstream diffuser. It was found that the surge margins of both low pressure and high pressure compressors were decreased with the increase of inlet pressure distortion levels. It was also remarkable that a reasonable relationship between thrust of the engine and its inlet distortion level could be obtained by using flow coupled model developed in this paper.

Key words: Gas turbine engine;Inlet;Distortion;Aerodynamic stability