某型发动机对畸变进气响应的流动耦合分析

Coupled compressor-diffuser flow model for predicting response of a twin-spool turbine engine to inlet pressure distortion

关键词:  燃气涡轮发动机  进气道  畸变  气动稳定性

Key words:  Gas turbine engine  Inlet  Distortion  Aerodynamic stability

摘要:

建立了畸变进气下某型双轴发动机高压压气机 扩压器间流动耦合模型,完善了畸变进气对发动机稳定性影响模拟方法。数值模拟结果表明,考虑耦合影响给出的高压压气机出口静压畸变与其总压畸变不仅相位相反,而且随进口总压畸变强度变化而变化。据此所给出的高、低压压气机畸变响应和发动机推力响应特性也与进气道 发动机相容性理论相符合。

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.