Effect of Steady State Inlet Temperature Distortion on the Engine Compressor Flow,

A prediction model for the effects of a steady state temperature distortion on the overall performance of a multistage engine compressor is presented. In contrast to the well-known parallel compressor model, this method takes into account the circumferential interaction of the distorted and undistorted compressor flow. An extensive experimental program has been carried out on a single-spool jet engine with steady-state inlet temperature and pressure distortion tests. The experimental set-up is briefly described. Detailed results of the flow measurements obtained at the compressor inlet and exit and at the compressor interstage positions are presented and discussed. The experimental results support the validity of the prediction model developed within this project.