Numerical Parametric Study of Inlet Distortion Propagation in Compressor Using Integral Approach with Taguchi Method

Abstract

Due to the advancement in aircraft propulsion, there is a need to understand compressor surge and stall from the engine operational requirement. Distorted inlet conditions in axial compressors may create large oscillations of the mass flow rate, which is known as “surge,” and self-induced circumferential flow distortions rotating around the annulus, which is called “rotating stall,” or a combination of both phenomenons may exist together. Therefore, it is important to carry out analysis on the parameters that may result in either surge or stall. This study looks into the research that has been done by Kim et al. [9] (on the distorted inlet flow propagation in the axial compressors). Integral method is applied to the problems of distorted inlet flow, investigating on the relationships and the effects that some of the key parameters would have on the propagation of inlet distortion flow. The objective of this study is to justify the findings from Kim et al.'s research by using Taguchi's quality control method. The results indicate that major parameters on the inlet distortion propagation are the ratio of drag-to-lift coefficient, the inlet distorted velocity coefficient, and inlet incidence angle in influence order. This conclusion is different from that in Kim et al.'s research. Their research was carried out using only a few test cases with integral method. When integral method with Taguchi quality control method is used, the prediction of degrees of influence by the parameters on the distortion propagation becomes more reasonable and accurate.