Effect of inlet geometric distortion on the aerodynamic performance of a multistage compressor

Abstract

This paper presents a comprehensive study on the effects of inlet geometric distortion on the aerodynamic performance and stall dynamics of a multistage axial flow compressor, a critical component in various high-performance industrial applications. Using a combination of experimental testing and full-channel numerical simulations, we analyze the performance degradation, energy loss mechanisms, and stall onset under varying distortion conditions in a 3.5-stage compressor. Our study introduces three distinct inlet distortion configurations and provides novel insights into how the number of distortion zones and radial distortion range influence compressor efficiency, pressure ratio, and stall margin. The results highlight that increased radial distortion exacerbates performance losses and narrows operational stability margins. Additionally, the study sheds light on the detailed stall mechanism by identifying the premature breakdown of tip leakage vortices as a key factor in accelerating stall development under distortion conditions. The innovation of this work lies in the integrated approach of experimental validation and advanced simulation to dissect the complex interaction between distortion-induced flow separation and compressor stall onset. These findings contribute to the development of more robust axial flow compressor designs, particularly for applications involving non-ideal inlet conditions, advancing the understanding of distortion-induced performance limitations and stall mitigation strategies.