Impact of Identical Volume Notch Damage at Different Locations of Rotor Blades on the Aerodynamic Performance of Transonic Compressors

This study aims to provide data and theoretical support for evaluating the aerodynamic performance of compressors with blade notch damage under operational conditions. Taking the NASA Rotor۳۷ transonic axial compressor rotor blade as the research object, it incorporates the characteristics of damaged blades in real service scenarios and establishes equal-volume notch damage models at six typical locations of the blade. Specifically, these positions include the tip, mid-span, and root at the leading-edge and trailing-edge of the blade. Using numerical simulations of a single-blade passage and taking the aerodynamic performance of intact blades as the baseline, the study quantitatively analyzes the degradation patterns and intrinsic mechanisms by which volume-loss notches at different positions affect the compressor’s overall performance. The results indicate that leading-edge notch damage induces substantial degradation of the compressor’s aerodynamic performance and notable narrowing of the stable operating flow range. Among these, notches at the leading-edge tip and mid-span lead to a sharp drop in the compressor’s total pressure ratio and isentropic efficiency, with the stability margin experiencing the most severe attenuation (maximum degradation rate of ۶۰.۹۸%). In contrast, trailing-edge notches exert a negligible influence on the compressor’s aerodynamic performance, resulting only in minor fluctuations at extremely low flow rates rather than significant deterioration. Further flow field analysis reveals that rotor blade notch damage markedly modifies the vortex structures within the flow channel, such as strengthening tip leakage vortices and inducing backflow vortices. This intensifies flow blockage and energy dissipation, ultimately leading to reduced aerodynamic performance of the compressor and even stall initiation. This study offers a theoretical foundation for the safety assessment and maintenance decision-making of damaged blades in aero-engine compressors.

کلیدواژه ها:

Transonic compressor ، Aerodynamic performance ، Blade notch damage ، Leakage vortex ، Flow loss ، Shock wave