高负荷亚音三级压气机设计转速试验与数值研究

The subsonic stage is an essential component of gas turbine high-load axial compressors and a dominant factor influencing the performance of multi-stage axial compressors. To meet the development demands of advanced gas turbine compressors, this study conducts experimental and numerical research on a typical high-load subsonic compressor. The compressor design and experimental testing were based on the characteristics of the intermediate stage in industrial gas turbine axial compressors. Subsequently, numerical simulations were conducted to analyze the aerodynamic performance and flow behavior of the compressor, with a particular focus on the leakage flow at the blade tip. The experimental results obtained the compressor’s characteristic curves at different rotational speeds and validated the numerical methods used. Analyses of the flow field at typical operating points revealed that the occurrence of blockage in the compressor is primarily caused by the interaction of shock waves and downstream flow separation in the third-stage moving and stationary blades. Additionally, the blade tip leakage flow in the first-stage moving blades was identified as the main reason for the performance degradation and flow instability during the compressor’s approaching stall process.