跨声速压气机多圆柱孔式处理机匣设计与扩稳机理研究

Design and Investigation of Multiple Cylinder Holes Casing Treatment for Transonic Axial Compressor

关键词:  跨声速轴流压气机  机匣处理  扩稳  数值模拟

Key words:  Transonic axial compressor  Casing treatment  Stall margin enhancement  Numerical simulation

摘要:

基于对跨声速轴流压气机内部失稳触发机制的认识，设计了一种新型多圆柱孔式处理机匣结构。对带该处理机匣的跨声速轴流压气机转子Rotor-37的内部流动进行了全三维非定常数值模拟，结果表明该新型多圆柱孔式处理机匣结构可使压气机的综合裕度提高6.5%，而最高效率点效率仅降低0.19%。对多圆柱孔式处理机匣的扩稳机理进行了详细分析，结果表明处理机匣能有效消除低速流体团引起的通道阻塞现象，并将低速阻塞流体团抽吸进入处理机匣容腔，然后从前端喷口预旋喷出以抑制叶顶区域的流动分离，从而有效提高跨声速轴流压气机的失速裕度。

Abstract:

A new form of multiple cylinder holes casing treatment with preswirl blowing for the NASA Rotor-37 was designed based on profound understanding of the mechanism behind the stall inception. Unsteady numerical simulations were carried out for Rotor-37 with multiple cylinder holes casing treatment. Results show that the casing treatment could extend the operating range by 6.5% with only 0.19% peak efficiency reduction. Detailed analysis of the mechanism behind the stall margin improvement was conducted，and the results show that the casing treatment could suppress the breakup of Tip Leakage Vortex and extracts the low-speed fluid cells to the chamber of the casing，then the fluid cells are injected to main flow passage with preswirl through injection nozzles to suppress tip flow separation，which all contribute to stall margin enhancement.