压气机叶片边缘磨损对其性能的影响研究

Research on Influence of Edge Wear on Transonic Compressor Blade Performance

航空发动机在实际运行中,压气机叶片会遭受风沙等侵蚀、磨损,从而导致其型面发生改变。为了研究压气机边缘磨损对其性能的影响,构建不同磨损程度的压气机模型进行数值模拟,结果表明,前缘磨损和后缘磨损对压气机性能的影响不一,前缘磨损导致压比、效率降低,堵塞点流量减小,对失速边界没有影响;后缘磨损只在小流量范围对性能影响较大,并且失速边界点流量增大,工作裕度减小,而对堵塞点流量没有影响。压气机性能对前缘更为敏感,前缘磨损导致叶尖区域激波后移,叶中区域分离涡损失增大,从而效率下降。同时,前缘磨损后,压力面的静压减小,导致压气机增压能力降低。

When the aero-engine is in actual running, the compressor blade will be eroded and worn by sand wind, which can lead to the change of its profile. In order to study the influence of compressor edge wear on its performance, the compressor models with different degrees of wear are built for numerical simulation. The results show that leading edge wear and trailing edge wear have different influences on compressor performance. Leading edge wear results in reduced pressure ratio and efficiency, increased choking mass flow rate, and no effect on the stall boundary. The trailing edge wear only has a great influence on the performance in the range of small flow, and the mass flow at the stall boundary point increases and the working margin decreases, but it has no influence on the choking mass flow rate. The compressor performance is more sensitive to the leading edge, leading edge wear causes shock wave backward movement in the tip area, separation vortex loss in the middle area of the blade increases, and the efficiency decreases. At the same time, after the leading edge has been worn, the static pressure on the pressure surface decreases, leading to a decrease in the compressor pressure ratio.