一种压气机叶型的可控环量尾缘造型方法

为了提高压气机叶型负荷，提出了一种可控环量尾缘造型方法，该方法对叶型尾缘处弦长2%的区域进行特殊造型，通过改变流动后驻点位置从而提高叶型环量，增加叶型气流转角。在不同马赫数及雷诺数下进行数值模拟得到了一致的结论。数值模拟结果显示:以设计进气角D因子为0.52的叶型为基准叶型，采用可控环量尾缘造型后叶型气流转角可提高21%，同时总压损失基本无变化，部分叶型甚至在气流转角提高的同时总压损失有所降低。而当气流折转角相同时，可控环量尾缘可以比传统尾缘的总压损失更小。 

A method for controlled circulation trailing edge design ofcompressor blade

A controlled circulation trailing edge design method for compressor blade was proposed to increase the circulation and the turning angle of cascades through the specific geometrical modelling at the region of 2% chord length of trailing edge. The conclusion was verified under different Mach numbers and Reynolds numbers. The numerical results showed that, for the cascade with the diffusion factor up to 0.52 at design condition, the controlled circulation trailing edge can improve the flow turning angle by about 21% while the total pressure loss was nearly kept unchanged. Some controlled circulation trailing edge designs can even have positive effect on the decrease of loss. At the same flow turning angle, the cascade with the controlled circulation trailing edge can have lower total pressure loss than that with traditional rounded trailing edge.