涡轮叶栅尾缘冷气喷射对主流场干扰的物理模型的研究

2-D MODEL FOR INFLUENCE OF TRAILING EDGE EJECTION ON AERODYNAMIC PERFORMANCE OF A TURBINE CASCADE

本文分析了叶片尾缘喷气与主流干扰的机理，改进了二维、可压缩的涡轮叶栅尾缘喷气模型，并以能量损失系数ξＦ 来反映冷气喷射对主流的气动影响。通过尾缘喷气模型与涡轮叶栅流场计算及附面层参数的关联，分析了冷气喷射后的气动损失。与实验结果的对比分析表明，该模型能较准确地反映叶栅尾缘冷气喷射与主流的掺混情况。

In accordance to analysis of interaction mechanism between the ejection and the main flow,a 2-D compressible model of the turbine blade trailing edge ejection has been improved,which uses energy loss coefficient for representing the effect of the ejection on the aerodynamics of the main flow.The aerodynamical loss after the ejection has been analyzed through correlation of the model with the numerical calculation of the cascade main flow field and boundary layer parameters.The comparison between calculation results and experimental data shows that the improved model can exactly describe the mixing process between the main flow and the ejection,and predict the energy loss coefficient for the ejection on the pressure side near the trailing edge and through the trailing edge holes.