论文部分内容阅读
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，适用于预测不同形式的叶栅尾缘喷气对叶栅气动性能的影响
In this paper, the mechanism of blade tip jet interference with mainstream is analyzed, and a two-dimensional and compressible turbine blade trailing edge jet model is improved. The aerodynamic effect of cooling jet on the mainstream is reflected by the energy loss coefficient ξF. The aerodynamic losses after the cold air injection are analyzed by the correlation between the trailing edge jet model and the flow field in the turbine cascade and the parameters of the cladding. Compared with the experimental results, it is shown that this model can accurately reflect the mixing of cold air injection and main flow in the trailing edge of the cascade and is suitable for predicting the aerodynamic performance of cascades with different forms of nozzle trailing edge jet