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通过对带有前缘气膜冷却的C3X涡轮叶片的传热和气动试验结果进行计算验证,表明所使用计算方法在对带有冷却射流的跨音涡轮压力及温度进行的预测具有较高的精度,在此基础上针对某型发动机低压涡轮,通过CFD数值模拟研究其叶顶冷却射流对叶顶泄漏流及涡轮性能的影响规律,并通过详细分析叶顶流动揭示该规律产生的原因;然后通过改变不同叶顶间隙大小,研究了间隙流和泄漏涡流动规律及叶顶间隙对叶顶冷却射流和透平性能影响,并通过其复杂流场分析揭示了其内在机理。
The results of heat transfer and aerodynamic tests on the C3X turbine blades with leading edge film cooling show that the proposed method has higher accuracy in predicting the turbo pressure and temperature with cooling jets On the basis of this, aiming at a certain type of engine low-pressure turbine, the influence law of its tip cooling jet on tip leakage flow and turbine performance is studied by CFD numerical simulation, and the cause of the law is revealed through detailed analysis of the flow at the tip of the blade. The different tip clearances were changed. The flow laws of the clearance flow and the leakage eddy and the influence of the tip clearance on the cooling jet and turbine performance were studied. The internal mechanism was also revealed through the complicated flow field analysis.