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本文以1+1/2对转涡轮为背景,采用理论分析与数值模拟相结合的方法对某1+1/2对转涡轮高压动叶进行了优化设计。研究结果表明,流道缩扩比对高出口马赫数涡轮叶栅性能有重要影响,合理的流道缩扩比能减弱甚至消除尾缘内伸波,从而提升叶栅的性能。文中综合考虑了叶栅流道周向以及径向两个方向的扩张因素后选择了叶栅流道缩扩比,进行1+1/2对转涡轮高压动叶叶型优化设计,数值计算表明所设计的涡轮高压动叶性能有一定的提升。
In this paper, 1 + 1/2 counter-rotating turbo is taken as the background, a 1 + 1/2 counter-rotating turbo high-pressure moving blade is optimized by the combination of theoretical analysis and numerical simulation. The results show that the expansion and contraction ratio of the runner has an important influence on the performance of the turbine cascade with high Mach number. A reasonable expansion and contraction ratio of the runner can reduce or even eliminate the inward wave of the trailing edge, thus improving the performance of the cascade. In this paper, the expansion ratio of cascade flow passage is selected considering the expansion factors in both the circumferential direction and the radial direction of the cascade runner. The optimal design of the 1 + 1/2 counter-rotating turbo-high pressure rotor blade is carried out. The numerical calculation shows Turbine high-pressure turbine blades designed to improve performance.