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Aerothermal Performance of Different Tips in Transonic Turbine Cascade with End-Wall Motion

机译:具有跨壁运动的跨音速涡轮叶栅叶尖的空气热性能

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摘要

Modern high-pressure axial turbines of aircraft engines are often transonic. This paper investigates and compares the aerothermal performance of the tip leakage flow of two widely used tips, a flat tip and a cavity tip, in a transonic turbine cascade. Numerical methods were first validated and then used to study different cases. Shock waves appear within the tip gap of a flat tip and have a large effect on the aerothermal performance. Unlike the flat tip, the flow physics within the tip gap of the cavity tip is significantly affected by the cavity vortices, and the effects of the shock waves are small. The impact of tip leakage flow physics on the loss mechanism and heat transfer are investigated. The effects of the relative motion between the blade tip and the casing are also investigated. A tangential viscous force is imposed by end-wall motion and changes the flow physics within the tip gap. Furthermore, a scrapping vortex is formed in the main flow passage due to relative end-wall motion. The scrapping vortex has a large effect on the flow pattern downstream of the cascade.
机译:飞机发动机的现代高压轴向涡轮通常是跨音速的。本文研究并比较了跨音速涡轮叶栅中两个广泛使用的尖端(扁平尖端和空腔尖端)的尖端泄漏流的空气热性能。首先验证了数值方法,然后将其用于研究不同的情况。冲击波出现在扁平尖端的尖端间隙内,对空气热性能有很大影响。与平坦尖端不同,空腔尖端的尖端间隙内的流动物理学会受到空腔涡旋的显着影响,并且冲击波的影响很小。研究了尖端泄漏流物理性质对损失机理和传热的影响。还研究了叶尖与壳体之间相对运动的影响。切向粘性力是由端壁运动施加的,它改变了尖端间隙内的流动物理特性。此外,由于相对的端壁运动,在主流道中形成刮擦涡流。刮除涡流对叶栅下游的流型有很大影响。

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  • 来源
    《Journal of propulsion and power》 |2014年第5期|1316-1327|共12页
  • 作者

    Chao Zhou;

  • 作者单位

    Peking University, 100871 Beijing, People's Republic of China;

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  • 正文语种 eng
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