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首页> 外文期刊>International Journal of Heat and Mass Transfer >Effects of endwall motion on thermal performance of cavity tips with different squealer width and height
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Effects of endwall motion on thermal performance of cavity tips with different squealer width and height

机译：端壁运动对不同压条宽度和高度的型腔尖端热性能的影响

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摘要

This paper investigates the thermal performance of cavity tips in a transonic high pressure turbine cascade. Numerical methods were first validated and then used to study more cases. The flow physics within the tip gap and the distribution of Nusselt number on the blade tip were presented. The effects of relative motion between the blade tip and the endwall were studied. For both cases with a stationary endwall or a moving endwall, a cavity vortex appears within the tip cavity. It is found that a cavity scraping vortex forms within the tip cavity as the endwall moves relatively to the blade tip, which was not observed before. The effects of the cavity scraping vortex on the distribution of Nusselt number are explained. Then, the effects of the squealer width and height on the thermal performance of the cavity tip were investigated. The flow physics within the tip cavity varies as the squealer geometry changes. As a result, the thermal performance of the cavity tips is different. The results show that increasing the height of the squealer reduces the average Nusselt number on the blade tip. The average Nusselt number and the heat flux on different parts of the blade tip, and the thermal performance of the blade surface near tip region and the loss of different blade tips are also discussed in this paper.
机译：本文研究了跨音速高压涡轮叶栅中腔尖的热性能。首先验证了数值方法，然后将其用于研究更多案例。给出了叶尖间隙内的流动物理学和叶尖上的努塞尔数分布。研究了叶尖和端壁之间相对运动的影响。对于具有固定端壁或移动端壁的两种情况，在尖端腔内都会出现腔涡。已经发现，当端壁相对于叶片尖端移动时，在尖端腔内形成了空腔刮擦涡流，这是以前没有观察到的。解释了腔刮涡对努塞尔数分布的影响。然后，研究了凹槽宽度和高度对腔尖热性能的影响。尖头腔内的流动物理特性会随着刮刀几何形状的变化而变化。结果，腔尖端的热性能是不同的。结果表明，增加刮刀的高度会降低叶片尖端的平均Nusselt数。本文还讨论了叶尖不同部位的平均Nusselt数和热通量，叶尖附近区域的叶片表面的热性能以及不同叶尖的损耗。

著录项

  • 来源
    《International Journal of Heat and Mass Transfer》 |2015年第12期|1248-1258|共11页
  • 作者

    Chao Zhou;

  • 作者单位

    College of Engineering, Peking University, Beijing, China Collaborative Innovation Center of Advanced Aero-Engine, 100191 Beijing, People's Republic of China;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

    Turbine; Blade tip; Numerical methods;

    机译：涡轮;刀尖;数值方法;

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