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首页> 外文期刊>Journal of turbomachinery >The Effect Of Combustor-turbine Interface Gap Leakage On The Endwall Heat Transfer For A Nozzle Guide Vane
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The Effect Of Combustor-turbine Interface Gap Leakage On The Endwall Heat Transfer For A Nozzle Guide Vane

机译：燃烧室-涡轮界面间隙泄漏对喷嘴导流叶片端壁传热的影响

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摘要

To enable turbine components to withstand high combustion temperatures, they are cooled by air routed from the compressor, which can leak through gaps between components. These gaps vary in size from thermal expansions that take place. The leakage flow between the interface of the combustor and the turbine, in particular, interacts with the flowfield along the endwall. This study presents measurements of adiabatic cooling effectiveness and heat transfer coefficients on the endwall of a first vane, with the presence of leakage flow through a flush slot upstream of the vane. The effect of axial contraction of the slot width due to thermal expansion of the engine was tested for two blowing rates. Contracting the slot width, while maintaining the slot mass flow, resulted in a larger coolant coverage area and higher effectiveness values, as well as slightly lower heat transfer coefficients. Matching the momentum flux ratio of the leakage flow from the nominal and contracted slot widths lowered both cooling effectiveness and heat transfer coefficients for the contracted slot flow. Comparison of the coolant coverage pattern to the measured endwall shear stress topology indicated that the trajectory of the slot coolant was dictated by the complex endwall flow.
机译：为了使涡轮机部件能够承受较高的燃烧温度，涡轮机部件会通过从压缩机输送的空气进行冷却，这些空气会通过部件之间的间隙泄漏。这些间隙的大小因发生的热膨胀而异。燃烧器的接口与涡轮之间的泄漏流，尤其是沿着端壁与流场相互作用。这项研究提出了在第一叶片的端壁上绝热冷却效率和传热系数的测量，并存在通过叶片上游冲洗槽的泄漏流。对于两个吹气速率，测试了由于发动机的热膨胀而引起的槽缝宽度轴向收缩的影响。在保持狭缝质量流量的同时缩小狭缝宽度会导致更大的冷却液覆盖面积和更高的有效值，以及稍低的热传递系数。从标称缝隙宽度和收缩缝隙宽度匹配泄漏流的动量通量比，会降低收缩缝隙流动的冷却效率和传热系数。冷却剂覆盖模式与测得的端壁剪切应力拓扑的比较表明，槽形冷却剂的轨迹是由复杂的端壁流决定的。

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