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FILM COOLING ON HIGHLY LOADED BLADES WITH MAIN FLOW SEPARATION - PART 1: HEAT TRANSFER

机译:高流量刀片上的薄膜冷却和主要流动分离-第1部分:传热

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Film cooling experiments were run at the high speed cascade wind tunnel of the University of the Federal Armed Forces Munich. The investigations were carried out with a linear cascade of highly loaded turbine blades. The main targets of the tests were to assess the film cooling effectiveness and the heat transfer in zones with main flow separation. Therefore the blades were designed to force the flow to detach on the pressure side shortly downstream of the leading edge and it reattaches at about half of the axial chord. In this zone film cooling rows are placed among others for reduction of the size of the separation bubble. The analyzed region on the blade is critical due to the high heat transfer present at the leading edge and at the reattachment line after main flow separation. Film cooling can contribute to a reduction of the size of the separation bubble reducing aerodynamic losses but increases in general heat transfer due to turbulent mixing. The reduction of the size of the separation bubble might also be twofold since it acts like a thermal insulator on the blade and reducing the size of the bubble might lead to stronger heating of the blade. Film cooling should therefore take into account both: firstly a proper protection of the surface and secondly reduce aerodynamic losses diminishing the extension of the main flow separation. While experimental results of the adiabatic film cooling effectiveness were shown in previous publications, the local heat transfer is analyzed in this paper. Emphasis is also put in analyzing in detail the flow separation process. The tests comprise furthermore the analysis of the effect of different outlet Mach and Reynolds numbers and film cooling. In part two of this paper the overall film cooling effectiveness is addressed. Local heat transfer is still difficult to predict with modern numerical tools and this is especially true for complex flows with flow separation. Some numerical results with RANS and LES show the capability of a commercial solver in predicting the heat transfer.
机译:薄膜冷却实验是在慕尼黑联邦武装大学的高速级联风洞中进行的。使用高负载涡轮叶片的线性级联进行了研究。测试的主要目标是评估薄膜冷却效果和具有主流分离区域的热传递。因此,叶片设计成迫使流动在前缘下游不久的压力侧分离,并在轴向弦的大约一半处重新附着。在该区域中,为了减少分离气泡的尺寸,放置了多个冷却行。叶片上的分析区域非常关键,这是因为主流分离之后,在前缘和重新连接线上存在较高的热传递。薄膜冷却可有助于减小分离气泡的尺寸,从而减少空气动力学损失,但由于湍流混合而增加了总体传热。分离气泡的尺寸减小也可能是双重的,因为它像叶片上的热绝缘体一样起作用,减小气泡的尺寸可能导致叶片更强的加热。因此,薄膜冷却应兼顾以下两个方面:首先对表面进行适当的保护,其次减少空气动力损失,从而减少主流分离的范围。虽然绝热膜冷却效果的实验结果已在以前的出版物中显示,但本文还是对局部传热进行了分析。还着重详细分析了流分离过程。该测试还包括对不同出口马赫数和雷诺数以及薄膜冷却的影响的分析。在本文的第二部分中,介绍了总体薄膜冷却效果。现代数值工具仍然难以预测局部传热,尤其是对于带有流动分离的复杂流动而言。 RANS和LES的一些数值结果显示了商用求解器预测传热的能力。

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