主流湍流度对涡轮导叶吸力面W型气膜孔冷却效率影响的实验研究

doi:10.13675/j.cnki. tjjs. 017

推进技术 ›› 2019, Vol. 40 ›› Issue (12): 2783-2791.DOI: 10.13675/j.cnki. tjjs. 017

主流湍流度对涡轮导叶吸力面W型气膜孔冷却效率影响的实验研究

姚春意¹,朱惠人^1,2,付仲议¹,刘存良^1,2,张博伦¹

1.西北工业大学动力与能源学院;2.西北工业大学;陕西省航空动力系统热科学重点实验室，陕西西安;710129

发布日期:2021-08-15
作者简介:姚春意，博士生，研究领域为航空发动机高温部件冷却。E-mail：npuycy@foxmail.com
基金资助:
国家自然科学基金 51776173;装备预研中国航发联合基金 6141B090213国家自然科学基金（51776173）；装备预研中国航发联合基金（6141B090213）。

Experimental Investigation for Effects of Mainstream Turbulence on Film Cooling Effectiveness of W-Shaped Film Hole on Suction Side of a Turbine Guide Vane

1.School of Power and Energy,Northwestern Polytechnical University,Xi’an 710129，China;2.Shaanxi Key Laboratory of Thermal Sciences in Aero-Engine System,Northwestern Polytechnical University，Xi’an 710129,China

Published:2021-08-15

摘要/Abstract

摘要： 为了获得亚声速涡轮导叶吸力面不同位置处单排W型气膜孔的气膜冷却特性，在短周期跨声速风洞中实验研究了吹风比、主流湍流度对W型气膜孔冷却效率的影响。两列单排气膜孔分别布置在吸力面16%和21%相对弧长处，实验进口雷诺数范围为3.0×10⁵~9.0×10⁵，吹风比范围是0.5~2.0，叶栅出口等熵马赫数为0.8，高低湍流度分别为14.7% 和1.3%。实验结果表明：低湍流度时孔排1和孔排2下游的气膜冷却效率都随吹风比的增大先增大后减小，最佳吹风比分别为BR=1.2和BR=0.8。由于孔排1和孔排2所处位置的主流边界层状态不同，导致湍流度对于气膜冷却效率有不同的影响。对于孔排1，大吹风比时高湍流度使冷气核心向壁面移动，提高了气膜冷却效率；而小吹风比时，湍流度对冷却效率的影响随雷诺数升高而减弱。对于孔排2，大吹风比时高湍流度提高了孔附近区域的冷却效率，同时加快了冷却效率沿流向下降的速度，而在小吹风比时高湍流度显著降低了孔排下游气膜冷却效率。

关键词: W型气膜孔;气膜冷却;吸力面;湍流度;吹风比

Abstract: In order to achieve the film cooling characteristic of W-shaped film holes at different positions on the suction side of a subsonic turbine vane, an experiment was conducted in the short-duration transonic wind tunnel to investigate the effect of blowing ratio and mainstream turbulence intensity on the film cooling effectiveness. Two single row of film cooling holes （SS1 and SS2）， are respectively located at 16% and 21% relative arc length on the suction side. The range of inlet Reynolds numbers was 3.0×10⁵~9.0×10⁵ and the range of blowing ratios was 0.5~2.0. The isentropic exit Mach number of the cascade was 0.8. The high and low turbulence intensity was 14.7% and 1.3%, respectively. The experimental results show that: at low turbulence intensity, the film cooling effectiveness downstream of SS1 and SS2 increases first and then decreases with the increase of blowing ratio, and the optimal blowing ratio is BR=1.2 and BR=0.8, respectively. The turbulence intensity has different effects on the film cooling effectiveness of SS1 and SS2, because the states of mainstream boundary layer is different. For SS1, high turbulence intensity makes the core of coolant to move towards the wall surface and improves the film cooling effectiveness at large blowing ratio, however, reduces the cooling effectiveness at small blowing ratio. The influence is weaker as the Reynolds number increases. For SS2, high turbulence intensity increases the cooling effectiveness in the vicinity of the film holes and increases the rate of decay along the flow direction at large blowing ratio, however, significantly reduces the film cooling effectiveness downstream of film cooling holes at small blowing ratio.

Key words: W-shaped hole;Film cooling;Suction side;Turbulence intensity;Blowing ratio

姚春意,朱惠人,付仲议,刘存良,张博伦. 主流湍流度对涡轮导叶吸力面W型气膜孔冷却效率影响的实验研究[J]. 推进技术, 2019, 40(12): 2783-2791.

YAO Chun-yi¹,ZHU Hui-ren^1,2,FU Zhong-yi¹,LIU Cun-liang^1,2,ZHANG Bo-lun¹. Experimental Investigation for Effects of Mainstream Turbulence on Film Cooling Effectiveness of W-Shaped Film Hole on Suction Side of a Turbine Guide Vane[J]. Journal of Propulsion Technology, 2019, 40(12): 2783-2791.

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主流湍流度对涡轮导叶吸力面W型气膜孔冷却效率影响的实验研究

Experimental Investigation for Effects of Mainstream Turbulence on Film Cooling Effectiveness of W-Shaped Film Hole on Suction Side of a Turbine Guide Vane

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