亚声速涡轮导叶全气膜冷却特性实验研究

推进技术 ›› 2019, Vol. 40 ›› Issue (1): 158-165.

亚声速涡轮导叶全气膜冷却特性实验研究

付仲议¹,朱惠人¹,姚春意¹,张洪²,高强¹

西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072,西北工业大学动力与能源学院，陕西西安 710072,中航商用航空发动机有限责任公司，上海 201108,西北工业大学动力与能源学院，陕西西安 710072

发布日期:2021-08-15
作者简介:付仲议，博士生，研究领域为航空发动机高温部件冷却。 E-mail: 252922326@qq.com 通讯作者:朱惠人，博士，教授，研究领域为航空发动机高温部件冷却及空气系统。 E-mail: zhuhr@nwpu.edu.cn 。
基金资助:
国家重点基础研究发展规划资助( 2013CB035702)

Experimental Investigation of Full Film Cooling Characteristics of Subsonic Turbine Guide Vane

School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China,School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China,AVIC Commercial Aircraft Engine Limited Company，Shanghai 201108，China and School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China

Published:2021-08-15

摘要/Abstract

摘要： 为了获得亚声速涡轮导叶的全气膜冷却特性，在短周期高速风洞中对全气膜覆盖涡轮导叶实验件进行了实验，获得了涡轮叶片表面在不同主流雷诺数( Re=3.0×105～9.0×105)、二次流质量流量比( MFR=5.5%～12.5%)和主流湍流度( Tu=1.3%，14.7%)下的气膜冷却效率分布。实验叶片前缘有 5排复合角度圆柱形气膜孔形成前缘喷淋冷却结构，压力面和吸力面分别有 6排和 3排圆柱形气膜孔。结果表明:在本文研究的质量流量比范围内，涡轮叶片压力面和吸力面的气膜冷却效率随着质量流量比的增大而减小，而前缘区域的冷却效率随质量流量比的增大而增大；雷诺数的变化主要影响叶片压力面相对弧长 S/Smax＜-0.6区域的冷却效率分布，在高雷诺数( Re=9.0×105)下，大质量流量比的冷却效率最高，而在中低雷诺数( Re=3.0×105，6.4×105)下，小质量流量比的冷却效率最高；叶片前缘气膜冷却效率受主流湍流度升高的影响较小，而在压力面和吸力面冷却效率均随着湍流度的升高而降低。

关键词: 涡轮导叶；气膜冷却；质量流量比；雷诺数；主流湍流度

Abstract: In order to study the full film cooling characteristics of subsonic turbine guide vane，the film cooling effectiveness of full coverage film cooling turbine vane at different mainstream inlet Reynolds number(Re=3.0×105～9.0×105)，second flow mass flow rate ratio(MFR=5.5%～12.5%)and mainstream turbulencein. tensity(Tu=1.3%，14.7%)conditions is measured in short-duration high speed wind tunnel. There are 5 com.pound angle cylindrical hole rows on the leading edge to obtain a showerhead film cooling，6 cylindrical holesrows on the pressure side and 3 rows on the suction side. The results show that in the range of mass flow rate ratiostudied in the present paper，the film cooling effectiveness on pressure and suction side decreases with mass flow rate ratio increasing，while the effect of mass flow rate ratio on the film cooling effectiveness on the leading edgeis opposite. The change of mainstream inlet Reynolds number mainly affects the film cooling effectiveness in theregion of relative arc S/Smax＜-0.6，at high Reynolds number(Re=9.0×105)the highest film cooling effectiveness is obtained at high mass flow rate ratio，while at middle and low Reynolds number(Re=3.0×105，6.4×105)the highest film cooling effectiveness is obtained at low mass flow rate ratio. The film cooling effectiveness on the lead. ing is not affected obviously by the change of turbulence intensity，while the film cooling effectiveness on pres.sure and suction side decreases with the mainstream turbulence intensity increasing.

Key words: Turbine vane； Film cooling； Mass flow rate ratio； Reynolds number； Mainstream turbu. lence intensity

付仲议,朱惠人,姚春意,张洪,高强. 亚声速涡轮导叶全气膜冷却特性实验研究[J]. 推进技术, 2019, 40(1): 158-165.

FU Zhong-yi¹,ZHU Hui-ren¹,YAO Chun-yi¹,ZHANG Hong²,GAO Qiang¹. Experimental Investigation of Full Film Cooling Characteristics of Subsonic Turbine Guide Vane[J]. Journal of Propulsion Technology, 2019, 40(1): 158-165.

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