高温风洞中空冷涡轮叶片冷却特性的实验研究

推进技术 ›› 2016, Vol. 37 ›› Issue (3): 496-503.

高温风洞中空冷涡轮叶片冷却特性的实验研究

马超,黄名海,葛冰,吉雍斌,臧述升

上海交通大学动力机械及工程教育部重点实验室，上海 200240,上海交通大学动力机械及工程教育部重点实验室，上海 200240,上海交通大学动力机械及工程教育部重点实验室，上海 200240,上海交通大学动力机械及工程教育部重点实验室，上海 200240,上海交通大学动力机械及工程教育部重点实验室，上海 200240

发布日期:2021-08-15
作者简介:马超，男，博士生，研究领域为燃气轮机热端部件传热及流动。E-mail: iammach@163.com 通讯作者:臧述升，男，博士，研究员，研究领域为燃气轮机燃烧及热端部件冷却。
基金资助:
国家自然科学基金(51206109)。

Experimental Investigation of Cooling Performance of Air-Cooled Turbine Blade in a High-Temperature Wind Tunnel

Key Laboratory of Mechanical and Power Engineering of Ministry of Education， Shanghai Jiaotong University，Shanghai 200240，China,Key Laboratory of Mechanical and Power Engineering of Ministry of Education， Shanghai Jiaotong University，Shanghai 200240，China,Key Laboratory of Mechanical and Power Engineering of Ministry of Education， Shanghai Jiaotong University，Shanghai 200240，China,Key Laboratory of Mechanical and Power Engineering of Ministry of Education， Shanghai Jiaotong University，Shanghai 200240，China and Key Laboratory of Mechanical and Power Engineering of Ministry of Education， Shanghai Jiaotong University，Shanghai 200240，China

Published:2021-08-15

摘要/Abstract

摘要： 为了研究涡轮叶片在高温燃气冲刷下的冷却特性，搭建了高温风洞环形叶栅实验台。采用红外热像仪对不同冷气流量比(0.016 ~ 0.036)及温比(0.47 ~ 0.58)工况下涡轮叶片吸力面冷却效率及温比特性进行了研究。结果表明:受叶片前后部冷却腔冷却特性的影响，吸力面前部和后部区域表现出了不同的冷却特性；在实验工况内，流量比从0.016增加到0.036过程中，叶片吸力面前、后部面积平均冷却效率分别增加了 30.4%和49.1%，相对温度分别降低0.017和0.049；当流量比不变，温比从0.47增加到0.58时，叶片吸力面前、后部面积平均冷却效率变化较小，分别减少了 2.9%和9.6%，相对温度分别增加0.013和0.015。

关键词: 燃气轮机；涡轮叶片；冷却效率；相对温度

Abstract: In order to investigate the cooling performance of a turbine blade scoured by high-temperature gas flow，an annular cascade test rig was set up. The distribution of temperature on suction side of blade was measured by an infrared camera. Effects of mass flow ratio (0.016 ~ 0.036) and temperature ratio (0.47 ~ 0.58) on cooling performance of blade were studied. Results showed that due to the influence of different cooling performance owned by the front and rear cooling chambers，the front and rear parts of the suction side of blade show different cooling performance. In the experiment，the area-averaged cooling efficiencies of the front and rear parts of suction side of blade increase by 30.4% and 49.1% with mass flow ratio increasing from 0.016 to 0.036，respectively. In the same process，the relative temeprature of the two parts decreases by 0.017 and 0.049，respectively. In case of the temperature ratio increasing from 0.47 to 0.58 with the mass flow ratio unchanged，the cooling efficiencies of the front and rear parts of suction side of blade both have minor changes，they decrease by 2.9% and 9.6%，respectively. However，the relative temperature of the two parts increases by 0.013 and 0.015，respectively， in the same process.

Key words: Gas turbine；Turbine blade；Cooling efficiency；Relative temperature

马超,黄名海,葛冰,吉雍斌,臧述升. 高温风洞中空冷涡轮叶片冷却特性的实验研究[J]. 推进技术, 2016, 37(3): 496-503.

MA Chao,HUANG Ming-hai,GE Bing,JI Yong-bin,ZANG Shu-sheng. Experimental Investigation of Cooling Performance of Air-Cooled Turbine Blade in a High-Temperature Wind Tunnel[J]. Journal of Propulsion Technology, 2016, 37(3): 496-503.

参考文献

[1] Drost U,Bolcs A. Incestigation of Detailed Film Cooling Effectiveness and Heat Transfer Distributions on a Gas Turbine Airfoil [J]. ASME Journal of Turbomachinery, 1999, 121(1): 233-242.
[2] 朱惠人, 向安定, 许都纯, 等. 涡轮叶片表面气膜冷却效率的实验研究[J]. 推进技术, 2003, 24(6): 528-531. (ZHU Hui-ren, XIANG An-ding, XU Du-chun, et al. An Experimental Investigation of Film Cooling Effectiveness on the Surface of Turbine Blade[J]. Journal of Propulsion Technology, 2003, 24(6): 528-531.)
[3] 向安定, 刘松龄, 朱惠人, 等. 涡轮工作叶片表面气膜冷却效率的实验研究[J]. 推进技术, 2004, 25(1):39-43. (XIANG An-ding, LIU Song-ling, ZHU Hui-ren, et al. Film Cooling Effectiveness Measurements for Gas Holes on Blade Surface in a Turbine Cascade[J]. Journal of Propulsion Technology, 2004, 25(1): 39-43.)
[4] 白江涛, 朱惠人, 张宗卫, 等. 叶片全表面换热系数和冷却效率的实验测量[J]. 西安交通大学学报, 2010, 44(11):92-97.
[5] Luzeng Zhang, Juan Yin, Hee Koo Moon. The Effect of Compound Angle on Nozzle Pressure Side Film Cooling[R]. ASME GT2009-59141.
[6] 史晓军, 王维, 高建民, 等. 透平叶片双工质冷却特性的实验研究[J]. 西安交通大学学报, 2013, 47(10): 81-86.
[7] Ekkad S V. A Transient Infrared Thermography Method for Simultaneous Film Cooling Effectiveness and Heat Transfer Coefficient Measurements from a Single Test[J]. Journal of Turbomachinery, 2004, 126(4): 597-603.
[8] Lu Y, Nasir H, Faucheaux D, et al. Film Cooling Measurements for Novel Hole Configurations[J]. Journal of Heat Transfer, 2006, 128(8).
[9] 黄名海, 臧述升, 葛冰, 等. 热风洞中涡轮叶片红外温度场红外热像测量方法[J]. 航空动力学报, 2014, 29(11): 2679-2683.
[10] 谭晓茗, 朱兴丹, 郭文, 等. 涡轮叶片前缘气膜冷却换热实验[J]. 航空动力学报, 2014, 29(11): 2672-2678.
[11] Jason E Dees, David G Bogard, Gustavo A Ledezma, et al. Overall and Adiabatic Effectiveness Values on a Scaled up, Simulated Gas Turbine Vane[J]. ASME Journal of Turbomachinery, 2013, 135(5): 051017-051017-10.
[12] Jason E Dees, David G Bogard, Gustavo A Ledezma, et al. Experimental Measurements and Computational Predictions for an Internally Cooled Simulated Turbine Vane[J]. ASME Journal of Turbomachinery, 2012, 134(6): 061005-061005-9.
[13] Jason E Dees, David G Bogard, Gustavo A Ledezma, et al. Momentum and Thermal Boundary Layer Development on an Internally Cooled Turbine Vane[J]. ASME Journal of Turbomachinery, 2012, 134(6): 061004-061004-11.
[14] Jason E Dees, David G Bogard, Ronald S Bunker. Heat Transfer Augmentation Downstream of Rows of Various Dimple Geometries on the Suction Side of a Gas Turbine Airfoil [J]. ASME Journal of Turbomachinery, 2010, 132(3): 031010-031010-7.
[15] Yu Rao, Shusheng Zang. Flow and Heat Transfer Characteristics in Latticework Cooling Channels with Dimple Vortex Generators [J]. ASME Journal of Turbomachinery, 2013, 136(2): 021017-021017-10.
[16] 杨世铭, 陶文铨. 传热学 (第三版) [M]. 北京:高等教育出版社, 1998: 250-252.
[17] Kline J L, Mcclintock F A. Describing Uncertainties in Single-Sample Experiments[J]. Mechanical Engineering, 1953, 75: 3-8.(编辑:朱立影)　　　　　　　　　　　　　*　收稿日期:2014-11-14；修订日期:2014-12-26。基金项目:国家自然科学基金(51206109)。作者简介:马超,男,博士生,研究领域为燃气轮机热端部件传热及流动。E-mail: iammach@163.com通讯作者:臧述升,男,博士,研究员,研究领域为燃气轮机燃烧及热端部件冷却。E-mail: sszang@sjtu.edu.cn