弯曲段冲击扰流柱/逆向对流/气膜冷却 效率的研究(1)——实验

石蕊; 熊纯; 曹俊; 谢婕; 杨卫华; 宋双文

弯曲段冲击扰流柱/逆向对流/气膜冷却效率的研究(1)——实验

1.
南京航空航天大学能源与动力学院,南京 210016
2.
长沙航空职业技术学院航空装备维修工程系,长沙 410124
3.
中国航空工业集团公司中国航空动力机械研究所,湖南株洲 412002

基金项目: 国家自然科学基金(50876041)

计量
- 文章访问数: 1716
- HTML浏览量: 114
- PDF量: 14
- 被引次数: 0
出版历程
- 收稿日期: 2010-04-12
- 修回日期: 2010-06-07
- 刊出日期: 2011-04-28

Cooling efficiency study of impingement pin fin /reversed convection/ film cooling in curved section Part 1: experiments

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China
2.
Aeronautical Equipment Repairing Engineering Deparment, Changsha Aeronautical Vocational and Technical College,Changsha 410124,China
3.
China Aviation Powerplant Research Institute, Aviation Industry Corporation of China,Zhuzhou Hunan 412002,China

摘要

摘要: 为了研究回流燃烧室弯曲段冲击扰流柱/逆向对流/气膜冷却结构形式对冷却效率的影响规律,设计了5种不同几何尺寸的实验件并进行了实验研究,研究结果表明:①扰流柱的存在使得弯曲段冲击扰流柱/逆向对流/气膜冷却效率得到了提高,特别是在小吹风比时更为突出;②吹风比对复合冷却效率有很大的影响,在相同冷却壁面处冷却效率随吹风比的增加而增加,但当吹风比M>1.0时,吹风比对冷却效率的影响已不明显;③扰流柱的排列形式对冷却效率的影响不大.
- 回流燃烧室 /
- 弯曲段 /
- 扰流柱 /
- 复合冷却 /
- 冷却效率
Abstract: In order to study the influence of impingement pin fin/reversed convection/film cooling structure on cooling efficiency in curved section of combustion chamber,five different kinds of geometry dimension test pieces were designed and studied experimentally.The test results show that:(1) The efficiency of impingement pin fin/reversed convection/film cooling in curved section with pin fins is better than that without pin fins,especially when the blowing ratio is small.(2) The blowing ratio has great influence on the efficiency of compound cooling;the efficiency of compound cooling increases with the blowing ratio at the same wall position.When the blowing ratio exceeds 1.0,efficiency improvement for blowing ratio is not obvious.(3) The arrangement of pin fins has little effect on cooling efficiency.
- reverse-flow combustion chamber /
- curved section /
- pin fin /

HTML

参考文献(12)

[1]	Lefebvre A H.Gas turbine combustion[M].New York:Hemisphere Publishing Corporation,1983.
[2]	Meller A M.Design of modern turbine combustor[M].New York,NY:Academic Press Inc.,1990.
[3]	Aldabagh A M,Andrews G E,Abdul Husain R A A,et al.Impingement/effusion cooling:the influence of the number of impingement holes and pressure loss on the heat transfer coefficient .ASME 89-GT-188,1989.
[4]	Andrews G E,Asere A A,Hussain C I,et al.Transpiration and impingement/effusion cooling of gas turbine combustion chambers .ISABE 85-7095,1985.
[5]	俞伯良,李继保.单、双层壁火焰筒壁面冷却效果比较试验研究[J].燃气涡轮试验与研究,1999,12(2):14-17. YU Boliang,LI Jibao.Contrast experiment study between single and double wall chamber on wall cooling efficiency[J].Gas Turbine Experiment and Research,1999,12(2):14-17.(in Chinese)
[6]	金捷,马继华,金如山.燃烧室室壁冲击/气膜复合冷却壁温分布研究(1)试验部分[J].推进技术,1994,15(1):14-17. JIN Jie,MA Jihua,JIN Rushan.Studies on the distribution of wall temperature of impingement and film cooling of combustion chambers (1):experimentally[J].Journal of Propulsion Technology,1994,15(1):14-17.(in Chinese)
[7]	金捷,马继华,金如山.燃烧室室壁冲击/气膜复合冷却壁温分布研究(2)理论部分[J].推进技术,1994,15(2):34-40. JIN Jie,MA Jihua,JIN Rushan.Studies on the distribution of wall temperature of impingement and film cooling of combustion chambers (2):theoretically[J].Journal of Propulsion Technology,1994,15(2):34-40.(in Chinese)
[8]	许全宏,林宇震,刘高恩.冲击-发散复合冷却方式发散壁换热系数研究[J].航空动力学报,2004,19(2):213-218. XU Quanhong,LIN Yuzhen,LIU Gaoen.Study of the effusion wall film heat transfer coefficients of impingement/effusion double wall cooling method[J].Journal of Aerospace Power,2004,19(2):213-218.(in Chinese)
[9]	许全宏,林宇震,刘高恩.主燃烧室冲击/发散双层壁冷却方式壁温验证试验研究[J].航空动力学报,2005,20(2):197-201. XU Quanhong,LIN Yuzhen,LIU Gaoen.Rig test of impingement/effusion double wall cooling methods for the main combustor[J].Journal of Aerospace Power,2005,20(2):197-201.(in Chinese)
[10]	韩振兴,朱谷君,冀守礼,等.气膜冷却燃烧室火焰筒二维壁温分布计算[J].航空动力学报,1995,10(1):83-86. HAN Zhenxing,ZHU Gujun,JI Shouli,et al.Calculation of 2D wall temperature distribution for film cooled flame tube of combustion chamber[J].Journal of Aerospace Power,1995,10(1):83-86.(in Chinese)
[11]	李彬,吉洪湖,江义军.燃烧室壁冲击-逆向对流-气膜冷却特性的数值研究[J].航空动力学报,2007,22(3):365-369. LI Bin,JI Honghu,JIANG Yijun.Numerical simulation for impingement-counterflow convection-film cooling of a combustor wall[J].Journal of Aerospace Power,2007,22(3):365-369.(in Chinese)
[12]	宋双文,杨卫华,胡好生,等.冲击+逆向对流+气膜冷却传热特性的实验研究[J].航空动力学报,2007,22(9):1417-1422. SONG Shuangwen,YANG Weihua,HU Haosheng,et al.Experimental study of the heat transfer characteristics of combined cooling of impingement+reversed convection+film[J].Journal of Aerospace Power,2007,22(9):1417-1422.(in Chinese)