冲击/发散冷却壁温分布和冷却效率研究

胡超; 许全宏; 徐剑; 林宇震

冲击/发散冷却壁温分布和冷却效率研究

北京航空航天大学能源与动力工程学院, 航空发动机气动热力国防科技重点实验室, 北京 100191

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出版历程
- 收稿日期: 2007-09-20
- 修回日期: 2007-11-26
- 刊出日期: 2008-10-28

Investigation of the wall temperature distribution and cooling efficiency for impingement/effusion cooling scheme

National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 针对高温升燃烧室长寿命火焰筒的要求,实验研究了孔排列方式、发散壁壁厚与孔径之比以及单位面积开孔率对壁温分布和冷却效率的影响.实验中冷却气为常温常压,主流速度20m/s,发散壁孔内气流与主流速度比为0.63,主流与冷却气温度比为1.6.实验结果表明:长菱形排布与正菱形排布相比冷却效率更高,但孔的排布方式对于壁温分布的影响较小;增大发散壁壁厚与孔径比可以增强冷却效果,并使壁温分布变得均匀;而减小单位面积开孔率对于壁温分布的影响较小,同时冷却效率也会降低.
- 壁温分布 /
- 冷却效率 /
- 燃烧室 /
- 冲击/发散 /
- 火焰筒
Abstract: In order to meet long-duration requirements of high-temperature combustor liner,impingement/ effusion cooling scheme was investigated experimentally in the following aspects: the influence of the hole arrangements,the ratio of the wall thickness to the hole diameter,and the opening rate per unit area on the overall cooling effectiveness and wall temperature distribution.The condition of cooling air was under atmospheric temperature and pressure.The velocity of the main flow was 20 m/s.The velocity ratio of the cooling air to the main flow was 0.63,and the temperature ratio of the main flow to the cooling air was 1.6.The experimental results indicate that it has a better performance in the cooling efficiency with the long rhombus hole arrangement,while little influence on wall temperature distribution,and reducing the opening rate per unit area has the same result.The wall temperature distribution becomes more uniform when the ratio of the wall thickness to the hole diameter increases,and the cooling efficiency will decrease at the same time.
- wall temperature distribution /
- cooling efficiency /
- combustor /
- impingement/effusion /
- liner

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参考文献(12)

[1]	Sokolowski D E,Rohde J E.The E3 combustor status and challenges[R].NASA-TM-82684,1981.
[2]	Du Bell T L,le Tourneau J J,Kaplam R M.Advanced float-wall TM combustor liner technology eliminates TF30-P-100 transition duct fatigue cracking[R].AIAA-85-1288.
[3]	俞文利,林宇震,刘高恩.冲击加发散双层壁冷却方式发散内换热研究[J].航空动力学报,2001,16(4):365-369.YU Wenli,LIN Yuzhen,LIU Gaoen.Investigation of heat transfer inside inclined multi··hole in the impingement/inelined multi-hole double wall[J].Journal of Aerospace Power,2001,16(4):365-369.(in Chinese)
[4]	许全宏,林宇震,刘高恩.冲击加发散双层壁冷却方式流量系数研究[J].推进技术,2000,21(5):49-52.XU Quanhong,I.IN Yuzhen,LIU Gaoen.Discharge coefficient of double wall with discrete-hole and inclined multihole for combustor liner[J].Journal of Propulsion Technology,2000,21(5):49-52.(in Chinese)
[5]	许全宏,张宝华,林宇震,等.冲击加发散双层壁冷却方式绝热温比研究[J].航空动力学报,2000,15(4):387-390.XU Quanhong,ZHANG Baohua,LIN Yuzhen,et al.Adiabatic film effectiveness of the double wall with inclined multi-hole and discrete-hole for combustor liner[J].Journal of Aerospace Power,2000,15(4):387-390.(in Chinese)
[6]	林宇震,俞文利,刘高恩,等.冲击加发散双层壁冷却方式压降分配对斜孔内对流换热影响的研究[J].航空学报,2003,24(2):97-101.LIN Yuzhen,YU Wenli,I.IU Gaoen,et al.Influence of pressure drop distribution on the convection heat transfer inside the inclined hole of impingement/effusion cooling[J].Acta Aeronautica et Astronautica Sinica,2003,24 (2):97-10lI(in Chinese)
[7]	赵清杰,李彬.陈志杰,等.浮动肇燃烧室实验研究[J].燃气涡轮实验与研究,2004,17(1):17-19.ZHA0 Qingjie,LI Bin,CHEN Zhijie,et al.An experimental study of floating-wall eombustor[J].Gas Turbine Experiment and Research,2004,17(1):17-19.(in Chinese)
[8]	许全宏,林宇震,刘高恩.封闭空间内单孔冲击局部换热特性研究[J].航空动力学报,2002,17(3):34l-343.XU Quanhong,LIN Yuzhen,LIU Gaoen.Investigation of impingement heat transfer of single hole in a limitedspace[J].Journal of Aerospace Power,2002,17(3):341-343.(in Chinese)
[9]	Andrews G E,Aldabagh A M,Asere A A.et al.Impingement/effusion cooling,heat transfer and cooling in gas turbine[R].AGARD CP 527,1992.
[10]	Aldabagh A M,Andrews G E,Abdul Husain R A A,et a1.Impingement/effusion cooling:The influence of the number of impingement holes and pressure loss on the heat transfer coefficient[R].ASME Paper 89-GT-188.
[11]	徐剑.火焰筒先进冷却方式壁温梯度研究[D].北京:北京航空航天大学,2007.XU Jian.The investigation of the temperature gradient for advanced cooling methods on combustion liner[D].Beijing:Beijing Universty of Aeronautics and Astronautics,2007.(in Chinese)
[12]	许全宏,林宇震,刘高恩.冲击加多斜孔双层壁冷却方式冲击换热系数[J].大连理工大学学报,2001,41(1):63-66.XU Quanhong,LIN Yuzhen,LIU Gaoen,Heat transfer coefficient of impingement of fusion double wall cooling method[J].Journal of Dalian University of Technology,2001,41(1):63-66.(in Chinese)