发散冷却与冲击/发散冷却的冷却效率对比

杨谦; 林宇震; 张弛; 许全宏

doi:10.13224/j.cnki.jasp.2014.02.004

发散冷却与冲击/发散冷却的冷却效率对比

doi: 10.13224/j.cnki.jasp.2014.02.004

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家级重点实验室, 北京 100191

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出版历程
- 收稿日期: 2012-12-28
- 刊出日期: 2014-02-28

Cooling effectiveness comparison between effusion cooling and impingement/effusion cooling

National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics, School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 为了得到最佳的冷却结构，在相同冷却气量下对发散孔单层壁与冲击/发散孔双层壁冷却结构的冷却效率进行了试验研究.试验保证相同的发散孔排布规律、热侧与冷侧进气温度、冷却气量、热气量以及热冷侧之间的空气压降，使用红外热像仪对发散孔壁的热侧壁面温度进行测量以得到冷却效率，并对两种结构的冷却效率进行对比分析.试验结果表明：在相同冷却开孔面积、相同冷热气条件下，冲击/发散孔双层壁的冷却效率要比发散孔单层壁大约高30%，这归因于冲击/发散冷却方式存在更高的换热强化能力.
- 发散孔 /
- 冲击/发散孔 /
- 单层壁 /
- 双层壁 /
- 冷却效率
Abstract: In order to acquire the optimal cooling approach of aero-engine chamber,experimental approaches were taken to study the cooling effectiveness of effusion cooling and impingement/effusion cooling.Cooling effectiveness of these two types of cooling configurations were investigated on the same hot/cold air conditions of inlet,such as position of effusion holes,inlet temperature of hot/cool side,mass flow of hot/cool air,pressure drop between hot/cool sides.Infrared camera was used to measure the temperature of effusion cooled surfaces on the side of hot main stream to get the cooling effectiveness,and analyzed the cooling effectiveness of these two cooling configurations.The results show that on the condition of the same opening area and hot/cold air conditions of inlet,double wall cooling gets higher cooling effectiveness than effusion cooling configurations by approximately 30%, owing to the heat transfer enhancement within the gap of the double walls.
- effusion holes /
- impingement/effusion holes /
- single wall /
- double walls /
- cooling effectiveness

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参考文献(25)

[1]	Mellor A M.Design of modern turbine combustors[M].London,UK:Academic Press,1990.
[2]	Tanrikut S,Marshall R L.Improved combustor durability-segmented spproach with advanced cooling techniques[R].AIAA 81-1354,1981.
[3]	林宇震,许全宏,刘高恩.燃气轮机燃烧室[M].北京:国防工业出版社,2008.
[4]	Colladay R S.Importance of combining convection with film cooling[R].AIAA 72-8,1972.
[5]	Mongia H C,Reider S B.Allison combustion research and development activities[R].AIAA 85-1402,1985.
[6]	Andrews G E,Alikhanpadeh M.Small diameter film cooling holes:wall convection heat transfer[R].ASME Paper 86-GT-225,1986.
[7]	Ou S,Rivir R B.Shaped-hole film cooling with pulsed secondary flow[R].ASME Paper GT2006-90272,2006.
[8]	LU Yiping,Alok D,Ekkad S V.Film cooling measurements for cratered cylindrical inclined holes[J].Journal of Turbomachinery,2009,131(1):011005.1-011005.12.
[9]	LU Yiping,Alok D,Ekkad S V.Trench film cooling-effect of trench downstream edge and hole spacing[R].ASME Paper GT2008-50606,2008.
[10]	Dorrington J R,Bogard D G.Film effectiveness performance for coolant holes embedded in various shallow trench and crater depressions[R].ASME Paper GT2007-27992,2007.
[11]	Ceccherini A,Facchini B.Combined effect of slot injection,effusion array and dilution hole on the cooling performance of a real combustor liner[R].ASME Paper GT2009-60047,2009.
[12]	Facchini B,Maiuolo F,Tarchi L.Combined effect of slot injection,effusion array and dilution hole on the heat transfer coefficient of a real combustor liner:Part 1 experimental analysis[R].ASME Paper GT2010-22936,2010.
[13]	Facchini B,Maiuolo F,Tarchi L.Combined effect of slot injection,effusion array and dilution hole on the heat transfer coefficient of a real combustor liner:Part 2 numerical analysis[R].ASME Paper GT2010-22937,2010.
[14]	Andreini A,Bonini A.Numerical study of aerodynamic losses of effusion cooling holes in aero-engine combustor liners[R].ASME Paper GT2010-22942,2010.
[15]	赵清杰,李彬,陈志杰,等.浮动壁燃烧室试验研究[J].燃气涡轮试验与研究,2004,17(1):17-20. ZHAO Qingjie,LI Bin,CHEN Zhijie,et al.An experimental study of floating-wall combustor[J].Gas Turbine Experiment and Research,2004,17(1):17-20.(in Chinese)
[16]	Tanrikut S,Marshall R L.Improved combustor durability segmented approach with advanced cooling techniques[R].AIAA 81-1354,1981.
[17]	Sokolowski D E,Rohde J E.The E3 combustors:status and challenges[R].NASA-TM-82684,1981.
[18]	赵清杰,李彬.浮动瓦块冷却结构在燃烧室中的应用和发展[J].燃气涡轮试验与研究,2001,14(1):10-13. ZHAO Qingjie,LI Bin.Application and development of floating panel cooling structure in combustors[J].Gas Turbine Experiment and Research,2001,14(1):10-13.(in Chinese)
[19]	Oha S H,Leea D H,Kima K M.Enhanced cooling effectiveness in full-coverage film cooling system with impingement jets[R].ASME Paper GT2008-50784,2008.
[20]	Land C C,Thole K A.Considerations of a double-wall cooling design to reduce sand blockage[R].ASME Paper GT2008-50160,2008.
[21]	Sweeney P C,Rhodes J F.An infrared technique for evaluating turbine airfoil cooling designs[J].Journal of Turbomachinery Transactions,2000,122(1):170-177.
[22]	Harrington M K,McWaters M A,Bogard D G,et al.Full-coverage film cooling with short normal injection holes[R].ASME Paper 2001-GT-0130,2001.
[23]	ZHANG Chi,SONG Bo,LIN Yuzhen,et al.Cooling effectiveness of effusion walls with deflection hole angles measured by infrared imaging[J].Applied Thermal Engineering,2009,29(5/6):966-972.
[24]	林宇震.燃烧室多斜孔壁气膜冷却研究[D].北京:北京航空航天大学,1997. LIN Yuzhen.An investigation of the inclined multihole wall film cooling in combustion chamber[D].Beijing:Beijing University of Aeronautics and Astronautics,1997.(in Chinese)
[25]	许全宏.燃烧室冲击/发散复合冷却方式研究[D].北京:北京航空航天大学,2001. XU Quanhong.The investigation of impingement/effusion double wall cooling method for combustor[D].Beijing:Beijing University of Aeronautics and Astronautics,2001.(in Chinese)