冲击加多斜孔双层壁对流与冲击换热优化研究

唐庆如

冲击加多斜孔双层壁对流与冲击换热优化研究

唐庆如

中国民航飞行学院, 广汉 618307

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出版历程
- 收稿日期: 2006-03-20
- 修回日期: 2006-10-30
- 刊出日期: 2007-03-28

A study of optimization of convection and heat transfer of impingement/effusion double wall

TANG Qing-ru

Civil Aviation Flight University of China, Guanghan 618307, China

摘要

摘要: 对冲击加多斜孔双层壁孔内对流和冲击换热这两部分冷却达到最大进行了优化.冲击加多斜孔双层壁结构中单位面积冲击孔数量和多斜孔数量比为1∶3, 多斜孔倾角为30°.本优化属于混合约束优化, 采用序列无约束极小化方法进行优化.通过计算分析, 得出了在冲击加多斜孔双层壁在压力降和单位面积冷却气量一定条件下的优化结果, 存在冲击换热和多斜孔内换热的最佳分配, 该结果对指导冲击加多斜孔双层壁设计有指导意义.
- 航空、航天推进系统 /
- 航空发动机 /
- 气膜冷却 /
- 冲击加多斜孔冷却 /
- 优化
Abstract: The convection and heat transfer within the effusion holes of impingement/effusion double wall were optimized to get the maximum internal cooling effect.The ratio of the number of impingement holes to the number of effusion holes per unit area is 1∶3,and the angel of effusion hole is 30 degree.As a hybrid restriction optimization approach,the sequential unconstrained minimization technique was applied for optimization.The optimal results of impingement/effusion double wall were obtained under the pressure drop and unit-area cooling air flow.The results indicate an optimal distribution between the impingement heat transfer and the convective heat transfer within the effusion holes,providing a basis for design of the impingement/effusion double wall for engineering applications.
- aerospace propulsion system /
- aero-engine /
- film cooling /
- impingement/effusion cooling /
- optimization

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参考文献(9)

[1]	俞文利,林宇震,刘高恩.冲击加多斜孔双层壁冷却方式多斜孔内换热研究[J].航空动力学报,2001,16(4):365-369.YU Wenli,LIN Yuzhen,LIU Gaoen.Investigation of heat transfer inside inclined multihole in the impingement/inclined multihole double wall[J].Journal of Aerospace Power,2001,16(4):365-369.
[2]	许全宏,林宇震,刘高恩.冲击加多斜孔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,LIN 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.
[3]	许全宏,张宝华,林宇震,等.冲击加多斜孔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 multihole and discrete-hole for combustor liner[J].Journal of Aerospace Power,2000,15(4):387-390.
[4]	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,LIU 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):97-101.
[5]	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):17-19.ZHAO Qingjie,LI Bin,CHEN Zhijie,et al.An experimental study of floating-wall combustor[J].Gas Turbine Experiment and Research,2004,17(1):17-19.
[6]	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):341-343.XU Quanhong,LIN Yuzhen,LIU Gaoen.Investigation of impingement heat transfer of single hole in a limited space[J].Journal of Aerospace Power,2002,17(3):341-343.
[7]	Andrews G E,Aldabagh A M,Asere A A,et al.Impingement/effusion cooling,heat transfer and cooling in gas turbine[R].AGARD CP 527,1992:30.1-30.10.
[8]	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[R].ASME Paper 89-GT-188.
[9]	何献忠,李萍.优化技术及其应用[M].北京:北京理工大学出版社,1995.