缩扩孔对孔板气膜冷却效果的数值研究

李志强; 田涛

缩扩孔对孔板气膜冷却效果的数值研究

李志强,
田涛

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重点实验室, 北京 100191

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出版历程
- 收稿日期: 2007-09-19
- 修回日期: 2008-03-10
- 刊出日期: 2008-10-28

Numerical studies of the effects of shaped holes on cooling effectiveness of flat plate film with conical shrink entrance and conical diffuser exit

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

摘要

摘要: 从加强气膜孔内的换热量和孔板热侧的气膜覆盖两个角度来提高气膜孔壁的冷却效果,通过对气膜孔孔型的改进,提出了缩扩型气膜孔型结构,数值计算结果表明收缩进气可以强化孔内的对流换热;而扩张出气则可以使冷气出口的速度降低,气膜覆盖面更广,提高气膜的覆盖效果.与扩张孔相比,所提出的缩扩型孔在较低的吹风比下有利于改善冷却效果,而在大吹风比下则对冷却不利;然而与普通圆柱型孔相比,缩扩型孔在任何吹风比下均能改善冷却效果.
- 气膜冷却 /
- 缩扩孔 /
- 冷却效率 /
- 数值研究
Abstract: The numerical simulation was used to study the film cooling effectiveness of plate with jet holes by increasing the heat transfer of wall of hole and enlarging the cooled area of plate in the side of hot gas stream.By studying different shape of jet holes,a new shaped hole(conical shrink entrance and conical diffuser exit shaped hole) was proposed.The computational results show that,the conical shrink entrance of the new shaped hole can efficiently enhance the convection heat transfer of wall of hole,and the conical diffuser exit of the new shaped hole can efficiently enlarge the cooled area of plate in the side of hot gas stream.If comparing with the conical diffuser shaped hole,it is found that,when the shrinkage hole is used,the film cooling effectiveness of plate is enhanced with low blowing ratio,and the film cooling effectiveness is inferior with high blowing ratio.However,when compared with the cylindrical hole,when the new shaped hole is used,the film cooling effectiveness of plate can be improved in any case.
- film cooling /
- shaped hole /
- cooling effectiveness /
- numerical studies

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参考文献(8)

[1]	陈焱.致密微孔壁复合冷却数值模拟和实验研究[D].南京;南京航空航天大学,2005.CHEN Yan.Numerical and experimental study of effusion cooling of a plate with compact tiny holes ED].Nanjing:Nanjing University of Aeronautics and Astronautics,2005.(in Chinese)
[2]	林宇震,宋波,李彬,等.多斜孔壁冷却方式小孔内对流换热研究[J].航空动力学报,1999,14(1):87-90.LIN Yunzhen,SONG 130,LI Bin,et al.A study on convective heat transfer in holes of inclined muhihole wall film cooling[J].Journal of Aerospace Power,1999,14(1):87-90.(in Chinese)
[3]	Colban W,Thole K.Influence of hole shape on the per formance of fl turbine vane endwall film-cooling scheme[J].International Journal of Heat and Fluid Flow,2007,28:341-356.
[4]	Miao J M,Wu C Y.Numerical approach to hole shape effect on film cooling effectiveness over flat plate including internal impingement cooling chamber[J].International Journal of Heat and Mass Transfer,2006,49:919-938.
[5]	Hyams D G,Leylek J H.A detailed analysis of film cooling physics:Part 11-Streamwise injection with shaped holes[J].ASME Journal of Turbomachinery,2000,122:122-132.
[6]	Brittingham R A,Leylek J H.A detailed analysis of film cooling physics:PartⅣ-Compound-angle injection with shaped holes[J].ASME Journal of Turbomachinery,2000,122:133-145.
[7]	刘建红.气膜冷却流动与传热特性的数值模拟[D].吉林:东北电力大学,2007.LIU Jianhong.Numerical simulation of characteristics of flow and heat transfer of film-cooling[D].Jilin:Northeast Dianli University,2007.(in Chinese)
[8]	康顺.冷却孔附近三维流动结构[J].工程热物理学报,2006,27(5):87-90.KANG Shun.Three dimensional flow structure nearby cooling holes[J].Journal of Engineering Thermophysics,2006,27(5):87-90.(in Chinese)