直通道和弯曲通道中超声速气膜冷却研究

Investigation of supersonic film cooling in flat and convex channels

Key Laboratory for Thermal Science and Power Engineering of Ministry of Educations, Department of Thermal Engineering, Tsinghua University, Beijing 100084, China

摘要: 对直通道和弯曲通道两种不同几何形状中的二维平行缝槽形式的超声速气膜冷却进行了数值模拟,分析了在有、无斜激波入射冷却层时的冷却效果.计算结果表明,斜激波的入射使壁面的冷却效率较无斜激波入射时要低.在该计算模型中,无斜激波入射时,弯曲通道壁面的冷却效果好于直通道壁面,而有斜激波入射时,弯曲通道壁面的冷却效果不如直通道壁面.
- 航空、航天推进系统 /
- 超声速 /
- 气膜冷却 /
- 激波 /
- 直通道 /
- 弯曲通道
Abstract: Film cooling with supersonic,tangential-slot injection of cooling air into supersonic air flow was numerically investigated.The effect of impingement of oblique shock wave was studied and its impacts on a flat surface and on a convex surface were compared.The results indicate that the adiabatic effectiveness of both the surfaces is reduced by the impingement of the oblique shock wave.The adiabatic effectiveness of convex surface is higher than that of flat surface when oblique shock wave is absent whereas the opposite is the case when it is present.
- aerospace propulsion system /
- supersonic /
- film cooling /
- shock wave /
- flat channel /
- convex channel

[1]	Kanda T,Masuya G,Ono F,et al.Effect of film cooling/ regenerative cooling on scramjet engine performances[J].Journal of Propulsion and Power,1994,10(5):618-624.
[2]	Juhany K A,Hunt M L.Flowfield measurements in supersonic film cooling including the effect of shock-wave interaction[J].AIAA Journal,1994,32(3):578-585.
[3]	O' Connor J P,Hail-Sheikh A.Numerical study of film cooling in supersonic flow[J].AIAA Journal,1992,30 (10):2426-2433.
[4]	Takita K,Masuya G.Effects of combustion and shock impingement on supersonic film cooling by hydrogen[J].AIAA Journal,2000,38(10):1899-1906.
[5]	Juhany K A,Hunt M L,Sivo J.Influence of injectant Mach number and temperature on supersonic film cooling[J].Journal of Thermophysics and Heat Transfer,1994,8(1):59-67.
[6]	Goldstein R J,Eckert E R G,Tson F K,et al.Film cooling with air and helium injection through a rearward-facing slot into a supersonic air flow[J].AIAA Journal,1966,4(6):981-985.
[7]	Kanda T,Ono F,Takahashi M,et al.Experimental studies of supersonic film cooling with shock wave interaction[J].AIAA Journal,1996,34(2),265-271.