期刊文献+

不同主流进口湍流度下的超音速气膜冷却 被引量:6

INFLUENCE OF FREE-STREAM TURBULENCE ON SUPERSONIC FILM COOLING
原文传递
导出
摘要 本文通过数值模拟的方法计算并分析主流进口湍流度、冷却流进口高度和进口马赫数对超音速气膜冷却的影响。计算结果表明,主流进口湍流度对超音速气膜冷却有较大影响,增大主流进口湍流度会减弱超音速气膜冷却效率,同时还表明,增大冷却流进口高度以及进口马赫数,能减弱主流湍流度对超音速气膜冷却的影响。 Numerical simulations are used to assess the effect of free-stream turbulence,coolant inlet height and Mach number on supersonic film cooling.The results indicate that increasing free-stream turbulence reduces the adiabatic film cooling effectiveness,while increasing coolant inlet height and Mach number weaken the effect of the free-stream turbulence.
作者 彭威 姜培学
出处 《工程热物理学报》 EI CAS CSCD 北大核心 2010年第1期127-129,共3页 Journal of Engineering Thermophysics
基金 国家自然科学重点基金项目(No.50736003) 973项目(No.2007CB210107)
关键词 超音速 气膜冷却 湍流度 supersonic film cooling free-stream turbulence
  • 相关文献

参考文献6

  • 1Saumweber C, Schulz A, Wittig S. Free-Stream Turbulence Effects on Fihn Cooling with Shaped Holes [J]. Journal of Turbomachinery, 2003, 125(1): 65-73.
  • 2Kohli A, Bogard D G. Effects of Very High FreeStream Turbulence on the Jet-Mainstream Interaction in a Film Cooling Flow [J]. Journal of Turbomachinery- Transactions of the ASME, 1998, 120(4): 185-790.
  • 3Bons J P. MacArthur C D, Rivir R B. The Effect of High Free-Stream Turbulence on Film Cooling Effectiveness [J]. Journal of Xhrbomachinery-Transactions of the ASME, 1996, 118(4): 814-825.
  • 4Juhany K A, Hunt M L, Sivo J M. Influence of Injecrant Math Number and Temperature on Supersonic Film Cooling [J]. Journal of Thermophysics and Heat Transfer, 1994, 8:59-67.
  • 5Kanda T, Ono F. Takahashi M, et al. Experimental Studies of Supersonic Film Cooling with Shock Wave interaction [J]. AIAA Journal, 1996, 34: 265-271.
  • 6Lebedev V P, Lemanov V V, Terekhov V I. Fihn-Cooling Efficiency in a Laval Nozzle Under Conditions of High Freestream Turbulence [J]. Journal of Heat Transfer, 2006, 28:571-579.

同被引文献42

  • 1张小英,王先炜.轴对称矢量喷管红外特性的数值计算研究[J].航空动力学报,2004,19(3):366-369. 被引量:24
  • 2王扬平,姜培学.超音速气膜冷却及其受斜激波的影响[J].工程热物理学报,2007,28(1):137-139. 被引量:5
  • 3Rao G A, Mahulikar S P. New Criterion for Aircraft Suscepti- bility to Infrared Guided Missiles [ J ]. Aerospace Science and Technology,2005,9 : 701 -712.
  • 4Mahulikar S P, Sonawane H R, Rao G A. Infrared Signature Studies of Aerospace Vehicles [ J ]. Progress in Aerospace Sciences,2007,43 : 218 -245.
  • 5Lebedev V P, Lemanov V V ,Terekhov V I. Film Cooling Effi- ciency in a Laval Nozzle under Conditions of High Freestream Turbulence[ J]. ASME Journal of Heat Transfer, 2006,28 : 571 - 579.
  • 6Ochs M, Schulz A, Bauer H J. Design and Commissoning of a Transonic Test Section for the Investigation on Shock Wave- film Cooling Interactions[ R]. ASME- GT2006- 90468 ,2006.
  • 7Martelli E, Nasuti F, Onofri M. Numerical Parametric Analy-sis of Dual- bell Nozzle Flows [ J ]. AIAA Journal, 2007,45 : 640 - 650.
  • 8Ochs M, Schulz A, Bauer H J. Design and Commissioning of a Transonic Test sSetion for the Investigation of Shock Wave- film Cooling Interactions[ R]. ASME- GT2006-90468,2006.
  • 9Martelli E. Film Cooling Effect on Dual- bell Nozzle Flow Transition [ R ]. AIAA - 2009 - 4953,2009.
  • 10Wei Peng, Jiang Peng xue. Influence of Dhock Eaves on Dupersonic Film Cooling [ J ]. Journal of Spacecraft and Rockets,2009,46 ( 1 ) :69 - 73.

引证文献6

二级引证文献10

相关作者

内容加载中请稍等...

相关机构

内容加载中请稍等...

相关主题

内容加载中请稍等...

浏览历史

内容加载中请稍等...
;
使用帮助 返回顶部