期刊文献+

不同入射角度平板气膜冷却的数值模拟

Numerical Simulations of Flat Plate Film Cooling Using Respectively Different Injection Angles
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摘要 利用RNG k-g湍流模型对斜圆柱孔不同角度入射气膜冷却进行了流动和传热的数值模拟。计算结果表明,在气动方面减小入射角度可以使冷气的射流核心更贴近壁面,但同时明显增大了壁面附近的气流速度;传热的影响也是两方面的,减小入射角度虽然可以显著地提高冷却效率,但同时也明显地增大了换热系数,最终的冷却效果取决于在实际工作状态下的底面热负荷。对于气膜冷却情况,25°入射和45°入射在总体冷却效果上都不如35°入射。 Film cooling with different injection angres was numerically simulated to investigate its flow and heat transfer characteristics, based on RNG κ-ε turbulent model. The results suggest that reducing injection angle can make the core of coolant air closer to the wall, but at the same time, accelerate the velocity of the air close to the wall evidently. The effects on the heat transfer have two sides, and the film cooling effectiveness could be increased obviously by decreasing injection angle, and the heat transfer coefficient increase remarkably at the same time. The actual cooling effect is determined by the wall thermal loads. In the cases of this thesis, the total effects of injection angle 35° is better than that of injection angles 25°and 45°.
出处 《东北电力大学学报》 2007年第6期24-28,共5页 Journal of Northeast Electric Power University
基金 国家科学自然基金项目(50476037)
关键词 气膜冷却 数值模拟 入射角度 Film Cooling Numerical Simulation Injection Angles
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参考文献9

  • 1颜培刚,王松涛,韩万金.涡轮叶栅双排孔气膜冷却数值模拟[J].工程热物理学报,2004,25(5):757-760. 被引量:5
  • 2[2]Sieverding C H,Recent progress in the understanding of basic aspects of secondary flows in turbine blade passages[J].ASME Journal of En-gineeringfor Gas Tu-ines and Power,1985,107 (2):248-257.
  • 3刘高文,董素艳,刘松龄.涡轮平面叶栅端壁附近的流动和损失[J].推进技术,2000,21(1):60-63. 被引量:9
  • 4[4]Biesinger T E,Gregory-Smith D G.Reduction in secondaryflows and losses in a turbine cascade by upstream boundarylay blowlng[C].ASME 93-GT-114,1993.
  • 5[5]Ffiedriche S,Hodson H P.Dawes W N.Distribution of film-eooling effectiveness on a turbine endwall measured using theammonia and dia-zo technique[C].ASME Journal of Turboma--chinery,1996,118(4)613-621.
  • 6刘高文,刘松龄,朱惠人,Lapworth B L,Forest A E.涡轮叶栅前缘上游端壁气膜冷却的传热实验研究[J].航空动力学报,2001,16(3):249-255. 被引量:16
  • 7刘高文,刘松龄.喷射角对涡轮叶栅端壁气膜冷却传热的影响[J].推进技术,2002,23(6):496-499. 被引量:11
  • 8[8]Zheng LJ.Jaiswal R S.Turbine nozzle endwall film ceolingstudy using pressure -sensitive paint[J].ASME Jonmal of Turbomachinery,2001,121(4):730-738.
  • 9[9]Sen B,Schmidt D L,Bogard D G.Film co ling with compound angle holes:Heat Tnmsfer[J].ASME Journal ofTurbo-machinery,1996,118 (4):800-803.

二级参考文献17

  • 1王性炎,王姝清.神经酸新资源——元宝枫油[J].中国油脂,2005,30(9):62-64. 被引量:61
  • 2Wang H P,J Turbomachinery,1997年,119卷,1期,1页
  • 3D Lakehal, G S Theodiridis, W Rodi. Three-Dimensional Flow and Heat Transfer Calculations Film Cooling at the Leading Edge of a Symmetrical Turbine Blade Model.International Journal of Heat and Fluid Flow, 2001, 22:113-122
  • 4James E Mayhew, James W Baughn, Aaron R Byerley.The Effect of Freestream Turbulence on Film Cooling Heat Transfer Coefficient. ASME GT-2002-30173, 2002
  • 5James D Heidmann, David L Rigby, Ali A Ameri. A Three-Dimensional Coupled Internal/External Simulation of a Film-Cooled Turbine Vane. ASME GT-99-186,1999
  • 6Bohn D. 3D Numerical Simulation of the Flow Through a Turbine Blade Cascade with Cooling Injection at the Leading Edge. ASME GT-1997-247, 1997
  • 7Haselhause A, Vigel D T. Numerical Simulation of Turbine Blade Cooling with Respect to Blade Heat Conduction and Inlet Temperature Profiles. AIAA Paper 95-3041, 1995
  • 8赵晓路.冷气掺混对高压涡轮导叶、转子流场结构影响的数值分析[A]..见:中国工程热物理学会热机气动热力学会议论文集[C].青岛,2002..
  • 9王松涛.[D].哈尔滨:哈尔滨工业大学,1999.
  • 10徐廷志.槭属的系统演化与地理分布[J].云南植物研究,1998,20(4):383-393. 被引量:40

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