气膜冷却是现代航空燃气轮机涡轮冷却技术的一种重要方法，冷却孔形状的改进是提高气膜冷却效率的重要手段。本文对双射流冷却孔形状进行了改型，并对新型双射流冷却孔在吹风比分别为0．5，1．0，1．5，2．0时的冷却效率进行了数值模拟。模拟结果表明新型双射流冷却孔与原双射流冷却孔相比在各吹风比下均优化了气膜在热表面上的分布，抑制了冷却孔出口射流的分离现象，提高了近冷却孔出口区域的气膜冷却效率；在M=0．5，1．0，1．5，2．0四种吹风比下，新型冷却孔在出口典型冷却区域（6D×10D）上的面积平均气膜冷却效率比原双射流冷却孔分别提高0．16，0．22，0．26，0．21。
Film cooling of aviation gas turbine has played a major role in preserving hot-section components of turbine at high temperature. Improvements of film cooling effectiveness can be achieved by changing film cooling hole shape. Improved double-jet film cooling hole has been designed to increase the film cooling. And, the numerical investigation of the effect of the new-type hole has been carried out in this paper at blowing ratios from 0.5 to.2.0. The results are compared with the results obtained by Kusterer （2007）, and show that improved film-cooling effectiveness can be increased because the momentum of cooling jets is decreased and lift-off of jets is inhibited. Furthermore, new double-jet film cooling hole has more homogeneous temperature distribution laterally. It is the reason that new double-jet film cooling hole has better cooling effect. Under the conditions of M=0.5, 1.0, 1.5, 2.0, area-averaged film cooling effectiveness of new-type double-jet film cooling hole is correspondingly higher than that of origin hole by 0.16, 0.22, 0.26 and 0.21.
参考文献
| [1] | D. L. Schmidt;B. Sen;D. G. Bogard .Film cooling with compound angle holes: adiabatic effectiveness[J].Journal of turbomachinery,1996(4):807-813. |
| [2] | K. T. McGovern;J. H. Leylek .A Detailed Analysis of Film-Cooling Physics: Part II - Compound-Angle Injection With Cylindrical Holes[J].Journal of turbomachinery,2000(1):113-121. |
| [3] | Karsten Kusterer;Dieter Bohn;Takao Sugimoto;Ryozo Tanaka .Double-Jet Ejection of Cooling Air for Improved Film Cooling[J].Journal of turbomachinery,2007(4):809-815. |
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