气动参数对后台阶三维缝隙气膜冷却效率的影响

朱惠人; 原和朋; 周志强; 许都纯

气动参数对后台阶三维缝隙气膜冷却效率的影响

西北工业大学动力与能源学院, 陕西西安 710072

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出版历程
- 收稿日期: 2005-06-26
- 修回日期: 2006-02-23
- 刊出日期: 2006-04-28

Effect of Aerodynamic Parameters of Backward-Step Three Dimensional Slots on Film Cooling Effectiveness

School of Power and Energy, Northwestern Polytechnical University, Xi'an 710072, China

摘要

摘要: 针对涡轮叶片尾缘冷却结构特点,建立了后台阶三维缝隙结构气膜冷却特性试验台,测量了缝隙中心和肋中心下游气膜冷却效率的局部分布,研究了气动参数变化对冷却效率的影响,其中基于缝高的二次流雷诺数变化范围是5 000～15 000,吹风比变化范围是0.5～2.0。试验结果表明:（1）二次流雷诺数对下游冷却效率的影响较小,对三维掺混区域的范围影响也不大;（2）吹风比对冷却效率有较大影响,总体上冷却效率随吹风比增大而降低;（3）吹风比对三维掺混区的范围及三维掺混的特征均有较大影响,吹风比较低时,二次流向两侧肋后区域的流动扩散性较好,有利于提高整个被保护面的冷却效率,吹风比较高时,二次流向两侧肋后区域的流动扩散性较差,造成肋后区域冷却效率较低。
- 航空、航天推进系统 /
- 涡轮叶片 /
- 三维缝隙 /
- 薄膜冷却 /
- 掺混流
Abstract: According to the feature of the turbine blade trailing edge cooling,film cooling effectiveness of backward-step three dimensional slots injection was measured at the slot center line and rib center line.The effects of aerodynamic parameters on the film cooling effectiveness have been studied.The secondary flow Reynolds number based on slot height varied from 5 000 to 15 000 and blowing ratio changed from 0.5 to 2.0.The experimental results show that the influence of secondary flow Reynolds Number on film cooling effectiveness and three dimensional flow mixing region is unremarkable;the influence of blowing ratio on film cooling effectiveness,and the size and performance of the three dimensional mixing flow region is very significant.For lower blowing ratio,secondary flow will flow into mainstream region and the region behind the rib,this will benefit the protected wall;for high blowing ratio,the situation is the contrary.
- aerospace propulsion system /
- turbine blade /
- trailing edge slot /
- film cooling /
- flow mixing

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参考文献(8)

[1]	葛绍岩,刘登赢,许靖中,等.气膜冷却.北京:科学出版杜,1985.
[2]	Bittlinger G,Schulz A,Wittig S.Film Cooling Effectiveness and Heat Transfer Coefficients for Slot Injection at High Blowing Ratios[R].ASME J GT-94-182,1994.
[3]	Sturgess G J.Design of Combustor Cooling Slots for High Film Cooling Effectiveness:Part Ⅰ -Film General Development[R].ASME 85-GT-35,1985.
[4]	Sturgess G J,Pfeiffer G D.Design of Combustor Cooling Slots for High Film Cooling Effectiveness:Part 2,Film Initial Development[R].ASME 85-GT-36,1985.
[5]	Holloway D S,Leylek J H,Scott F A.Pressure Side Bleed Film Cooling:Part Ⅰ -Steady Framework for Experimental and Computational Results[R].ASME GT-2002-30741,2002.
[6]	Holloway D S,Leylek J H,Scott F A.Pressure Side Bleed Film Cooling:Part Ⅰ -Unsteady Framework for Experimental and Computational Results[R].ASME GT 2002-30742,2002.
[7]	Martini P,Schulz A,Whitney C F,Lutum E.Experimental and Numerical Investigation of Trailing Edge Film Cooling Downstream of a Slot with Internal Rib Arrays[R].5th European Conference on Gas Turbines,2003.
[8]	Martini P,Schulz A.Experimental and Numerical Investigation of Trailing Edge Film Cooling by Circular Coolant Wall Jets Ejected from a Slot with Internal Rib Arrays[J].Journal of Turbomachinery,Issue 2,2004,126:2 29～ 236.