非定常环境下动叶气膜冷却流场的数值模拟

周莉; 张鑫; 蔡元虎

非定常环境下动叶气膜冷却流场的数值模拟

西北工业大学动力与能源学院,西安 710072

基金项目: 国家自然科学基金(50906071); 西北工业大学基础研究基金(JC201011); 西北工业大学翱翔之星项目

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出版历程
- 收稿日期: 2010-07-23
- 修回日期: 2010-11-20
- 刊出日期: 2011-08-28

Unsteady numerical simulation of the turbine blade film cooling

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

摘要

摘要: 对非定常环境下动叶气膜冷却的流场进行了数值模拟,研究了动静部件之间非定常效应对气膜冷却效率的影响.计算结果表明,静叶的尾流迁移在冷气喷射位置处时,冷气在喷射位置下游壁面附近的覆盖宽度增大,距喷射位置下游约30%弧长范围内具有较高的气膜冷却效率,但在喷射位置附近的冷却效果略差一些.气膜冷却效率的振荡幅度随着吹风比的增大而增大.由于端壁附近旋涡的影响,冷气很难到达端壁附近,而是被卷吸到喷射位置的下游去,在喷射位置下游靠近端壁附近的冷却效果更好一些.
- 动叶气膜冷却 /
- 非定常效应 /
- 气膜冷却效率 /
- 尾流 /
- 端壁
Abstract: The unsteady flowfield of the turbine blade film cooling was investigated numerically,and the influence of unsteady stator/rotor interaction on the blade film cooling effectiveness was discussed.Results show that,the overlying width of the cooling jet flow increases near the downstream of the cooling jet position,when the stator wake is transferred to the cooling jet position,resulting in better film cooling effectiveness at the downstream within 30% arc length range.The fluctuation of the film cooling effectiveness increases with the increment of the blowing rate.Due to the influence of the vortex near the endwall,the cooling jet flow can hardly reach the endwall region,but be entrained to the downstream of the jet position,so the cooling effectiveness is improved correspondingly.
- turbine blade film cooling /
- unsteady interaction /
- film cooling effectiveness /
- wake /
- endwall

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参考文献(12)

[1]	Teng S,Han J C,Poinsatte P E.Effect of film-hole shape on turbine-blade heat-transfer coefficient distribution[J].Journal of Thermophysics and Heat Transfer,2001,15(3):249-256.
[2]	Schobeiri M T,ztürk B.Experimental study of the effect of periodic unsteady wake flow on boundary layer development,separation,and reattachment along the surface of a low pressure turbine blade.ASME Paper GT2004-53929,2004.
[3]	Bons J P,Rivir R B,Mac Arthur C D,et al.The effect of unsteadiness on film cooling effectiveness.AIAA 95-0306,1995.
[4]	Garg V K,Abhari R S.Comparison of predicted and experimental Nusselt number for a film-cooled rotating blade.ASME Paper 96-GT-223,1996.
[5]	朱惠人,张丽,刘松龄.非定常尾迹对涡轮叶片换热影响的数值模拟[J].推进技术,1999,20(4):53-56. ZHU Huiren,ZHANG Li,LIU Songling.Numercial simulation of influence of unsteady wake on heat transfer of turbine blade[J].Journal of Propulsion Technology,1999,20(4):53-56.(in Chinese)
[6]	Kim S T,Hassan I G.Unsteady heat transfer analysis of a film cooling flow.AIAA 2008-1287,2008.
[7]	Heidmann J D,Lucci B L,Reshotko E.An experimental study of the effect of wake passing on turbine blade film cooling[J].ASME Journal of Turbomachinery,2001,123(1):214-221.
[8]	Narzary D P,Gao Z H,Mhetras S.Effect of unsteady wake on film-cooling effectiveness distribution on a gas turbine blade with compound shaped holes.ASME Paper GT2007-27070,2007.
[9]	Gao Z,Narzary D P,Han J C.Film cooling on a gas turbine blade pressure side or suction side with axial shaped holes[J].International Journal of Heat and Mass Transfer,2008,51(10):2139-2152.
[10]	Teng S,Sohn D K,Han J C.Unsteady wake effect on film temperature and effectiveness distributions for a gas turbine blade[J].ASME Journal of Turbomachinery,2000,122(2):340-347.
[11]	袁锋,竺晓程,杜朝辉.尾迹对气膜冷却影响的三维非定常数值模拟[J].动力工程,2006,26(6):818-821. YUAN Feng,ZHU Xiaocheng,DU Zhaohui.Three dimensional unsteady numerical simulation of the effect of wakes on film cooling[J].Journal of Power Engineering,2006,26(6):818-821.(in Chinese)
[12]	Turner M G,Vitt P H,Topp D A,et al.Multistage simulations of the GE90 turbine.NASA-CR-1999-209311,1999.