突片形状对气膜冷却效率的影响
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摘要
气膜冷却广泛应用于航空发动机热端部件的热防护,为了提高气膜冷却效果,设计了3种突片型式,采用实验的方法对其冷却效果进行了对比研究,结果表明:突片的存在强化了气膜冷却效率,使得气膜冷却效率远高于无突片的气膜冷却效率。吹风比对不同突片作用有所不同,存在一最佳吹风比,但该值随着突片的型式变化。突片的堵塞比对气膜冷却效率有很大的影响,3种突片作用下的气膜冷却效率均随堵塞比的增加而增大。梯形突片的冷却效率明显优于三角形突片和椭圆突片。但突片亦增大了气膜孔的流动阻力,降低了流量系数。
The film cooling is widely used in the thermal protection of aircraft engine.To improve the effectiveness of film cooling,three kinds of tabs are designed,and experimenal results of film cooling effectiveness show that tabs on the film holes can effectively strengthen the film cooling efficiency,which makes the film cooling effectiveness much higher than that without tabs.The effects of blowing ratios on film cooling is different for different tabs,and there exists an optimal blowing ratio which is different for different tabs.The blockage ratio of tabs has a great influence on film cooling effectiveness.The three kinds of tabs keep the same film cooling characteristics that the film cooling effectiveness increases with the increase of the blockage ratio.Trapezoidal triangle tab is obviously better than the other two kinds of tabs.However,the discharge coefficient of the film hole is largely decreased by the tab.
The film cooling is widely used in the thermal protection of aircraft engine.To improve the effectiveness of film cooling,three kinds of tabs are designed,and experimenal results of film cooling effectiveness show that tabs on the film holes can effectively strengthen the film cooling efficiency,which makes the film cooling effectiveness much higher than that without tabs.The effects of blowing ratios on film cooling is different for different tabs,and there exists an optimal blowing ratio which is different for different tabs.The blockage ratio of tabs has a great influence on film cooling effectiveness.The three kinds of tabs keep the same film cooling characteristics that the film cooling effectiveness increases with the increase of the blockage ratio.Trapezoidal triangle tab is obviously better than the other two kinds of tabs.However,the discharge coefficient of the film hole is largely decreased by the tab.
引文
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[15]李建华,杨卫华.椭圆形突片气膜冷却效率的试验研究[J].动力工程,2008,24(4):528-531.Li Jianghua,Yang Weihua.The experimental study of cooling efficiency on film cooling with ellipse tab[J].Journal of Power Engineering,2008,24(4):528-531.
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[2]杨卫华,彭建勇,曹俊,等.回流燃烧室复合冷却结构冷却效果研究[J].南京航空航天大学学报,2012,44(6):769-774.Yang Weihua,Peng Jianyong,Cao Jun,et al.Experimental study on cooling effectiveness of compound cooling configurations in reverse flow combustor[J].Journal of Nanjing University of Aeronautics&Astronautics,2012,44(6):769-774.
[3]Yao Y,Zhang J Z.Investigation on film cooling characteristics from a row of converging slot holes on flat plate[J].Sci China Technol Sci,2011,54:1793-1800.
[4]Heneka C,Schulz A,Bauer H J,et al.Film cooling performance of sharp edged diffuser holes with lateral inclination[J].ASME,Journal of Turbomachinery,2012,134:041015-1-7.
[5]Yusop N M,Ali A H,Abdullah M Z.Computational study of a new scheme for a film-cooling hole on convex surface of turbine blades[J].International Communications in Heat and Mass Transfer,2013,43:90-99.
[6]Liu Cunliang,Zhu Huiren,Zhang Zongwei,et al.Experimental investigation on the leading edge film cooling of cylindrical and laid-back holes with different hole pitches[J].International Journal of Heat and Mass Transfer,2012,55:6832-6845.
[7]Liu C L,Zhu H R,Bai J T,et al,Experimental research on the thermal performance of converging slot holes with different divergence angles[J].Exp Therm Fluid Sci,2009,33:808-817.
[8]Liu C L,Zhu H R,Bai J T,et al.Experimental and numerical investigation on the film cooling of waistshaped slot holes comparing with converging slot holes[J],ASME,Journal of Turbomachinery,2012,134:011021-1-10.
[9]Zaman K B M Q,Foss J K.The effect of vortex generators on a jet in a cross-flow[J].Phys Fluids,1997,9:106-114.
[10]Zaman K B M Q.Reduction of jet penetration in a cross-flow by using tabs[R].AIAA-98-3276,1998.
[11]Li Y K,Zhang J Z,Yao Y,Numerical investigation on improvement of film cooling effectiveness using delta-shaped tabs[J].J Aerospace Power,2006,21:83-87.
[12]Yang Chengfeng,Zhang Jingzhou.Experimental investigation on film cooling characteristics from a row of holes with ridge-shaped tabs[J].Experimental Thermal and Fluid Science,2012(37):113-120.
[13]杨卫华,马国锋,张靖周.突片作用下气膜冷却对流传热特性的试验研究[J].航空动力学报,2006,21(6):978-983.Yang Weihua,Ma Guofeng,Zhang Jingzhou.Experimental study on convective heat transfer characteristics of film cooling with tab[J].Journal of Aerospace Power,2006,21(6):978-983.
[14]杨卫华,李永康,张靖周,等.突片作用下气膜冷却效率的试验研究[J].航空动力学报,2007,22(3):380-383.Yang Weihua,Li Yongkang,Zhang Jingzhou,et al.Experimental study of cooling efficiency of film cooling with tab[J].Journal of Aerospace Power,2007,22(3):380-383.
[15]李建华,杨卫华.椭圆形突片气膜冷却效率的试验研究[J].动力工程,2008,24(4):528-531.Li Jianghua,Yang Weihua.The experimental study of cooling efficiency on film cooling with ellipse tab[J].Journal of Power Engineering,2008,24(4):528-531.
[16]陈利强,杨卫华,杨成风,等.梯形突片气膜冷却特性的实验[J].航空动力学报,2008,23(9):1660-1669.Chen Liqiang,Yang Weihua,Yang Chengfeng,et al.The experimental study on cooling characteristics of film cooling[J].Journal of Aerospace Power,2008,23(9):1660-1669.