顺–逆向组合气膜孔在涡轮导叶端壁上的应用研究  

Study on Applications of Combined Forward and Backward Injection Film Holes on Turbine Nozzle Guide Vane Endwall

作　　者：王志多 秦康 吴兴 齐文娇 张庆尧 丰镇平[2] WANG Zhiduo;QIN Kang;WU Xing;QI Wenjiao;ZHANG Qingyao;FENG Zhenping(Aviation Engineering School,Air Force Engineering University,Xi'an 710038,China;School of Energy and Power Engineering,Xi'an Jiaotong University,Xi'an 710049,China;School of Mechanical Engineering,Xi'an Shiyou University,Xi'an 710065,China)

机构地区：[1]空军工程大学航空工程学院,西安710038 [2]西安交通大学能源与动力工程学院,西安710049 [3]西安石油大学机械工程学院,西安710065

出　　处：《工程热物理学报》2023年第4期931-937,共7页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.52106122);中国博士后科学基金资助项目(No.2022M712522);西安市青年人才托举计划资助项目(No.095920221379)。

摘　　要：本文利用经过试验数据验证的RANS方法,针对高压涡轮导向器端壁双排气膜冷却结构,研究了顺向以及不同顺/逆向组合气膜孔下的端壁流动和气膜冷却特性,探索了逆向孔在涡轮端壁上应用的可行性。结果表明:端壁周向整排逆向孔出流与主流的强烈掺混增强了马蹄涡和通道涡强度并降低了冷气动量,使冷气无法到达下游区域;逆向孔布置在中部近吸力侧的顺/逆向组合方案对端壁涡系影响较小,可使端壁上游冷效明显增加且下游冷效降低较少;逆向孔角度减小,冷效增加,但提升幅度有限;本文提出的顺/逆向组合孔在MFR=1~3的范围内,明显改善了顺向孔对端壁上游冷却有限的问题,使端壁65%轴向弦长之前区域气膜冷效明显提升,且对尾缘冷效的影响较小。In this paper,the Reynolds-averaged Navier-Stokes method validated against experimental data was applied to study the flow characteristics and film cooling performance of turbine nozzle guide vane(NGV)endwall with double-row staggered film holes.The film cooling performance of forward film holes and different forward/backward combination film holes was studied to explore the feasibility of applying backward injection film holes on turbine NGV endwall.The results shown that the strong mixing between the mainstream and the film coolant injecting from backward injection film holes arranged along the whole circumferential position enhanced the intensity of horse shoe vortex and passage vortex significantly,and the enhanced vortices weaken the migration of film coolant toward downstream endwall region.The backward injection film holes arranged at mid and suction side regions have little influence on the endwall vortices,and the film cooling effectiveness at endwall upstream region can be markedly elevated with less decrement at the downstream region.The film cooling effectiveness increases with the decrease of backward injection film hole angle,while the increase range is limited.The forward/backward combination scheme proposed in this paper could improve the problem that forward injection film holes have limited cooling effectiveness at endwall upstream regions.The film cooling effectiveness is elevated before 65%axial chord length markedly,while at trailing edge is less influenced.

关 键 词：航空发动机 涡轮端壁 逆向孔 组合孔 气膜冷却 

分 类 号：TK472[动力工程及工程热物理—动力机械及工程]