涡轮动叶吸力侧单排气膜孔冷却性能研究  

Cooling Performance of Single-Row Cylindrical Film Holes on Suction Side of a Rotor Blade

作　　者：陶皓杰 迟重然[1] 臧述升[1] TAO Hao-Jie;CHI Zhong-Ran;ZANG Shu-Sheng(School of Mechanical Engineering,Shanghai Jiao Tong University,Shanghai 200240,China)

机构地区：[1]上海交通大学机械与动力工程学院,上海200240

出　　处：《工程热物理学报》2021年第3期595-600,共6页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.51506119);工信部重大专项基础研究项目(No.2017-V-0012-0064)。

摘　　要：本文通过数值模拟的方法,针对涡轮叶片吸力侧的单排气膜孔,研究了无量纲气膜孔出流位置、气膜孔复合角度和冷却空气质量流量占比对其气膜冷却效率与气动掺混损失的影响。结果表明,对于近前缘气膜孔,0.5%的冷却空气质量流量可以在保证较好的气动效率的同时在下游附近提供较高的绝热气膜冷却效率;对于中后部气膜孔,90°的气膜孔导致的掺混损失比相同冷气量的近前缘气膜孔高出一倍,此时复合角为60°的气膜孔有更好的气膜冷却效果。对比不同的孔排位置,位于流向位置0.3的气膜孔可以在下游较大区域取得良好的冷却效果,而且不引起过大的掺混损失。In this paper,a parametric study was carried out based on 3 D RANS CFD methods to investigate the influence of both cooling performance and aerodynamic loss of theparameters of singlerow film holes on the suction side of a rotor blade.The parameters include dimensionless streamwise,compound angles,and relative coolant mass flows.The results show that for near-leading-edge film holes,0.5%of the cooling air mass flow can provide a higher adiabatic film cooling effectiveness in the downstream while ensuring better aerodynamic loss.And for the near-trailing-edge holes,the aerodynamic loss caused by the cases with 90°compound angles is much higher than that of the near-leading-edge holes.As for the downstream film holes,60°compound angle could provide better cooling performances comparing various hole positions,streamwise location 0.3 could give a favorable cooling performance on a wide area in the downstream without introducing large aerodynamic loss.

关 键 词：涡轮叶片 气膜冷却 参数化 

分 类 号：TK471[动力工程及工程热物理—动力机械及工程]