带偏转角气膜出流发散壁冷却特性的数值分析  

Numerical Simulation on Cooling Characteristics of Effusion Wall with Deflection Film Outflow

作　　者：谢婕[1] 张靖周[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《南京航空航天大学学报》2013年第2期157-161,共5页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：国家自然科学基金(51276090)资助项目

摘　　要：运用数值计算方法对带偏转角气膜出流发散孔壁的冷却特性进行了研究,分析了气膜孔偏转角对气膜冷却效率和流量系数的影响。研究结果表明,带偏转角气膜孔喷出的气膜出流具有侧向涡旋特征,增强了气膜射流的横向能力,对于改善发散壁前端的冷却效率具有一定的作用,在高吹风比下更为显著;随着偏转角的增加,发散壁前端气膜孔的流量系数则呈降低趋势。Numerical investigations are performed on the cooling characteristics of effusion wall with deflection film outflow. The effects of film deflection angle on the film cooling effectiveness and discharge coefficient are revealed. The results show that a swirling film outflow issued from deflection hole enhances the lateral flow capacity of film jet and the film cooling effectiveness in the front of effusion cooled wall, especially under higher blowing ratio cases. As the increase of film deflection angle, the discharge coefficient of film holes located at the front of effusion cooled wall is decreased.

关 键 词：发散冷却 气膜孔偏转 气膜冷却效率 流量系数 数值计算 

分 类 号：V233.1[航空宇航科学与技术—航空宇航推进理论与工程] V233.2