径向稳定器冷却方式对壁温和流场影响的数值模拟  

Impact analysis of cooling method of radial flameholder on wall temperature and flow field by numerical simulation

作　　者：翟云超 钟世林 康玉东 邓远灏 王金涛 ZHAI Yun-chao;ZHONG Shi-lin;KANG Yu-dong;DENG Yuan-hao;WANG Jin-tao(AECC Sichuan Gas Turbine Establishment,Chengdu 610500,China)

机构地区：[1]中国航发四川燃气涡轮研究院,成都610500

出　　处：《燃气涡轮试验与研究》2018年第6期14-17,共4页Gas Turbine Experiment and Research

摘　　要：为探寻一种良好的径向稳定器冷却方式,采用数值模拟的方法比较并分析了冲击冷却、冲击-发散冷却及其发散孔倾角和发散孔开孔数目对径向稳定器冷却和径向稳定器后方流场的影响。结果表明:在设计冷却气量下,冲击冷却基本能满足使用要求;冲击-发散冷却的冷却效果要比冲击冷却的好,但该冷却方式对径向稳定器后方流场的影响较大;可通过适当减小发散孔倾角和发散孔开孔数目可有效削弱冲击-发散冷却对径向稳定器后方流场的影响。In order to find a good cooling method of radial flameholder, the impact of impingement cooling, impingement effusion cooling, effusion hole inclination and number of effusion holes on the cooling of radial flameholder and the flow field behind the radial flameholder are analyzed. The results show that with designed amount of cooling air, impingement cooling can meet the basic usage requirements while the impingement effusion cooling works better. However, the impingement effusion cooling has a serious effect on the rear flow field of the radial flameholder. The influence of cooling air on the flow field could be effectively reduced by reducing the effusion hole inclination and number of effusion holes.

关 键 词：航空发动机 凹腔驻涡燃烧室 冲击冷却 冲击-发散冷却 发散孔倾角 径向稳定器 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]