斜流驻涡燃烧室火焰筒冷却方案数值模拟  

Numerical Simulation of Liner Cooling Scheme in Oblique Flow Trapped Vortex Combustor

作　　者：王嘉玺 张净玉[1] WANG Jia-xi;ZHANG Jing-yu(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

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：《航空发动机》2020年第4期24-29,共6页Aeroengine

摘　　要：为了优化斜流驻涡燃烧室火焰筒的冷却设计方案,根据燃烧室各部分流量分配设计要求,结合工程计算和理论设计思路,开展火焰筒壁面冷却结构设计研究。在设计多斜孔冷却方案时,分析凹腔内近壁面流场、绝热壁温、有效温比及冷却气量等参数,并据此进行进一步优化设计。结果表明:采用多斜孔加冲击复合结构有效保护了凹腔壁面,凹腔前壁最高温度降低400 K。In order to optimize the liner cooling design scheme in oblique flow trapped vortex combustor,based on the flow distribution design requirements of each part of the combustor,the design of cooling structure of liner wall was carried out combining with engineering calculation and theoretical design ideas. The parameters such as near-wall flow field,adiabatic wall temperature,effective temperature ratio and cooling gas volume in the cavity were analyzed in the design of inclined multi-hole cooling scheme. Further optimization design was carried out in view of the above. The results show that the cavity wall was protected effectively by the impact composite structure with inclined multi-hole,and the maximum temperature of the front wall of the cavity was reduced by 400 K.

关 键 词：驻涡燃烧室 火焰筒 多斜孔 冷却特性 数值模拟 航空发动机 

分 类 号：V233.7[航空宇航科学与技术—航空宇航推进理论与工程]