涡扇发动机折流燃烧室的气动分析  

Aerodynamic Analysis of Fanjet Annular Slinger Combustor

作　　者：王伟利[1] 陈宝延[1] 于锦峰[1] 郭昊雁[1] 

机构地区：[1]北京动力机械研究所,北京100074

出　　处：《战术导弹技术》2014年第3期84-89,共6页Tactical Missile Technology

摘　　要：针对某型发动机折流燃烧室附带空心叶片导向器的独特结构,给出了一种简便的气动特性一维计算方法,并与三维数值仿真结果进行了对比。计算结果表明,两种方法计算下的总温总压等性能参数基本一致,在计算火焰筒流量分配时的最大偏差为2.36%,总压恢复系数偏差不大于0.5%。该计算方法为折流燃烧室的流量分配与气动评估提供了便利,适用于燃烧室的改型和初步设计。A convenient one-dimensional method of calculating aerodynamic characteristics for annular slinger eombustor with hollow-blade guide vanes was proposed. The results of one-dimensional method are compared with three-dimensional, which are in good agreement with results of CFD simulation. The flow distribution discrepancies between two methods are lower than 2.36% , the deviation of total-pressure re- covery coefficient below 0.5 %. The method can greatly facilitate flow distribution and aerodynamic eval- uation of slinger eombustors. It is appropriate to the retrofit and preliminary design of combustors.

关 键 词：折流燃烧室 气动特性 一维方法 初步设计 

分 类 号：TJ760.33[兵器科学与技术—武器系统与运用工程]