涡轮冲压组合发动机加力/冲压燃烧室流动及燃烧模拟  

Flow and Combustion Simulation of Augmented/Ramjet Burner for Turbine Based Combined Cycle Engine

作　　者：王玉男[1] 王占学[2] 张军峰[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015 [2]西北工业大学动力与能源学院,西安710072

出　　处：《航空发动机》2013年第3期23-26,76,共5页Aeroengine

摘　　要：为了解加力/冲压燃烧室内流场分布特性,利用0维串联式涡轮冲压组合发动机(TBCC)性能计算程序得到发动机主要截面参数结果。基于计算流体力学(CFD)模拟方法,进行了小型涡轮冲压组合发动机在关加力模态、开加力模态、模态转换和冲压模态下加力/冲压燃烧室内部流动及燃烧模拟,分析了单环和双环火焰稳定器对加力/冲压燃烧室长度等方面的影响,通过对比可知:在同等长度下含有双环火焰稳定器的燃烧室出口温度更高。To investigate the vortex distribution characteristics of augmented/ramjet burner,the main section parameters of Turbine Based Combined Cycle（TBCC） enginewere obtained by 0-dimension numerical computation program.The flow and combustion state of the turbine/ramjet combined engine at close augmented burner mode,open augmented burner mode,mode transition and ramjet mode were simulated based on Computational Fluid Dynamics（CFD） simulation method.The influences of single-ring and double-ring flameholder on the length of augmented /ramjet burner were analyzed.The contrast result show that the exit total temperature of burner with double-ring flameholder was higher than that with single-ring flameholder at the same length.

关 键 词：加力 冲压燃烧室 涡轮冲压组合发动机 流动 燃烧 计算流体力学 数值模拟 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]