摘要
对不同航空发动机燃烧室主燃区出口特征下的速度分布和温度分布进行模拟,获得了不同主燃区出口特征下的出口温度场。结果表明:在均匀的主燃区出口速度分布下,燃烧室出口温度场更均匀;主燃区出口最高温度突升及温升幅度对出口温度分布系数To和径向温度分布系数Tr的影响很小;主燃区最高温度点向内、外涵靠近时,To和Tr都会迅速增大,靠近外涵时比靠近内涵时增大得快。
The velocity and temperature distribution was simulated at different aeroengine combustor primary zone outlet feature, and the combustor outlet temperature field was obtained at corresponding primary zone outlet feature. The reuhs show that the combustor outlet temperature field is more uniform at uniform velocity distribution of the primary zone outlet. The jump and rise extent of the highest temperature on the primary zone outlet have little effect on To and Tr. Both To and Tr increase rapidly when the highest temperature point of the primary zone outlet moves to the outer annulus or the inner annulus, To and Tr increase is faster when the highest temperature point of the primary zone outlet moves to the outer annulus.
出处
《航空发动机》
2012年第4期17-21,共5页
Aeroengine
关键词
高推重比燃烧室
主燃区出口特征
数值模拟
航空发动机
出口温度场
high thrust-weight ratio combustor
primary zone outlet feature
numerical simulation
aeroengine
outlet temperature field
