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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 distribution and temperature distribution under the outlet characteristics of the main combustion zone of different aeroengines were simulated and the outlet temperature field under the outlet characteristics of different main combustion zones was obtained. The results show that the outlet temperature distribution of the combustion chamber is more uniform under the uniform outlet velocity distribution of the main combustion zone. The effect of the maximum temperature rise and temperature increase of the outlet of the main combustion zone on the outlet temperature distribution coefficient To and the radial temperature distribution coefficient Tr Small; the maximum temperature of the main combustion zone inward, the outer culvert near, To and Tr will rapidly increase, approaching the connotation when the increase faster than the connotation.