针对未来高推重比航空发动机加力燃烧室的设计需求,提出了一种与涡轮后框架一体化的加力燃烧室方案,并用商业数值计算软件对其进行了三维冷态和热态流场数值模拟研究。结果表明,该方案利用涡轮整流支板及壁式稳定器,能够较好地组织加力燃烧室内的燃烧,出口截面温度分布均匀,综合性能良好。 Aiming at the design requirements of the afterburner with high thrust and heavy aerogels in the future, a new type of afterburner with integrated rear turbine frame is proposed. The commercial numerical software is used to calculate the three-dimensional cold and hot flow fields Simulation study. The results show that the scheme can make the combustion in the afterburner be well organized by using the turbine rectification support and the wall stabilizer. The outlet section temperature distribution is even and the comprehensive performance is good.