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为了提高超紧凑型涡轮级间燃烧室在航空发动机的应用范围,文中在常规超紧凑燃烧室上引入驻涡燃烧,提出了一种双凹腔燃烧室。利用CFD技术对双凹腔燃烧室的三维两相流场和燃烧进行了数值模拟。结果表明:总压损失低至2.81%,燃烧室效率高达99.7%,气体温度提高685.7 K;出口径向温度随无量纲高度呈线性分布。与常规超紧凑燃烧室相比,双凹腔驻涡燃烧室具有更高的燃烧效率、出口温度和更低的总压损失。
In order to improve the application scope of the ultracompact turbine intercooler in aeroengine, a dual-cavity combustor is proposed in this paper. The CFD technique was used to simulate the three-dimensional two-phase flow field and combustion in a dual-cavity combustor. The results show that the total pressure loss is as low as 2.81%, the efficiency of the combustion chamber is as high as 99.7% and the gas temperature is increased by 685.7 K. The outlet radial temperature is linear with the dimensionless height. The dual-cavity trapped vortex combustor has higher combustion efficiency, exit temperature, and lower total pressure loss than conventional ultra-compact combustion chambers.