新型纽扣式涡喷发动机燃烧室数值模拟  

Simulation Calculation of Combustion Chamber for Button Turbojet Engine

作　　者：马红鹏[1] 方蜀州[1] 高航[1] 李腾[1] 方冠林 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《北京理工大学学报》2017年第4期354-359,共6页Transactions of Beijing Institute of Technology

基　　金："十一五"民用航天科研预研项目(C2220062202)

摘　　要：为了给超微型燃烧室提供数据参考,对设计的某微型燃烧室的稳态燃烧过程进行数值模拟.采用三维建模,入口参数采用等熵数值计算,考虑了湍流化学反应、热辐射等情况,不仅得到燃烧室稳态工作时的速度场、温度场及各组分浓度分布,而且分析了燃料/空气的流动与回流、燃烧效率以及总压恢复系数的情况,并与实验数据进行对比.计算结果可以较为准确地反映燃烧室的实际燃烧情况.结果表明,燃烧室出口速度约为65m/s,出口温度约1 000K,仿真与实验数据契合度高,燃烧室结构设计合理.To provide reference data for ultra-micro combustor, a new type button turbojet engine was designed and simulated in the combustion＇s steady-state process. The boundary condition of inlet was calculated with isentropic numerical calculation taking into account turbulent chemical reaction, heat radiation, and so on, to get the combustion chamber＇s steady-state of the velocity, temperature and component concentration distribution, to analyze the fuel/air flow and backflow, combustion efficiency and total pressure recovery coefficient, and to compare with the experimental data. The calculation results can accurately reflect the actual combustion. The results show that, when combustion chamber exit velocity is about 65 m/s, outlet temperature is around 1 000 K, the simulation and experimental data are more similar, combustion chamber structure design is reasonable.

关 键 词：微型涡喷发动机 燃烧室 稳态燃烧 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]