微型涡喷发动机燃烧室数值模拟  

Numerical simulation of annular combustion chamber for micro-turbine engine

作　　者：李聪[1] 方蜀州[1] 张平[1] 

机构地区：[1]北京理工大学宇航科学与技术学院,北京100081

出　　处：《推进技术》2008年第5期513-518,共6页Journal of Propulsion Technology

摘　　要：微型涡轮喷气发动机(Micro-turbine engine)燃烧室具有传热损失大及燃烧驻留时间短的特点。为了给微型燃烧室定型提供数据参考,对设计的微型环形燃烧室中的稳态燃烧过程进行数值模拟。计算入口边界参数采用等熵数值计算结果,喷雾性能参数通过试验获得,考虑了湍流化学反应、热辐射、液滴的蒸发及二次雾化等情况,得到燃烧室稳态工作时的速度场、温度场及浓度分布,计算结果可以较为准确地反映燃烧室的实际燃烧情况。计算结果表明,燃烧室设计合理,燃料可以充分燃烧,各项性能参数基本符合设计要求,能够为燃烧室的进一步优化设计提供改进依据。The combustion chamber of micro-tubine engine has some characters, such as higher heat losses, shortened residence time of reaction. The process of steady combustion in a micro annular combustor was simulated. The boundary condition of inlet was gained through computing and the parameter of spray was obtained through experiment. Chemical reaction, heat radiation,evaporating of fuel and secondary breakup of spray were considered in numerical simulation. It indicates the design is reasonable, fuel can combusted sufficiently in the chamber and the performance parameter is satisfied with the design requirement. All data can provide numerical foundation for optimizing combustion chamber.

关 键 词：微型燃气涡轮发动机 燃烧室 数值仿真 燃烧 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]