摘要
为某微型涡喷发动机设计了一个蒸发管环形燃烧室.根据发动机对燃烧室的性能要求,设计了燃烧室的主要部件,对燃烧室的流量分配及流程参数进行了数值计算.参照发动机的总体结构,设计了燃烧室的试验器,对燃烧室进行了一定的性能试验.结果表明,所设计的燃烧室在结构方案、主要部件和总体性能方面基本满足设计要求.
An annular combustor with evaporation tubes was designed for certain microturbojet engine. According to performance requirements of the engine, designed main components of the combustor, calculated flow distribution and flowage parameters of the combustor. Refers to overall structure of the engine, designed test apparatus of the combustor and carried out the several performance experiments. The results show that the designed combustor meets the demand for structural project, main components and overall performance.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第1期70-74,共5页
Journal of Aerospace Power
基金
西北工业大学科技创新基金(2003CR070001)
关键词
微型涡喷发动机
燃烧室
蒸发管
主要部件
数值计算
性能试验
micro-turbojet engine
numerical calculation
combustor
evaporation tube
main component
performance experiment
