某型航空发动机火焰筒流量对比试验研究  

Comparative Experiment Study of Flame Tube Flow for an Aeroengine

作　　者：郭强[1] 陈代富[1] 贺孝涛[1] 

机构地区：[1]海军装备部,西安710054

出　　处：《航空发动机》2013年第3期77-80,共4页Aeroengine

摘　　要：针对某型发动机在研制过程中频繁发生单位燃油消耗率(SFC)过高的故障,在自行设计的航空发动机燃烧室火焰筒流量测试试验器上,运用模拟压比和模拟马赫数准则,采用冷吹风流量试验法,对比测试了某型发动机燃烧室与原型燃烧室火焰筒空气的流量,并对测试数据进行分析。试验结果表明:发动机燃烧室火焰筒流量分布均匀,与原型燃烧室火焰筒流量相同。该试验法耗时短、成本低,对开展燃烧室火焰筒内空气流量研究具有借鉴意义。The air flow test device self-designed on the flame tube of aeroengine combustion chambers was introduced.The comparison test of the flame tube flow of aeroengine combustion chambers with prototype aeroengine was conducted by the cold blowing flow experiment method,the simulation pressure ratio and Mach number criterion,and the test data were analyzed.The test result show that the flame tube flow of aeroengine combustion chambers was uniform and relative with prototype flame tube,which is not the main reason leading to high specific fuel consumption（SFC）.The test method of short-time consuming and low cost provid significance to study the air flow of combustion chamber flame tube.

关 键 词：燃烧室 火焰筒 流量 燃油消耗率 航空发动机 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]