加力燃烧室双层喷油杆内冷却气流动特性  

Cooling air flow performance of an afterburner fuel injector with double-wall construction

作　　者：闫宝华[1] 樊未军[1] 杨茂林[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083

出　　处：《航空动力学报》2008年第7期1182-1188,共7页Journal of Aerospace Power

摘　　要：对新型外涵引气冷却双层壁加力喷油杆的冷气流动特性进行了模拟实验,为双层喷油杆结构设计和冷却性能研究提供基础.通过对8套不同结构尺寸实验件的研究,得到了双层喷油杆冷却套管内气流流阻系数随来流质量流量的变化规律、流阻系数随双层喷油杆结构尺寸的变化规律和冷却套内气流雷诺数随进口总压的变化规律等.对8套实验件结果进行比较,综合三个因素最终选择了较为合理的新型双层喷油杆结构尺寸.这种尺寸的喷油杆流阻系数为1.2,迎风尺寸宽16 mm较为合适,相同工况下冷却气的雷诺数最大.The performance of cooling air flow extracted from the fan stream to a new type fuel injector with double-wall construction for afterburner was simulated experimentally, so as to provide a basis for design and cooling performance research of advanced fuel in- jector. The effects of mass flux and fuel injector structure on pressure coefficient were studied through experiments of eight cooling casings of fuel injector. The effects of inlet total pressure on Reynolds number of the flow in cooling casing were also obtained. An optimum, new fuel iniector was selected by comparing the results of eight casings of fuel injector. The pressure coefficient of such fuel injector is 1.2, the appropriate width is 16 mm, and the Reynolds number in the same inlet conditions is the biggest.

关 键 词：加力燃烧室 外涵引气 喷油杆流阻系数 

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]