外涵引气加力喷油杆冷却特性模拟实验  

Experimental research on the cooling characteristics of an afterburner fuel injector with double-wall construction

作　　者：闫宝华[1] 樊未军[1] 李瑞明[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,北京100191

出　　处：《航空动力学报》2008年第10期1788-1794,共7页Journal of Aerospace Power

摘　　要：根据实际需要,提出了新型外涵引气双层壁喷油杆的结构方案.共设计了不同结构尺寸的8种新型双层喷油杆冷却套,在流动特性研究的基础上进一步对其换热特性和高温工况下流动性能进行了对比实验.综合其引气和冷却性能,对比八种尺寸套管,选取了较为合适的冷却套管结构尺寸.并对这种尺寸的套管进行了油杆内壁温度沿杆高的变化、油杆内壁温度随冷却气总压的变化及油杆内壁温度随套管进口雷诺数的变化的研究.实验表明:可以有效从外涵引气(压差850 Pa时,引气量9 g/s),能够较大降低油杆内壁温度(冷却效率0.7以上).A new afterburner fuel injector with double-wall construction was presented to meet the actual requirements. 8 test pieces of new fuel injector casings with different sizes were designed in this research. The heat transfer characteristics and cooling air flow per- formance were tested based on previous flow characteristics research. In view of the air extraction and cooling performance, an optimum cooling case was selected. Then, this casing of fuel injector was researched with respect to the distribution of injector temperature, change of injector temperature with cooling flow inlet total pressure and change of injector temperature with Re of cooling flow inlet. The results show that： this new afterburner fuel injector can extract enough cooling air from the fan stream（When Δp is 850 Pa, extracted air flow flux is 9 g/s） and decrease effectively the temperature of the wall of fuel injector（cooling efficiency is not less than 0.7）.

关 键 词：加力燃烧室 喷油杆 气冷 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]