内燃波转子燃料填充方案研究  

Investigation on Fuel Injection Strategies of Wave Rotor Combustor

作　　者：李建中[1] 巩二磊[1] 袁丽[2] 刘双丽[1] 刘博强[1] 

机构地区：[1]南京航空航天大学能源与动力学院,江苏省航空动力系统重点实验室,江苏南京210016 [2]中国人民解放军理工大学国防工程学院,江苏南京210007

出　　处：《推进技术》2016年第11期2120-2125,共6页Journal of Propulsion Technology

基　　金：国家自然科学基金(51476077);江苏省研究生培养创新工程(KYLX-0299)

摘　　要：为获得内燃波转子进气端口内可靠的燃料填充方案,研究混气形成规律,采用数值模拟与实验相结合的方法,从燃料分布不均匀度及涡轮径向温度分布要求方面考虑,比较了壁面单孔喷射、单孔逆喷、双孔逆喷以及多孔侧喷四种燃料喷注方案下混气的掺混情况。研究结果表明,单孔逆喷方案实现了与典型涡轮进口温度要求一致的燃料分布,且燃料分布不均匀度适中,距进口150mm以后混气分布不均匀度趋于恒定,确定为最佳方案;主流与喷孔射流以燃料进口压力等于0.3MPa为界,分别主导混气的掺混。In order to acquire the authentic fuel-filling scheme of wave rotor combustor, and study the mixed gas formation principles,with experiments and numerical simulation,the mixing results of four fuel injection strategies which include single hole on the wall,single-hole inverse injection,double-holes inverse injection and multi-holes tangential injection,were compared from fuel distribution unevenness and the turbine radial temperature distribution aspects. The results show that,the single-hole reverse injection scheme was identified as the best strategy for achieving the fuel distribution. It is consistent with the typical turbine inlet temperature and appropriate fuel distribution unevenness. It tends to be constant backwards the position of 150 mm away from the inlet. The mainstream and jet flow respectively dominant the mixing with taking the fuel inlet pressure of0.3MPa as the dividing line.

关 键 词：波转子 内燃波转子 燃料填充 喷注方案 掺混 

分 类 号：V235.1[航空宇航科学与技术—航空宇航推进理论与工程]