液体推进剂对ATR发动机性能影响的研究  

Effects Research of Different Liquid Propellant on Air-Turbo-Rocket Engine Performance

作　　者：屠秋野[1] 丁洁[1] 李成[1] 陈玉春[1] 

机构地区：[1]西北工业大学 动力与能源学院,西安710072

出　　处：《航空工程进展》2012年第3期332-337,共6页Advances in Aeronautical Science and Engineering

摘　　要：为了研究液体推进剂对ATR发动机的燃烧室进口油气比、排气温度、比冲等重要性能参数的影响,针对两套不同的ATR发动机热力循环参数,选择目前国内常用的液体推进剂作为燃料,对上述参数进行了数值模拟。计算结果与理论分析表明:做功能力强的推进剂有利于减小燃烧室进口的油气比,提高ATR发动机比冲;选择合适的推进剂与ATR发动机设计参数相匹配有利于提高二次燃温,进而从油气比和排气温度两个方面改善二次燃烧性能,提高ATR发动机比冲;即使在设计状态推进剂与设计参数两者之间做到了很好的匹配,但是在非设计状态,由于油气比的变化仍然表现出推进剂与工作参数的失配性。The effects of different liquid propellant on the propellant/air ratio at burner inlet, exhausted tempera- ture and （specific impluse） Isp of Air-Turbo-Rocket（ATR） engine at the conditions of two different thermody- namic cycles are researched by numerical simulations. Calculating results show that high working capability of the propellant in turbine can reduce the propellant/air ratio at burner inlet and increase the Isp of ATR engine. It also shows that proper propellant matching to the thermodynamic cycle parameters can increase the exhausted temperature and Isp greatly. Although the propellant matched to design parameters perfectly at design point, mismatch would still arise due to the change of propellant/air ratio at off-design conditions.

关 键 词：ATR发动机 液体推进剂 比冲 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]