CAJ | 학술논문

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。
위료연구액체추진제대ATR발동궤적연소실진구유기비、배기온도、비충등중요성능삼수적영향，침대량투불동적ATR발동궤열력순배삼수，선택목전국내상용적액체추진제작위연료，대상술삼수진행료수치모의。계산결과여이론분석표명：주공능력강적추진제유리우감소연소실진구적유기비，제고ATR발동궤비충；선택합괄적추진제여ATR발동궤설계삼수상필배유리우제고이차연온，진이종유기비화배기온도량개방면개선이차연소성능，제고ATR발동궤비충；즉사재설계상태추진제여설계삼수량자지간주도료흔호적필배，단시재비설계상태，유우유기비적변화잉연표현출추진제여공작삼수적실배성。
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.