亚燃模态下释热分布对发动机性能的影响  

Effects of Heat Release Distribution on Scramjet Performance under Ramjet Mode Conditions

作　　者：肖保国[1] 田野[1] 张顺平[1] 邢建文[1] 

机构地区：[1]中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室,四川绵阳621000

出　　处：《推进技术》2016年第11期2017-2022,共6页Journal of Propulsion Technology

基　　金：国家自然科学基金(51376193;91441204)

摘　　要：为揭示释热分布对亚燃模态下超燃发动机性能的影响规律,对马赫数2.0,总温1100K,总压1.0MPa的来流,完成了燃烧室直连式实验和数值模拟研究。针对上游释热和下游释热条件,对比了发动机壁面压力分布,分析了内流道一维质量加权马赫数,获得了发动机部件和总体性能数据。结果表明,在总当量比相同情况下,上游释热能够获得更好的发动机性能,没有尾喷管时比下游释热获得的推力高出约18%,但在有尾喷管时只相差2.6%;对于本文构型,燃烧室和尾喷管是发动机推力的主要来源,两种释热分布下,二者产生的推力超过了发动机总推力的90%;但对于更高总当量比,上游释热可能会导致进气道不启动,需要增加下游释热获得更高的发动机性能。In order to find the influence law of heat release distribution on scramjet performance under ramjet mode conditions,a direct-connect combustor experiment and numerical simulation were carried out at the inflow Mach number 2.0,stagnation temperature 1100 K and stagnation pressure 1.0MPa. Wall-pressure distribution and 1-D mass weighted Mach number were compared and analyzed for upstream heat release and downstream heat release. Performance parameters of scramjet component and overall scramjet were also achieved. Results show that better thrust performance was obtained in upstream heat release mode for the constant total equivalence ratio. Upstream heat release mode show 18% higher in thrust of scramjet without the nozzle than that of downstream heat release mode. However,there was only 2.6% difference of thrust when the scramjet has the nozzle.The combustor and nozzle were the primary component that are used to produce the thrust,which was more than90% of the total thrust of overall scramjet for the two heat release modes. As the total equivalence ratio increases,the inlet unstart may be occurred under the upstream heat release mode. Therefore,the downstream heat release mode should be adopted to produce better thrust performance of scramjet.

关 键 词：超燃发动机 释热分布 亚燃模态 实验 数值模拟 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程]