组合动力用过氧化氢煤油推力室热防护方案设计方法  

Design Methodology for Thermal Protection of Hydrogen Peroxide and Kerosene Thrust Chamber Used by Combined Cycle Engine

作　　者：韩兆鹏 郭晟 刘亚冰[1] 侯金丽 韦宝禧[1] 冮强[1] HAN Zhao-peng;GUO Sheng;LIU Ya-bing;HOU Jin-li;WEI Bao-xi;GANG Qiang(Science and Technology on Scramjet Laboratory,Beijing Power Machinery Institute,Beijing 100074,China)

机构地区：[1]北京动力机械研究所高超声速冲压发动机技术重点实验室,北京100074

出　　处：《推进技术》2021年第10期2267-2276,共10页Journal of Propulsion Technology

摘　　要：为满足组合动力对过氧化氢煤油推力室的方案设计需求,建立工程计算方法,可快速进行热防护方案设计。通过修正燃气对流换热系数和引入液膜分解率完善工程算法,使工程计算结果与三维流固热耦合计算结果和实际试验结果符合较好。在此基础上,对组合动力用推力室进行热防护方案设计,结果表明:采用头部过氧化氢液膜和身部过氧化氢再生的方式可实现可靠热防护,其中,液膜流量在氧化剂中占比为30%。采用上述研究思路具备开展快速方案论证的能力,可在众多方案中选出热防护性能较优的方案。An engineering calculating method was built to fulfill the requirement of thermal protection design on a hydrogen peroxide and kerosene biopropellant thrust chamber embeded in rocket combined cycle engine.By modifying the convection heat transfer coefficient of burned gas and introducing the liquid film decomposition rate of coolant,the results match well with those of experiment and three dimensional coupled numerical simulation.Then,applied in the thermal protection of a thruster assembled in combined cycle engine,the result indicates that the cooling design is proved practicable,with liquid film cooling in the head and regenerative cooling in the body.The coolant is selected as hydrogen peroxide and the consumption of liquid film cooling makes up about 30%.The method manages to evaluate the performance of thermal protection conveniently,and contribute to the assessment of the overall performance.

关 键 词：组合动力 过氧化氢 推力室 工程算法 热防护 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]