| 摘要: |
| 全流量补燃循环发动机性能高，并具备便于重复使用的优势，是未来重复使用运载器的最佳选择之一。在液体火箭发动机启动过程中，泵入口推进剂的压力和温度变化会对全流量补燃循环发动机动力系统的启动特性造成一定的影响。为分析其影响规律，建立了涡轮泵、预燃室、推力室、两相流和混合气体组件等动力学模型并进行求解。结果表明，随着燃料泵入口压力升高或氧化剂泵入口压力降低，涡轮泵系统参数的波动将会逐渐增大，甲烷温度和液氧温度所产生的影响要强于甲烷压力和液氧压力，而液氧的影响则强于甲烷。为动力系统中泵入口推进剂状态参数控制提供了一定的指导。 |
| 关键词: 火箭发动机 启动特性 敏感度 泵入口压力 |
| DOI： |
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| 基金项目:民用航天预先研究项目（D020101） |
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| Research on the Influence of Pump Inlet Parameters on the Dynamic Characteristics of the Full-Flow Staged Combustion Cycle Engine |
| WANG Jue,ZHOU Chuang,ZHU Pingping,YU Nanjia,CAI Guobiao |
| (China Academy of Launch Vehicle Technology, Beijing 100076, China;1.Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China;2. School of Astronautics, Beihang University, Beijing 102206, China) |
| Abstract: |
| The full-flow staged combustion cycle engine is one of the best choices for the future reusable launch vehicles because of its high performance and the advantage of easy reuse. During the startup process of a liquid rocket engine, the pressure and temperature changes of the pump inlet propellant will have a certain influence on the startup characteristics of the full-flow staged combustion cycle engine system. In order to analyze the influence law, dynamic models of the turbopump, preburner, thrust chamber, two-phase flow and mixed gas components are established and solved. The fluctuation of the turbopump system parameters will gradually increase as the inlet pressure of the fuel pump increases or the inlet pressure of the oxidizer pump decreases. The sensitivity of the combustion chamber pressure overshoot to the propellant pressure and temperature is higher than the combustion chamber pressure build-up time Combining the parameters, the temperature of the methane and the liquid oxygen produce a stronger effect than the pressure of the methane and the liquid oxygen, and the liquid oxygen has a stronger effect than the methane. This study provides some guidance for the control of pump inlet propellant state parameters in propulsion systems. |
| Key words: Rocket engine Startup characteristics Sensitivity Pump inlet pressure |