【摘要】 第三代猛禽发动机是美国太空探索技术公司最新、最先进版本的液体火箭发动机。它在推力、比冲、推重比等核心指标取得了长足进步，而其生产成本却实现了大幅下降。通过分析，第三代猛禽发动机进行了巨大改进，其主要创新在于内化流道设计、取消外部隔热罩、采用先进材料提高结构强度等。针对世界首型经过飞行试验的全流量补燃循环方式发动机，利用系统动态特性仿真平台分析了系统起动工作特性，发现在预燃室点火后，双预燃室的压力均会迅速升高，涡轮压比降低，涡轮输出功率下降，从而使得双泵的出口压力和转速存在下降的过程。在燃烧室点火后，燃料涡轮和氧化剂涡轮的压比变化不同，从而使混合比发生偏离。本研究深化了对全流量补燃循环方式发动机的认识。更多还原

【Abstract】 The third-generation Raptor engine is the latest and most advanced version of liquid rocket engine developed by SpaceX. It has made significant progress in core metrics such as thrust, specific impulse, and thrust-to-weight ratio, while simultaneously achieving a substantial reduction in production costs. Through analysis, it is evident that the third-generation Raptor engine has made substantial improvements. Its primary innovations include internalized flow path design, elimination of the external thermal shield, and the use of advanced materials to enhance structural strength. For the first full-flow staged combustion cycle engine to undergo flight testing, the start-up characteristics were analyzed using a system dynamic characteristic simulation platform. It was found that after ignition in the preburner, the pressure in both preburners would rapidly increase, causing a decrease in turbine pressure ratio and a reduction in turbine output power, which in turn led to a drop in the outlet pressure and speed of both pumps. After ignition in the combustion chamber, the pressure ratio changes in the fuel turbine and oxidizer turbine were different, leading to a deviation in the mixture ratio. This study has promoted a deeper understanding of full-flow staged combustion cycle engines.更多还原