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CN104919167A 火箭发动机、火箭及火箭发动机的启动方法 无效 - 撤回

火箭发动机、火箭及火箭发动机的启动方法
摘要：
一种火箭发动机、火箭及火箭发动机的启动方法。火箭发动机具备：燃料流路(31～39)、触媒部(51)、涡轮机(12)、第1泵(11)、燃烧室(21)和喷嘴(22)。燃料流路(31～39)用于烃类的燃料流通。触媒部(51)设于燃料流路(31～39)的途中，用于使燃料气化。涡轮机(12)由被气化的燃料驱动。第1泵(11)利用涡轮机(12)的驱动向燃料流路(31～39)供给燃料。燃烧室(21)使从燃料流路(31～39)供给的被气化的燃料和氧化剂燃烧。喷嘴(22)将燃烧室(21)的燃烧气体送出，并与燃料流路(31～39)的一部分进行热交换来进行冷却。
摘要（英）：

A rocket engine is provided with a fuel flow path (31-39), a catalyst part (51), a turbine (12), a first pump (11), a combustion chamber (21), and a nozzle (22). Hydrocarbon-based fuel flows through the fuel flow path (31-39). The catalyst part (51) is provided in the middle of the fuel flow path (31-39), and gasifies the fuel. The turbine (12) is driven by the gasified fuel. The first pump (11) supplies the fuel to the fuel flow path (31-39) by the driving of the turbine (12). The combustion chamber (21) burns the gasified fuel supplied from the fuel flow path (31-39), and an oxidizing agent. The nozzle (22) delivers combustion gas in the combustion chamber (21) and is cooled by heat exchange with part of the fuel flow path (31-39).

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