Provides a pure liquid oxygen engine, from a liquid oxygen tank 1, a heat exchanger 2, a heater 3, the pressure of the buffer tank 4, oxygen flow regulator 5, aero engine 6 and a connecting pipeline, the aero engine air inlet and oxygen flow regulator of oxygen outlet connection pipe 7, an oxygen outlet pressure of the buffer tank and the oxygen flow regulator of oxygen inlet connection pipe 8, aeroengine exhausts outlet and heating gas inlet connecting pipe heater 9, oxygen outlet pressure of the buffer tank and the oxygen inlet connection 10, after the tail gas outlet vent pipe heater 11, aviation engine radiator cooling medium outlet and heat exchanger heating carrier inlet connecting pipe 12, heat exchanger heating carrier outlet and cooling medium engine radiator inlet connection pipe 13, heat exchanger and oxygen outlet heater oxygen inlet connection pipe 14, a liquid oxygen tank of oxygen Inlet oxygen inlet of heat exchanger and pipe 15. The utility model has the advantages of saving energy by 80% and reducing emission by 95%.
【技术实现步骤摘要】
【技术保护点】
１．一种纯液氧航空发动机，其特征是：由液氧罐（１），换热器（２），加热器（３），压力缓冲罐（４），氧气流量调控器（５），航空发动机（６）和连接管道组成，其中航空发动机空气进口与氧气流量调控器氧气出口连接管（７），压力缓冲罐氧气出口与氧气流量调控器氧气进口连接管（８），航空发动机尾气出口与加热器加热气体进口连接管（９），加热器氧气出口与压力缓冲罐氧气进口连接管（１０），经过加热器的尾气出口放空管（１１），航空发动机散热器冷却介质出口与换热器加热载体进口连接管（１２），换热器加热载体出口与航空发动机冷却介质进口连接管（１３），换热器氧气出口与加热器氧气进口连接管（１４），液氧罐氧气出口与换热器氧气进口连接管（１５）。
【技术特征摘要】
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