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公开(公告)号：JPH0196452A
公开(公告)日：1989-04-14
申请号：JP25222187
申请日：1987-10-06
Applicant: NAT AEROSPACE LAB
Inventor： KARITA TAKESHI , WAKAMATSU YOSHIO , KAN AKIO
IPC: F02K9/48
Abstract: PURPOSE:To improve specific propulsion of propellant and to improve engine performance by arranging a heatexchanger in a propellant flow path for pressure feeding propellant into a combustion chamber and improving enthalpy of propellant and feeding propellant into the combustion chamber. CONSTITUTION:Propellant A is pressure fed through a pump 1 which is driven by a turbine 3 and cools a rocket nozzle 2, then drives the turbine 3 and fed into a combuster 5. Propellant B is simultaneously pressure fed into the combustion chamber 5 through a pump 4 which is driven by same turbine 3 so as to burn the propellant A. Propellant A fed through the pump 1 passes through a heatexchanger 6 arranged in the way where it is heated then fed to the cooling circuit of the nozzle 2. Consequently, enthalpy of propellant is improved so as to improve specific propulsion of the propellant thus improving the engine performance.
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公开(公告)号：JPH07243350A
公开(公告)日：1995-09-19
申请号：JP5256994
申请日：1994-02-28
Applicant: NAT AEROSPACE LAB
Inventor： KAN AKIO , KATOU SHIYUUTOKU , WAKAMATSU YOSHIO , KARITA TAKESHI
Abstract: PURPOSE:To enable both increase in large propulsion force required at launching and specific impulse after rising despite of one engine without changing nozzles and propellants. CONSTITUTION:A combined cycle rocket engine is provided with a circuit for supplying liquid oxygen LOX and liquid hydrogen LH to a main combustion chamber 9 of an engine by a pump 12, a circuit for supplying a part of these propellants to a gas generator 13 for driving a turbine and discharging gas from an auxiliary nozzle 10 after driving the turbine 11 by generation gas, and a circuit for supplying liquid hydrogen which is vaporized after fed to the main combustion chamber and the nozzle by the pump for cooling so as to drive the turbine, to the main combustion chamber. Gas generator cycle and expander cycle are thus changed by valves 1-8 provided in respective circuits so that at first when it is launched, the gas generator cycle is used and after rising, the expander cycle is used.
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公开(公告)号：JPH01164700A
公开(公告)日：1989-06-28
申请号：JP32359787
申请日：1987-12-21
Applicant: NAT AEROSPACE LAB
Inventor： KARITA TAKESHI , KAN AKIO , WAKAMATSU YOSHIO
Abstract: PURPOSE: To improve efficiency by cooling an airframe with a propellant, and spouting the heated propellant after this heat exchange from a nozzle in a missile exposed to a high temperature by aerodynamic heating, etc. CONSTITUTION: The hydrogen fed from a liquid hydrogen tank 2 provided in an airframe 1 exposed to a high temperature is boosted by a pump 3, then it is used for the heat exchange (cooling) with the airframe 1 by a heat exchanger 4. The heat-exchanged hydrogen drives a turbine 6' with its whole quantity, for example, then the hydrogen is exhausted through a nozzle 5. Power is obtained by a large turbine flow in this cycle, the hydrogen temperature at a turbine outlet is relatively high in a range that the pressure ratio required for the turbine 6' is near 1, and a high specific impulse can be expected.
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公开(公告)号：JPS58108399A
公开(公告)日：1983-06-28
申请号：JP20651181
申请日：1981-12-21
Applicant: NAT AEROSPACE LAB
Inventor： WAKAMATSU YOSHIO , TSUGI KIYOUICHIROU , KAN AKIO
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