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1. 发明专利

JP2002317700A THRUSTER DEVICE 失效
公开(公告)号：JP2002317700A
公开(公告)日：2002-10-31
申请号：JP2001125947
申请日：2001-04-24
申请人： NAT SPACE DEV AGENCY , MITSUBISHI HEAVY IND LTD
发明人： KOBAYASHI YOSHITAKA , MIKI YOICHIRO
IPC分类号： B64G1/26 , F02K9/60
摘要： PROBLEM TO BE SOLVED: To provide a thruster device capable of suppressing cost increase by suppressing the number of part items and establishing a stable combustion at all times. SOLUTION: The thruster device 1 includes a body 2, thrust force changing member 3, nozzle 4, fuel supplying means 5, and an oxidator supplying means 6. The device body 2 constitutes the contour of the device 1, while the thrust force changing member 3 is supported rotatably inside the device body 2, and the nozzle 4 is connected with the device body 2. The fuel supplying means 5 is furnished with a fuel manifold 21 and a fuel injection nozzle 22 which opens at the manifold 21 and inside the nozzle 4, while the oxidator supplying means 6 is furnished with an oxidator manifold 31 and an oxidator injection nozzle 32 which is open at the manifold 31 and inside the nozzle 4. The fuel injection nozzle 22 and oxidator injection nozzle 32 are furnished with major diametric nozzles 25 and 35 having a comparatively large flow section area and minor diametric nozzles 26 and 36 having a relatively small flow section area, respectively.

2. 发明专利

JPH0734969A SCRAM RACE COMPOUND ENGINE 失效
公开(公告)号：JPH0734969A
公开(公告)日：1995-02-03
申请号：JP17420893
申请日：1993-07-14
申请人： NAT AEROSPACE LAB , MITSUBISHI HEAVY IND LTD
发明人： EGUCHI KUNIHISA , TOGAWA MORIHITO , MIKI YOICHIRO
IPC分类号： F02K7/14 , F02K7/18
摘要： PURPOSE:To reduce the number of kinds and the weight of engines by a method wherein an air liquefied rocket engine (LACE) and a scram jet engine, which are shared with specified regions different from each other, are disposed and the LACE is used for both two functions of an air suction type engine and a rocket engine. CONSTITUTION:A compound engine is used in a propulsion device for a single stage type space shuttle to take off and return between a ground and a space. In this case, an LACE 10 to be shared with a speed region of approximate mach 4 - mach 20 or more and an SCRAM(supersonic combustion RAM) jet engine 11 shared with a speed region in a range of approximate mach 4 - mach 25 are disposed. When speed exceeds mach 5, a hydrogen valve 8 on the LACE 10 side is closed and a hydrogen valve 7 on the engine 11 side is opened for acceleration. Thereafter, when a speed exceeds mach 20 and altitude exceeds 50km, the hydrogen valve 8 and an oxygen valve 9 on the LACE 10 side are opened and the LACE 10 is worked as a rocket engine.

3. 发明专利

JPH1054302A ROCKET ENGINE 失效
公开(公告)号：JPH1054302A
公开(公告)日：1998-02-24
申请号：JP21365096
申请日：1996-08-13
申请人： MITSUBISHI HEAVY IND LTD
发明人： TOGAWA MORIHITO , MIKI YOICHIRO
IPC分类号： B64G1/26 , F02K9/62 , F02K9/88
摘要： PROBLEM TO BE SOLVED: To provide a device excellent in durability and heat resistance while improving oxidation resistance of Nb. SOLUTION: A combustion chamber, adopting a radiation cooling system to generate a surface temperature at a high temperature, is formed by the following layer. In a strength layer 6, Nb is laminated in about 1000μm by a CVD method. In an intermediate layer 7, Nb and iridium Ir, by the CVD method, are alternately laminated by each several μm in an internal/external peripheral surface of the strength layer, Nb and Ir layers are provided by two layers or more. Further, in a skin layer 8, Ir, by the CVD method, is laminated by about 50μm in an internal/external peripheral surface of the intermediate layer.

4. 发明专利

JPH09151799A HEAT RESISTANCE STRUCTURE 失效
公开(公告)号：JPH09151799A
公开(公告)日：1997-06-10
申请号：JP31070995
申请日：1995-11-29
申请人： NAT AEROSPACE LAB , MITSUBISHI HEAVY IND LTD
发明人： KUMAKAWA AKINAGA , MIKI YOICHIRO , TAGUCHI HIDEYUKI
IPC分类号： F02K9/62 , C23C18/16 , C23C18/52 , C23C30/00
摘要： PROBLEM TO BE SOLVED: To prevent generation of crack caused by heat stress by arranging an etching cut in at least the vicinity of a surface of a heat resistance member formed on a base material surface. SOLUTION: The inner surface of a combuster wall 1 made of nickel, copper, and the like of a combuster is covered with a dispersion plating layer 2, and multiple regular etching cuts (a pre-crack) 3 are arranged in a thickness direction which is led from the surface of the dispersion plating layer 2 to a surface which is brought in contact with a combustion wall 1. The dispersion plating layer 2 made of a material such as nickel-zirconia, the composition of metal (nickel and the like) and a non-metal (zirconia and the like) is inclined, and non metal having high heat resistance property is concentrated on the surface of the inner surface side (the opposite side of the combuster wall 1) of the dispersion plating layer 2 which is brought in contact with combustion gas.

5. 发明专利

JPH06330816A HIGH TEMPERATURE COMBUSTION ENGINE 失效
公开(公告)号：JPH06330816A
公开(公告)日：1994-11-29
申请号：JP11696193
申请日：1993-05-19
申请人： NAT AEROSPACE LAB , MITSUBISHI HEAVY IND LTD
发明人： SHINNO MASAYUKI , TOGAWA MORIHITO , MIKI YOICHIRO
IPC分类号： F02K9/64
摘要： PURPOSE:To provide a high temperature combustion engine of which pressure loss for the flow of cooling medium is small, heat resisting performance is heightened, and the combustion chamber having cooling passages therein is provided. CONSTITUTION:A plurality of cooling passages extending in the axial direction of a combustion chamber are formed in an inner cylinder 1 forming the combustion chamber C of a rocket engine. Fuel to be burned in the rocket engine is introduced to the cooling passages from an inlet piping 8, through an inlet manifold 3. The fuel flowing in the cooling passages flows out from an outlet piping 9 through an outlet manifold 4, and led to the rocket engine combustion chamber from the inlet of an injection device 10. Triangular fins are extendingly arranged along the passages in the cooling passages. Bubbles generated on the heat transfer surface of the cooling passage quickly break away by arranging the fins, so as to restrain film boiling on the heat transfer surface.

6. 发明专利

JPH09317559A COMBUSTOR FOR OXYGEN/METHANOL AND ITS STARTING METHOD 失效
公开(公告)号：JPH09317559A
公开(公告)日：1997-12-09
申请号：JP12993096
申请日：1996-05-24
申请人： MITSUBISHI HEAVY IND LTD
发明人： MATSUI ATSUSHI , MIKI YOICHIRO
IPC分类号： F02K9/52 , F02K9/88
摘要： PROBLEM TO BE SOLVED: To provide a device and a starting method capable of eliminating a conventional malfunction, propelling space apparatuses aimed at a long time mission, and being used for a power system in relation to a combustor of oxygen/methanol, which is used for a thrustor, etc., of space apparatuses, and its starting method. SOLUTION: A combustor comprises an ignitor part 1 which sets the mixing ration of oxygen/methanol to 0.1 to 0.4 to ignite the mixture to burn it, main oxygen nozzles 17 which are formed integrally with the ignitor part and arranged at equal pitches on two circumferences concentrically arranged and differed from each other in the length of diameter, and an injector part 15 permitting oxygen and methanol from circumferentially and diametrically adjacent two main oxygen nozzles and two main methanol nozzles out of the main oxygen nozzles and the main methanol nozzles 20 to collide with each other at one point in a combustion chamber 14 to burn at a finally set mixing ratio. Thus, burnung of an ignition device 10 does not occur, stable ignition and combustion at a low mixing ratio are performed, and methanol less apt to vaporize is efficiently evaporated to realize highly efficient, stable final (steady) combustion.

7. 发明专利

JPH09151798A INJECTOR OF ROCKET ENGINE 失效
公开(公告)号：JPH09151798A
公开(公告)日：1997-06-10
申请号：JP31070895
申请日：1995-11-29
申请人： NAT AEROSPACE LAB , MITSUBISHI HEAVY IND LTD
发明人： KUMAKAWA AKINAGA , MIKI YOICHIRO , TAGUCHI HIDEYUKI
IPC分类号： F02K9/52
摘要： PROBLEM TO BE SOLVED: To suitably hold flow rate ratios of gas fuel and a liquid oxidant by forming a part for forming the injection hole of an outer wall of shape memory alloy which is deformed so as to contract the injection hole at the time of high pressure combustion, in a device for injecting gas fuel from the circumference of liquid oxidant injected to a combustion chamber. SOLUTION: In the injector of a rocket engine, a circular cross sectional bulk head 4 is concentrically arranged in the outer wall 3 of a circular cross sectional injector, and liquid oxidant supplied in the bulk head 4 is injected into a combustion chamber. Gas fuel 1 supplied through a passage formed between the bulk head 4 and the outer wall 3 is injected from the circumference of the liquid oxidant 2. In this case, a part 3a for forming an injecting hole opened to the combustion chamber of the outer wall 3 of the injector is formed of shape memory alloy such as nickel, copper, and the like, and also it is formed in a bending shape so as to throttle a gas fuel passage at the time of a low temperature. In the case where a temperature is raised to a constant value or more, the injecting hole is deformed outward so as to enlarge the injection hole, and proper injection flow speed is held regardless of a temperature at all times.

8. 发明专利

JPH07299157A FLUID JETTING APPARATUS 失效
公开(公告)号：JPH07299157A
公开(公告)日：1995-11-14
申请号：JP9478994
申请日：1994-05-09
申请人： MITSUBISHI HEAVY IND LTD
发明人： TAGUCHI HIDEYUKI , MIKI YOICHIRO
IPC分类号： A62C35/58 , F02K99/00 , F22B1/18
摘要： PURPOSE:To provide a fluid jetting apparatus which can jet a flow of fluid with a large flow rate over a long arrival distance. CONSTITUTION:This apparatus is made up of a precombustion chamber 7 which performs a precombustion of a liquid hydrogen 17 as fuel and a liquid oxygen 16 as oxidizer to generate a hydrogen rich combustion gas 18, a rocket engine having a main combustion chamber 8 for burning the combustion gas 18, a turbo water pump 10 which is driven by the combustion gas 18 from the precombustion chamber 7, a heat exchanger 11 to heat a high pressure water 19 from the turbo water pump 10 by the combustion gas 18 and a water manifold 12 which jets the high pressure water 19 from the heat exchanger 11 into the combustion gas 20 of the main combustion chamber 8 to be turned to steam 21.

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