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    ROCKET ENGINE COMBUSTION CHAMBER
    2.
    发明专利
    ROCKET ENGINE COMBUSTION CHAMBER 失效

    公开(公告)号：JPH06173775A

    公开(公告)日：1994-06-21

    申请号：JP31611592

    申请日：1992-10-30

    Applicant: NAT AEROSPACE LAB ,  MITSUBISHI HEAVY IND LTD ,  SUMIX KK ,  UEMURA KOGYO KK

    Inventor： KUMAKAWA AKINAGA ,  TOGAWA MORIHITO ,  YOSHIKAWA TOSHIHARU ,  OKADA MASUO ,  MATSUMURA MUNEYORI

    IPC: F02K9/62 ,  C25D15/02

    Abstract: PURPOSE:To prevent occurrence of come-off or crack of a heat insulator due to an abrupt rise of the temperature of the inner surface of a combustion chamber during initial combustion of rocket propellent by continuously decreasing the variance of heat insulator particles in a mother metal material from the thicknesswise center part to the inner and outer surfaces. CONSTITUTION:The center part of a rocket engine combustion chamber is formed of a composite metal material layer in which heat insulator particles 2 are uniformly distributed in a mother metal material 1 by a greatest variance. Further, intermediate parts 4, 5 formed on the inner and outer surfaces of the center part 3, are formed of a composite metal material layer in which the heat insulator particles 2 are uniformly dispersed in the metal mother material 1 by a variance which is smaller than that of the center part 3. Further, an inner surface part 6 formed on the inner surface of the inner intermediate part 4, and an outer surface part 7 formed on the outer surface of the outer intermediate part 5 are formed of a metal layer made of the pure mother metal material in which no heat insulator particles 2 are contained. That is, the variance of the heat insulator particles 2 in the mother metal material is reduced from the widthwise center part toward the inner and outer surfaces.

    ANNULAR MULTI-DIVISION TYPE WATER COOLED COMBUSTION CHAMBER
    3.
    发明专利
    ANNULAR MULTI-DIVISION TYPE WATER COOLED COMBUSTION CHAMBER 失效

    公开(公告)号：JPS57212350A

    公开(公告)日：1982-12-27

    申请号：JP9630681

    申请日：1981-06-22

    Applicant: NAT AEROSPACE LAB

    Inventor： SHINNO MASAYUKI ,  YATSUYANAGI NOBUYUKI ,  KUMAKAWA AKINAGA ,  SUZUKI AKIO ,  GOMI HIROMI ,  SAKAMOTO HIROSHI ,  SASAKI MASAKI

    IPC: G01M15/14 ,  F02K9/64 ,  F02K9/96

    Abstract: PURPOSE:To improve the critical heat flux density remarkably by a method wherein a saw-toothed array of fins is provided on a cooling surface and a mixing boiling property generated on the fin is utilized. CONSTITUTION:The combustion chamber is formed by the combination of annlar segments A having the cooling water flow paths such as a cooling water inlet pipe 1, an outlet pipe 2, a cooling water introducing pipe 3, an annular path 7 and the like and is provided with paths for fuel F, an oxidizer 0 and the cooling water CW. The cooling surface 5 of the alley of saw-toothed fin is formed on the surface of the combustion chamber side of the annular path 7 and the saw- toothed fin 8 on the cooling surface 5 of the alley of this saw-toothed fins is formed so as to have an apex angle of 60 deg., a height of 0.5mm. and a pitch of 0.6mm. substantially. Further, one of this path 7 is connected to the cooling water inlet pipe 1 while the other thereof is connected to the outlet pipe 2. According to this method, the cooling efficiency thereof may be improved remarkably.

    HEAT RESISTANCE STRUCTURE
    4.
    发明专利
    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

    Applicant: NAT AEROSPACE LAB ,  MITSUBISHI HEAVY IND LTD

    Inventor： KUMAKAWA AKINAGA ,  MIKI YOICHIRO ,  TAGUCHI HIDEYUKI

    IPC: F02K9/62 ,  C23C18/16 ,  C23C18/52 ,  C23C30/00

    Abstract: 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.

    PRODUCTION OF TILTING FUNCTIONAL MATERIAL
    5.
    发明专利
    PRODUCTION OF TILTING FUNCTIONAL MATERIAL 失效

    公开(公告)号：JPH0494926A

    公开(公告)日：1992-03-27

    申请号：JP21294890

    申请日：1990-08-10

    Applicant: NAT AEROSPACE LAB ,  KAWASAKI HEAVY IND LTD

    Inventor： SHINNO MASAYUKI ,  KUMAKAWA AKINAGA ,  WAKAMATSU YOSHIO ,  NAMIKATA SHUNICHI ,  FUJIOKA JUNZO ,  HINO HARUKI ,  MATSUMURA HIROYUKI

    IPC: B32B15/20 ,  B32B5/14 ,  B32B18/00 ,  C22C1/00 ,  C22C1/10 ,  C22C47/08

    Abstract: PURPOSE:To eliminate gravity segregation becoming trouble in the case of producing the tilting functional material by a melting method by constituting the surface of one side of only powdery material having large thermal conductivity and mixing the material excellent in heat resistance with the former so that the mixing ratio of the latter is gradually increased to ward the opposite side and melting this mixture in the gravity-free environment, cooling and solidifying it. CONSTITUTION:Powder such as CU and T1 large in thermal conductivity is utilized for a first material. Powder or fiber such as oxide, carbide and nitride excellent in heat resistance is utilized for a second material. For example, copper is regulated to powder of 1mum mean particle diameter and silicon oxide is regulated to powder of 0.1mum mean particle diameter. A volatile binder is mixed with the powdery raw material and this mixture is supplied to a quantitative mixer 2. This quantitative mixer is controlled by a computer 3 to continuously change the mixing ratio in the direction of board thickness. The this mixture is filled in a mold 4 and the binder is vaporized and removed. The mixture is pressurized by a press and transferred into a glass capsule. A plurality of molded raw materials obtained thereby are arranged into a cartridge by pinching ceramic wool between these molded raw materials while holding the mixture in the glass capsule. These are placed in a space craft and heated at 1200 deg.C for about one hour in the gravity-free environment of the space. Copper powder is melted and cooled to room temp.

    FUNCTIONALLY GRADIENT MATERIAL AND ITS MANUFACTURE
    6.
    发明专利
    FUNCTIONALLY GRADIENT MATERIAL AND ITS MANUFACTURE 失效

    公开(公告)号：JPH0417638A

    公开(公告)日：1992-01-22

    申请号：JP12034190

    申请日：1990-05-09

    Applicant: KAWASAKI HEAVY IND LTD ,  NAT AEROSPACE LAB ,  MIYAMOTO YOSHIO

    Inventor： NAMIKATA SHUNICHI ,  FUJIOKA JUNZO ,  HINO HARUKI ,  MATSUZAKI YUJI ,  SHINNO MASAYUKI ,  KUMAKAWA AKINAGA ,  WAKAMATSU YOSHIO ,  MIYAMOTO YOSHIO

    IPC: C04B35/622 ,  B22F3/14 ,  B22F3/15 ,  C04B35/645 ,  C22C1/04 ,  C22C29/00 ,  C22C29/18 ,  C22C32/00

    Abstract: PURPOSE:To attain at least any of the lightening in weight, the improvement of the degree of the sintering and the improvement of the workability in a functionally gradient material by combining any of ceramics, metals or intermetallic compounds with intermetallic compounds. CONSTITUTION:At the time of manufacturing a functionally gradient material, e.g. of an MoSi2(C11b type intermetallic compounds)-TiAl(L10 type intermetallic compounds), one end in the axial direction in a cylindrical vessel is filled with Ti-Al and the other end is filled with a gradient compsn. in such a manner that the mixed powder of Mo and Si is arranged in the molar ratio of 1:2, which is thereafter subjected to precompacting by cold isostatic pressing to obtain a raw material green compact 1. This green compact 1 is inserted into a glass container (capsule) 2 so that the axial direction of the green compact 1 will be approximately vertical, which is thereafter vacuum-sealed into a hot isostatic pressing apparatus 3, and the raw material powder or the like in the capsule is brought into reaction with or is sintered under the condition of pressurizing.

    INJECTOR OF ROCKET ENGINE
    8.
    发明专利
    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

    Applicant: NAT AEROSPACE LAB ,  MITSUBISHI HEAVY IND LTD

    Inventor： KUMAKAWA AKINAGA ,  MIKI YOICHIRO ,  TAGUCHI HIDEYUKI

    IPC: F02K9/52

    Abstract: 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.

    SCRAM JET ENGINE
    9.
    发明专利
    SCRAM JET ENGINE 失效

    公开(公告)号：JPH07259650A

    公开(公告)日：1995-10-09

    申请号：JP7135294

    申请日：1994-03-16

    Applicant: NAT AEROSPACE LAB ,  MITSUBISHI HEAVY IND LTD ,  UYEMURA C & CO LTD ,  SUMIX KK

    Inventor： KUMAKAWA AKINAGA ,  TOGAWA MORIHITO ,  MATSUMURA MUNEYORI ,  OKADA MASUO

    IPC: F02C7/00 ,  F02C7/04 ,  F02K7/14

    Abstract: PURPOSE:To provide a scram engine which is excellent in heat insulating property, and further in heat resistance, wear-resistance and durability and eliminates the possibility of generating blister by forming a metal composite material layer having an inclining function in which the dispersion amount of heat insulating particles in a base metal material is gradually decreased from the central part in the direction of thickness to the inner and outer surfaces on a part subjected to aerodynamic heating. CONSTITUTION:A metal composite material layer so constructed that the maximum amount of heat insulating material particles are dispersed in the central part in the direction of thickness in a base metal material, the dispersion amount is gradually decreased as it is directed to the inner and outer surfaces, and the inner surface and outer surface parts are respectively formed by a metal layer which does not contain heat insulating material particles is formed on at least one of the inside inclined wall and outside inclined wall of an intake part 3, a front wall of a strut part 6 and an outside inclined wall of a cowl part 8 of a scram jet engine main body 2.

    ENGINE COMBUSTION CHAMBER AND HEAT SHIELDING COATING FOR COMBUSTION CHAMBER INNER WALL
    10.
    发明专利
    ENGINE COMBUSTION CHAMBER AND HEAT SHIELDING COATING FOR COMBUSTION CHAMBER INNER WALL 失效

    公开(公告)号：JPH06167245A

    公开(公告)日：1994-06-14

    申请号：JP14739492

    申请日：1992-06-08

    Applicant: NAT AEROSPACE LAB ,  HITACHI LTD

    Inventor： SHINNO MASAYUKI ,  KUMAKAWA AKINAGA ,  FUKAYA YUKIKO ,  KOJIMA YOSHIYUKI ,  CHIKAZAKI MITSUO ,  ARIKAWA HIDEYUKI

    IPC: F02K7/14 ,  F02K9/62 ,  F23R3/42

    Abstract: PURPOSE:To prolong the life of the combustion chamber of an engine for space plane and improve reliability. CONSTITUTION:An engine combustion chamber is constituted so that a heat shielding coating 4 is formed through the dynamic mixing method when the necessary thickness of the heat shielding coating for a combustion chamber inner wall base member 1 is within a rang of several ten mum or so, while a heat shielding coating 5 is formed through the plasma flame spraying method in the case where the necessary thickness is larger, and the thickness of the heat shielding coating is continuously varied according to the degree of thermal load applied at the place, and the component in the thickness direction of the heat shielding coating is continuously changed from the component having the equal thermal expansion rate to that of the base member 1 to the ceramics component. Since the thickness of the heat shielding coating continuously varies, the heat shielding coating suitable for the place can be obtained, even if the degree of, the applied thermal load varies according to the place, and the life of the combustion chamber is prolonged, and the reliability of the engine can be improved.

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