公开(公告)号：JPH03246355A

公开(公告)日：1991-11-01

申请号：JP4350790

申请日：1990-02-23

Applicant: NAT AEROSPACE LAB

Inventor： MASUTANI GORO ,  KOMURO TOMOYUKI ,  MURAKAMI JUNRO ,  KUDO KENJI ,  TANI KOICHIRO ,  CHINZEI NOBUO ,  WAKAMATSU YOSHIO ,  KARITA TAKESHI

IPC: F02K7/14

Abstract: PURPOSE:To ignite the fuel jets from plural wall surfaces by a single ignitor and to reduce the number of ignitors, by forming a recirculating area of the fuel including a fuel mixture gas to be jetted from numerous fuel jet orifices in a scrum jet combustor, from plural wall surfaces. CONSTITUTION:In a combustion chamber in which wall surfaces 1 and 2 are crossed at 90 deg., backward steps 3 are formed to the wall surfaces, and plural pilot fuel fet orifices 5 are formed on the wall surface 1 at the upper stream side of steps 3, while an ignitor 6 is provided near the step 3 at the downstream side of the step. And plural main fuel jet orifices 7 are formed on the wall surface 2 at the downstream side of the step. As a result, a low speed recirculating area including a fuel mixture gas with a density suitable to circulate flames 4 along the wall surface of the combustion chamber can be formed, the fuel jets from the wall surfaces 1 and 2 can be ignited by the single ignitor 6, and the number of ignitors can be reduced.

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

IPC: B64C1/38 ,  B64C15/14 ,  B64D27/16 ,  B64D41/00

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.

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

IPC: F42B35/00 ,  F02K9/46 ,  F42B15/00

公开(公告)号：JPH06249070A

公开(公告)日：1994-09-06

申请号：JP5466793

申请日：1993-02-22

Applicant: NAT AEROSPACE LAB

Inventor： KARITA TAKESHI ,  MASUTANI GORO ,  ONO FUMIE ,  CHINZEI NOBUO ,  WAKAMATSU YOSHIO ,  SAITO TOSHIHITO ,  TAKAHASHI MASAHIRO

IPC: F02K9/64 ,  F02K7/10

Abstract: PURPOSE:To improve cooling efficiency, reduce flow of cooling medium and restrain engine performance from lowering by film cooling a position exposed to high temperature air current by the use of gas heated to high temperature. CONSTITUTION:Positions exposed to high temperature air current of a ramjet, rocket engine, etc., are film cooled by the use of gas heated to high temperature. For example, regenerative cooling is utilized for a heater 1 in a flow path of liquid hydrogen A. The liquid hydrogen A cools the wall surface of a combustion chamber, while it is heated and gasified to be jetted from a fuel injector 3 into the combustion chamber, mixed and burnt with air from an air intake port for jetting combustion gas C. A portion of high temperature gasified hydrogen is jetted from a film coolant injector 2 along the wall thereof to prevent the combustion gas contact with the wall of the injector and reduce the temperature rise of the wall. The flow of the coolant can be reduced by a simple constitution of disposing thus a heating source in a film coolant flow path.

公开(公告)号：JPH0566176A

公开(公告)日：1993-03-19

申请号：JP22805991

申请日：1991-09-09

Applicant: NAT AEROSPACE LAB ,  MITSUBISHI HEAVY IND LTD

Inventor： KUMAGAI TATSUO ,  SAKURANAKA NOBORU ,  UEDA SHUICHI ,  SAITO TOSHIHITO ,  WAKAMATSU YOSHIO ,  SHINNO MASAYUKI ,  ADACHI NAOTO ,  NAGATA SATOSHI ,  SAKAMOTO AKIRA

IPC: G01M9/04 ,  G01N3/18 ,  G01N3/60 ,  G01N25/00

Abstract: PURPOSE:To restrain oxidation of a panel-shaped test piece from its end face and to enable miniaturization of the test piece by fixing the panel-shaped test piece in the direction of flow, and extending the surface of the test piece in the longitudinal or cross direction. CONSTITUTION:In a test piece holder 2 a panel-shaped test piece 1 is installed between two holders 2 each shaped like an extended test piece 1, and the test piece 1 is fixed within the gas flow of a high temperature gas generator 3 and in the direction of the gas flow. Because the boundary layer of the high temperature gas flow first develops on the holders 2, then transfers itself into turbulent flow, and becomes a sufficiently developed turbulent flow boundary layer on the test piece 1, no great change in heat conduction due to the transition of the boundary layer occurs on the test piece 1 and the test piece 1 is uniformly heated. Since heat stagnation points exit only on the holders 2, the rate of uneven heating of the test piece 1 can be lowered. Also, the holders 2 prevent the end portion of the test piece 1 from being exposed at its face to the high temperature gas flow, thereby preventing oxidation of the test piece 1 from its end face.

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.

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.

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.