公开(公告)号：JPH04271996A

公开(公告)日：1992-09-28

申请号：JP3285891

申请日：1991-02-27

Applicant: NAT AEROSPACE LAB ,  MITSUBISHI HEAVY IND LTD

Inventor： KUMAGAI TATSUO ,  SAITO TOSHIHITO ,  WAKAMATSU YOSHIO ,  SHINNO MASAYUKI ,  TOGAWA MORIHITO

IPC: B64C1/00 ,  B64C1/38 ,  B64G1/00 ,  B64G1/58

Abstract: PURPOSE:To provide a high speed flight body applied with the diamond coating having the high heat conductivity at the top edge, in order to efficiently disperse the aerodynamic heating. CONSTITUTION:A high speed flight body having the high relative speed for air such as a space shuttle and aircraft has the diamond coating which is characterized by the application on the top edge surface.

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：JPH09229025A

公开(公告)日：1997-09-02

申请号：JP6385496

申请日：1996-02-27

Applicant: NAT AEROSPACE LAB

Inventor： KARITA TAKESHI ,  ONO FUMIE ,  SAITO TOSHIHITO ,  WAKAMATSU YOSHIO ,  SUNAMI TETSUHARU

IPC: B64D33/04 ,  B64G1/00 ,  F02K9/62 ,  F02K9/97 ,  F15D1/08

Abstract: PROBLEM TO BE SOLVED: To restrain pressure from increasing after reflection of shock wave by forming a secondary flow layer through application of injection or the like of secondary flow along a wall surface onto a part where the shock wave generated in a supersonic flow field reaches the wall surface. SOLUTION: A rocket engine 1 is provided with a secondary flow injection port 3 formed circularly which injects a secondary flow along the upstream to the downstream wall surface so that a secondary flow layer is formed, at a part where shock wave 6 of nozzle skirt 2 is reflected. A downstrem stage is formed at a circumferential wall and the port 3 is made open at the stepped wall. In the Fig. numerals 5, 7 denote a combustion unit and swelling wave, respectively. The engine 1 is so constituted in this way. Pressure increase after the reaction is restrained and the shock wave 6 after the reaction can be weakened by making a secondary flow layer reflect the shock wave 6, the secondary flow layer being formed by injecting the secondary flow, especially subsonic gas, along the wall surface, to a part where the shock wave 6 is incident to the wall surface.

公开(公告)号：JPH0672783A

公开(公告)日：1994-03-15

申请号：JP22403792

申请日：1992-08-24

Applicant: KAWASAKI HEAVY IND LTD ,  NAT AEROSPACE LAB

Inventor： NAMIKATA SHUNICHI ,  FUJIOKA JUNZO ,  MATSUZAKI YUJI ,  KAWAMURA MASASHI ,  KUSAKA KAZUO ,  SAITO TOSHIHITO ,  SASAKI MASAKI

IPC: C01B31/30 ,  C01B33/06 ,  C01B35/04 ,  C04B35/48 ,  C04B37/02 ,  C04B41/89

Abstract: PURPOSE:To obtain a heat resistant high strength lightweight cooling member by joining a compsn. gradient type material to the heating side surface of a heat resistant cooling structural member made of an intermetallic compd. CONSTITUTION:Plural constituent parts made of an intermetallic compd. such as a Ti-Al, Ni-Al, or Ti-B intermetallic compd. are prepd. A compsn. gradient type material 1 contg. an intermetallic compd. as a constituent material is also prepd. The plural constituent parts are joined by a diffusion joining method to obtain a cooling structural member 7. The compsn. gradient type material 1 is then joined to the heating side surface of the cooling structural member 7 so that the amt. of a coolant required is considerably reduced.

公开(公告)号：JPH0510854A

公开(公告)日：1993-01-19

申请号：JP16437991

申请日：1991-07-04

Applicant: NAT AEROSPACE LAB ,  MITSUBISHI HEAVY IND LTD

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

IPC: G01M15/14 ,  G01M9/04 ,  G01M15/00 ,  G01N3/60

Abstract: PURPOSE:To enable a large heat-resistance material and a sample such as a cooling structure to be heated for achieving an evaluation test by allowing a high-temperature high-speed gas to be discharged by receiving supply of a fuel and an oxidizer and this gas flow to be directed toward the sample. CONSTITUTION:A high-temperature high-speed gas is generated by allowing a fuel f to be combusted in a combustion equipment 10 and a gas flow is accelerated in a nozzle 11, thus forming a field of a high-temperature high-speed gas flow h. Then, a heat-resistance material, a sample 12 in cooling structure, etc., are installed within the field of this flow h and is heated, thus enabling them to be evaluated. Since this structure is based on a rocket-engine structure. a flow rate of a high-temperature gas can be set to a high level. thus enabling a test device to be large, especially an exit diameter of the nozzle 11 to be large. This increase in size allows a field of a large gas flow h to be formed, thus enabling the large heat-resistance material and the sample such as a cooling structure to be heated and evaluation test to be performed.