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：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：JPH0192560A

公开(公告)日：1989-04-11

申请号：JP24961787

申请日：1987-10-02

Applicant: NAT AEROSPACE LAB

Inventor： YATSUYANAGI NOBUYUKI ,  TAMURA HIROSHI ,  SAKAMOTO HIROSHI ,  ONO FUMIE ,  GOMI HIROMI

IPC: B64G1/26 ,  F02K9/52

Abstract: PURPOSE:To improve combustion efficiency in a rocket having two kinds of fuel and liquid for propulsion agent by providing a fuel jet for sending atomized main liquid fuel info sub-fuel jet jetted under the gasified state and a liquid oxygen jet coaxial with said fuel jet. CONSTITUTION:In a rocket engine liquid oxygen, kerosene and hydrogen respectively for oxidizing agent, fuel and sub-fuel, liquid hydrogen 4 as sub-fuel is sent by a pump 8, and a portion of the sub-fuel is jetted from an injector 1 into a combustor 5, while the remaining is sent to a high temperature gas generator 6 to be burnt with the liquid oxygen 2 being supplied by a pump 8'. Pumps 8-8'' are driven through turbines 7, 7' with high temperature gas generated by said generator 6. Main fuel 3 is forced into the combustor 5 by the pump 8''. Then, the main fuel 3 and liquid oxygen 2 are jetted into the combustor 5 respectively from a jet 13 and an oxygen jet 12 provided in the center of a jet 14. A hydrogen jet 14' is opened to the upstream side wall of jet 14 to supply the sub-fuel 4.

公开(公告)号：JPS6082602A

公开(公告)日：1985-05-10

申请号：JP18880483

申请日：1983-10-07

Applicant: NAT AEROSPACE LAB ,  MASUDA YOSHIMICHI ,  WATANABE KAGOZOU ,  TAKEGAWA JIYUNJIROU ,  SUMITOMO ELECTRIC INDUSTRIES

Inventor： SHINNO MASAYUKI ,  SUZUKI AKIO ,  YATSUYANAGI NOBUYUKI ,  KUMAKAWA AKINAGA ,  SASAKI MASAKI ,  TAMURA HIROSHI ,  ONO FUMIE ,  MASUDA YOSHIMICHI ,  WATANABE KAGOZOU ,  TAKEGAWA JIYUNJIROU ,  DOI YOSHIHIKO ,  KUROISHI ATSUSHI ,  TAKEDA YOSHINOBU ,  OCHI SHIGEKI

IPC: B22F7/08 ,  B22F5/00 ,  B22F5/10 ,  B22F7/06 ,  F02K9/62 ,  F02K9/64

Abstract: PURPOSE:To manufacture a minute and solid external cylinder of a combustion chamber with hydrostatic pressure molding at comparatively low pressure by furnishing a reinforcing external cylinder to the outside of a Cu or an Ag-Sn Cu alloy sintered layer. CONSTITUTION:A hollow cylinder 1 made of oxygen-free copper is worked into an internal cylinder having a coolant passage groove 2 by numerical control mechanical cutting. A molten filler of Wood's metal 7 is poured into the groove 2 and the inside of the internal cylinder 1, and casted as a core. The surplus Wood's metal 7 is removed again by machining. The machined body is placed in a cylindrical mold 8, and copper powder 3 is packed into the clearance between the mold 8 and the cylinder 1. Then a powder packed layer is compression molded by hydrostatic pressure molding.