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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
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.
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Patent Agency Ranking
公开(公告)号：JPH0749060A
公开(公告)日：1995-02-21
申请号：JP21104093
申请日：1993-08-04
Applicant: NAT AEROSPACE LAB
Inventor： SAKAMOTO HIROSHI , YATSUYANAGI NOBUYUKI , SATO KAZUO , SASAKI MASAKI
IPC: F02K9/52
Abstract: PURPOSE:To obtain an ejector for a rocket engine which can keep highly efficient combustion with a widely variable air-fuel mixture without enlarging a capacity of a burner. CONSTITUTION:An outlet of a gas propellant ejector 11 has a tapered inside which contracts on an axis of a liquid propellant ejector 12. The gas propellant is struck against the liquid propellant ejected from the liquid propellant ejector 12. The gas propellant, entering the liquid propellant, changed into bubbles. The liquid propellant is further atomized in an expansion process in a burner 2 for easy combustion.
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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
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.
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公开(公告)号：JPS6082603A
公开(公告)日：1985-05-10
申请号：JP18880583
申请日：1983-10-07
Applicant: NAT AEROSPACE LAB , MASUDA YOSHIMICHI , WATANABE KAGOZOU , TAKEGAWA JIYUNJIROU , SUMITOMO ELECTRIC INDUSTRIES
Inventor： SHINNO MASAYUKI , YATSUYANAGI NOBUYUKI , KUMAKAWA AKINAGA , SUZUKI AKIO , SASAKI MASAKI , GOMI HIROMI , SAKAMOTO HIROSHI , MASUDA YOSHIMICHI , WATANABE KAGOZOU , TAKEGAWA JIYUNJIROU , DOI YOSHIHIKO , KUROISHI ATSUSHI , TAKEDA YOSHINOBU , OCHI SHIGEKI
Abstract: PURPOSE:To obtain a coolant passage with low friction pressure drop and good cooling efficiency by using a low-melting point alloy as a filler for a groove in the manufacture of an external cylinder of a liquid rocket combustor having a grooved cooling wall. CONSTITUTION:An external cylinder of a rocket combustor is manufactured through a grooved cooling wall providing stage, a stage for filling a filler into the groove, a stage for compression molding metallic powder into a specified thickness around an internal cylinder filled with the filler in the groove, and a stage for sintering the compression molded body. In this case, a low-melting point alloy such as Wood's metal is used as the filler. Accordingly, since the filler is not deformed during compression molding, the cross-sectional shape of the groove is not changed and the sintered surface is also smoothed. The coolant passage with low friction pressure drop and good cooling efficiency can be obtained in this way.
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公开(公告)号：DE3320556A1
公开(公告)日：1983-12-08
申请号：DE3320556
申请日：1983-06-07
Applicant: NAT AEROSPACE LAB
Inventor： NIINO MASAYUKI , YATSUYANAGI NOBUYUKI , KUMAKAWA AKINAGA , SUZUKI AKIO , GOMI HIROMI , SAKAMOTO HIROSHI , SASAKI MASAKI , MASUDA YOSHIMICHI , WATANABE RYUZO , TAKEKAWA JUN JIRO , OHTSUKI ETSUO , ISAGO TERASHI
Abstract: In the cooling wall of a regenerative cooling rocket combustion chamber, the throat portion thereof in which the heat load is highest is formed of a porous material having a perspiring cooling action. The other portion in which the heat load is relatively low is designed to be cooled by conventional forced convection. By such a composite cooling system, a high cooling effect is provided and yet the pressure loss in the cooling passages is small and light weight and long life of the engine are attained concurrently.
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公开(公告)号：DE3320557A1
公开(公告)日：1983-12-08
申请号：DE3320557
申请日：1983-06-07
Applicant: NAT AEROSPACE LAB
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