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31. 发明专利

JP2008508463A Heat engine 有权
公开(公告)号：JP2008508463A
公开(公告)日：2008-03-21
申请号：JP2007523238
申请日：2005-07-28
申请人：アガムエナージィシステムズリミテッド
发明人：アッサフ，ガド
IPC分类号： F02C7/08 , F01C13/04 , F02C3/045 , F02C7/105 , F04C23/02
CPC分类号： F01C11/004 , F01C7/00
摘要：流体入口及び流体出口を有する少なくとも１つの液封式回転ケーシング圧縮機（ＬＲＲＣＣ）と、ＬＲＲＣＣの出口と流体連通する燃焼室と、流体入口及び流体出口を有し流体入口が燃焼室と連通する少なくとも１つの膨張機とを備える熱機関。

32. 发明专利

JP2977340B2 失效
公开(公告)号：JP2977340B2
公开(公告)日：1999-11-15
申请号：JP26380091
申请日：1991-10-11
申请人： MITSUBISHI JUKOGYO KK
发明人： AOYAMA KUNIAKI
IPC分类号： F02C3/045 , F01D25/12 , F02C7/14 , F02C7/18

33. 发明专利

JPH1182061A GAS TURBINE 失效
公开(公告)号：JPH1182061A
公开(公告)日：1999-03-26
申请号：JP28421797
申请日：1997-09-08
申请人： MURAYAMA YOSHINOBU
发明人： MURAYAMA YOSHINOBU
IPC分类号： F02C3/045 , F02C5/04 , F02C5/12 , F02C7/00
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine that excels a reciprocating engine in performance, cost and exhaust components as a movable or stationary prime mover, has a simple structure causing no vibrations, needs easier maintenance and starting, and utilizes various types of fuel. SOLUTION: A disk 5 that is mounted on its one surface with compression blades 9 and on the other with impulse blades 4 is secured on a shaft 23 through a boss 28. The disk is mounted on its circumference with a ring 6 that defines an intake reservoir 64 encircling the compression blades and a combustion chamber 62 encircling the impulse blades. This ring has an intake port 40, which is closed by an intake valve 39. For a startup, an air tank 31 blows compressed air over the impulse blades to rotate a magnet 19, which accordingly generates electricity to red-heat a heating plug 61. A resultant rise in pressure of the reservoir opens the valve, in which state a fuel nozzle hole 37 jets fuel out into the combustion chamber so that it flows together with intake air up to the plug and ignites there. The explosion pressure closes the valve, in which state the combustion gas expands in the combustion chamber adiabatically and blows the impulse blades round to rotate the shaft. The combustion gas is straightened by guide vanes 10 to rotate the compression blades, which are integrated with axial blades 13, and supercharge the reservoir, and is also straightened by guide vanes 67 to rotate axial blades 68 and rotate the shaft.

34. 实用新型

JP2506309Y2 失效
公开(公告)号：JP2506309Y2
公开(公告)日：1996-08-07
申请号：JP11917889
申请日：1989-10-13
IPC分类号： F02C3/045 , F02C6/20 , F02C7/36 , F02C9/56

35. 实用新型

JPH0645636Y2 失效
公开(公告)号：JPH0645636Y2
公开(公告)日：1994-11-24
申请号：JP8226089
申请日：1989-07-14
IPC分类号： F02C3/045 , F02C7/36 , F02C9/28 , F02C9/56

36. 发明专利

JPH04308325A POWER SELF-CONTAINED TYPE HEAT EXCHANGER 失效
公开(公告)号：JPH04308325A
公开(公告)日：1992-10-30
申请号：JP31860991
申请日：1991-11-07
申请人： GEN ELECTRIC
发明人： JIYOOJI ARUBAATO KOFUINBERII
IPC分类号： B64D33/08 , F02C1/04 , F02C1/10 , F02C3/045 , F02C6/10 , F02C7/12 , F28D21/00
摘要： PURPOSE: To provide a heat exchange system for a supersonic flight vehicle capable of transmitting a mass quantity of heat from a high temperature zone to a low temperature zone. CONSTITUTION: In a heat exchange system 10, a gas outlet 30 of a compressor 20 of a turbo compressor 16 driven by gas (helium) is connected to a gas inlet 24 of a turbine 18 of a turbo compressor by a first conduit 32, and a gas outlet 26 of the turbine 18 is connected to a gag inlet 28 of the compressor 20 by a second conduit 34. The first conduit 32 has a part disposed close to a high temperature zone 12 (such as a combustor wall), and the second conduit 34 has a part disposed close to a low temperature zone 14 of a flighte vehicle (such as a fuel zone). The turbo compressor 16 is self-powered by temperature difference, a mass quantity of heat can be transmitted, and gas is enclosed in a housing 37 without leaking.

37. 实用新型

JPH0343537U 失效
公开(公告)号：JPH0343537U
公开(公告)日：1991-04-24
申请号：JP10350089
申请日：1989-09-05
IPC分类号： F02C3/045 , F02C3/22 , F02C3/30 , F23R3/00

38. 发明专利

JPH0266306A BOOSTING METHOD OF FLUIDIZED GASEOUS MEDIUM AND COMPRESSION TUBE THEREFOR AND POWER MACHINE TO WHICH SAID COMPRESSION TUBE IS APPLIED 失效
公开(公告)号：JPH0266306A
公开(公告)日：1990-03-06
申请号：JP17784389
申请日：1989-07-10
申请人： RAASUROO RENJIERU , GERUGEI BUERESHIYU
发明人： RAASUROO RENJIERU , GERUGEI BUERESHIYU
IPC分类号： F02C3/045 , F02C1/00 , F02C7/042 , F04F5/46 , F15D1/02
摘要： PURPOSE: To increase the actual pressure and entire pressure of a gaseous medium by taking off heat from gaseous medium flow while the gaseous medium flow is supersonic, that is, while flow after acceleration is guided through a supersonic diffuser. CONSTITUTION: An input element of a compression tube 10 is an accelerating element 8 which accelerates gaseous medium flow led in a direction of an arrow mark G, to supersonic velocity. A transient tube part 14 is a straight tube or a supersonic diffuser that can take off heat from the gaseous medium flow. In an impact tube part 13, steady shock wave is generated in the gaseious medium flow when supersonic flow enters it. A shock wave tube part 12 ensures deceleration from supersonic flow to subsonic flow so as to increase pressure once dropped to minimum pressure Pmin to take off heat in the transient tube part 14. A passing tube part 16 is a straight tube or a subsonic diffuser which takes off heat from the gaseous medium flow.

39. 实用新型

JPS5840265Y2 失效
公开(公告)号：JPS5840265Y2
公开(公告)日：1983-09-10
申请号：JP13837878
申请日：1978-10-07
IPC分类号： F02C3/045 , F02B37/00

40. 发明专利

JPS55117035A TURBOOMACHINE 失效
公开(公告)号：JPS55117035A
公开(公告)日：1980-09-09
申请号：JP300080
申请日：1980-01-14
申请人： SIMON JEAN MICHEL
发明人： JIYAN MISHIERU SHIMON
IPC分类号： F02C3/00 , F01D1/02 , F01D5/03 , F01D5/28 , F01D21/04 , F02C3/045 , F02C3/14 , F02C3/16

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