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31. 发明专利

JP2003041949A Variable cycle propulsion system with mechanical transmitting means for supersonic airplane 有权
标题翻译：用于超级飞机机械传动装置的可变周期推进系统
公开(公告)号：JP2003041949A
公开(公告)日：2003-02-13
申请号：JP2002170959
申请日：2002-06-12
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： FRANCHET MICHEL , LAUGIER YANN , LOISY JEAN
IPC分类号： B64C30/00 , F02C7/36 , F02K3/04 , F02K3/075 , F02K3/12
CPC分类号： F02K3/04 , F02C7/36 , F02K3/12 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To provide a variable cycle propulsion system for supersonic flight that definitely separates a subsonic constitution from a supersonic constitution. SOLUTION: The variable cycle propulsion system for a supersonic airplane has at least one engine 1 capable of generating thrust for supersonic flight speed, and at least one auxiliary propulsion assembly 16 separate from the engine and capable of generating additional thrust for takeoff, landing and subsonic speed. The auxiliary propulsion assembly 16 has no gas generator. A transmitting means 20 is provided to transmit a part of mechanical force generated by the engine to the auxiliary propulsion assembly so that the additional thrust for takeoff, landing and subsonic cruising flight is generated. A means is further provided to decouple the transmitting means 20 for supersonic cruising flight.
摘要翻译：要解决的问题：为超音速飞行提供可变循环推进系统，确定将亚音速构造与超音速构造分开。解决方案：用于超音速飞机的可变循环推进系统具有至少一个能够产生用于超音速飞行速度的推力的发动机1，以及至少一个与发动机分离的辅助推进组件16，并能够产生用于起飞，着陆和亚音速的额外推力速度。辅助推进组件16没有气体发生器。发送装置20被提供以将由发动机产生的一部分机械力传递到辅助推进组件，使得产生用于起飞，降落和亚音速巡航飞行的附加推力。进一步提供了一种用于对发射装置20进行解耦用于超音速巡航飞行。

32. 发明专利

JP5325367B2 A method and apparatus for operating a gas turbine engine 有权
公开(公告)号：JP5325367B2
公开(公告)日：2013-10-23
申请号：JP2005068300
申请日：2005-03-11
申请人：ゼネラル・エレクトリック・カンパニイ
发明人：ジョン・ビー・タルコ , ゲーリー・クレイグ・ヴォーレンウェーバー
IPC分类号： B64D41/00 , F02K3/12 , F01D13/00 , F01D13/02 , F02C6/06 , F02C6/08 , F02C7/32 , F02K3/02 , F02K3/04 , F02K3/06
CPC分类号： F02C6/08 , F01D13/003 , F01D13/02 , F02C6/06 , F02K3/06 , F02K3/12 , F05D2220/50
摘要： An aircraft gas turbine engine assembly (10), including at least one propelling gas turbine engine (11) comprising a core engine (13) and an exhaust (32). The core engine includes at least one turbine (20) for generating thrust for the aircraft; and at least one auxiliary engine (12) including an inlet (24), at least one turbine (44), and an exhaust (80). The inlet is coupled in flow communication with at least one propelling gas turbine engine, such that a portion of airflow (31) flowing through the propelling engine is extracted from the propelling engine upstream from the propelling engine turbine, and is channeled to the auxiliary engine for generating power.

33. 发明专利

JP3903270B2 Double bypass engine 失效
公开(公告)号：JP3903270B2
公开(公告)日：2007-04-11
申请号：JP13734996
申请日：1996-04-24
申请人：勇根本
发明人：勇根本
IPC分类号： F02K3/06 , F02K3/12

34. 发明专利

JP2005256840A Method and apparatus for operating gas turbine engine 有权
标题翻译：用于运行气体涡轮发动机的方法和装置
公开(公告)号：JP2005256840A
公开(公告)日：2005-09-22
申请号：JP2005068300
申请日：2005-03-11
申请人： General Electric Co , ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人： TRUCO JOHN B , WOLLENWEBER GARY CRAIG
IPC分类号： B64D41/00 , F01D13/00 , F01D13/02 , F02C6/06 , F02C6/08 , F02C7/32 , F02K3/02 , F02K3/04 , F02K3/06 , F02K3/12
CPC分类号： F02C6/08 , F01D13/003 , F01D13/02 , F02C6/06 , F02K3/06 , F02K3/12 , F05D2220/50
摘要： PROBLEM TO BE SOLVED: To provide a method and an apparatus for operating a gas turbine engine used for aircraft propulsion and auxiliary power.
SOLUTION: An aircraft gas turbine engine assembly (10) contains at least one propelling gas turbine engine (11) equipped with a core engine (13) and an exhaust port (32). The core engine (13) contains at least one turbine (20) for generating thrust force of an aircraft, and at least one auxiliary engine (12) includes an inlet (24), at least one turbine (44) and an exhaust port (80). The inlet (24) is coupled to the at least one propelling gas turbine engine (11) in a state of fluid-communication. Part of an airflow flowing through the propelling engine (11) is extracted from the propelling engine (11) upstream from a propelling engine turbine, and is channeled to the auxiliary engine (12) to generate power.
COPYRIGHT: (C)2005,JPO&NCIPI
摘要翻译：要解决的问题：提供一种用于操作用于飞行器推进和辅助动力的燃气涡轮发动机的方法和装置。解决方案：飞机燃气涡轮发动机组件（10）包含装备有核心发动机（13）和排气口（32）的至少一个推进燃气涡轮发动机（11）。所述核心发动机（13）包含用于产生飞行器的推力的至少一个涡轮机（20），并且至少一个辅助发动机（12）包括入口（24），至少一个涡轮机（44）和排气口 80）。入口（24）以流体连通的状态联接到至少一个推进燃气涡轮发动机（11）。流经推进发动机（11）的气流的一部分从推进发动机（11）从推进式发动机涡轮机的上游抽出，并被引导到辅助发动机（12）以产生动力。版权所有（C）2005，JPO＆NCIPI

35. 发明专利

JP3431491B2 失效
公开(公告)号：JP3431491B2
公开(公告)日：2003-07-28
申请号：JP8105498
申请日：1998-03-27
IPC分类号： F02C3/10 , F02C3/113 , F02C7/36 , F02K3/02 , F02K3/12

36. 发明专利

JP2003090233A VARIABLE CYCLE PROPULSION SYSTEM HAVING COMPRESSED AIR BRANCHING MEANS FOR SUPERSONIC AIRCRAFT 审中-公开
公开(公告)号：JP2003090233A
公开(公告)日：2003-03-28
申请号：JP2002170958
申请日：2002-06-12
申请人： SNECMA MOTEURS
发明人： FRANCHET MICHEL , LAUGIER YANN , LOISY JEAN
IPC分类号： F02C7/36 , F02C3/14 , F02C9/18 , F02K3/02 , F02K3/075 , F02K3/12
摘要： PROBLEM TO BE SOLVED: To provide a variable cycle propulsion system for supersonic flight clearly separating a subsonic speed constitution from a supersonic speed constitution. SOLUTION: This variable cycle propulsion system for a supersonic aircraft, has at least one engine 1 having at least one compressor to be capable of generating thrust for a supersonic flight speed, and at least one auxiliary propulsion assembly 12 separate from the engine to be capable of generating further thrust for taking-off, landing, and subsonic speed cruising. The system is characterized in that the engine 1 is connected to the auxiliary propulsion assembly 12 so that it can generate further thrust for taking off, landing, and subsonic speed cruising, and that at least one pipe 20 guiding compressed air generated by the compressor to the auxiliary propulsion assembly and further at least one valve which closes the pipe for supersonic speed cruising are provided.

37. 发明专利

JP4068071B2 Gas turbine engine assembly 有权
公开(公告)号：JP4068071B2
公开(公告)日：2008-03-26
申请号：JP2004017793
申请日：2004-01-27
申请人：ゼネラル・エレクトリック・カンパニイGeneral Electric Company
发明人：ゲーリー・クレイグ・ヴォーレンウェーバー
IPC分类号： B64D41/00 , F02K3/02 , F02C6/06 , F02C6/08 , F02K3/06 , F02K3/12
CPC分类号： F02K3/12 , F02C6/06 , F02K3/06 , F05D2220/50

38. 发明专利

JP4005851B2 Variable cycle propulsion system with a gas branch means for supersonic aircraft, and the method of operation 有权
公开(公告)号：JP4005851B2
公开(公告)日：2007-11-14
申请号：JP2002170960
申请日：2002-06-12
申请人：スネクマ
发明人：ジヤン・ロワジー , ミシエル・フランシエ , ヤン・ロジエ
IPC分类号： B64C30/00 , F02K1/12 , F02C3/10 , F02C7/36 , F02K3/02 , F02K3/075 , F02K3/12
CPC分类号： F02K3/075 , F02K3/025 , F02K3/12 , Y02T50/671

39. 发明专利

JP2003065155A Variable-cycle propulsion system having gas branching means for supersonic aircraft and operation method thereof 有权
标题翻译：具有用于超级飞机的气体分配装置的可变循环推进系统及其运行方法
公开(公告)号：JP2003065155A
公开(公告)日：2003-03-05
申请号：JP2002170960
申请日：2002-06-12
申请人： Snecma Moteurs , スネクマ・モトウール
发明人： FRANCHET MICHEL , LAUGIER YANN , LOISY JEAN
IPC分类号： B64C30/00 , F02C3/10 , F02C7/36 , F02K1/12 , F02K3/02 , F02K3/075 , F02K3/12
CPC分类号： F02K3/075 , F02K3/025 , F02K3/12 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To provide a variable-cycle propulsion system for a supersonic aircraft with a subsonic construction and a supersonic construction that are fully separated. SOLUTION: This system includes a means for generating exhaust gas, at least one engine 1 having a gas exhaust nozzle, at least one separate auxiliary propulsion assembly 14 that is separated from the engine and has no gas generator and further gas flow branching means. The gas flow branching means branches at least a part of the exhaust gas generated by the engine, supplies the branched part of the exhaust gas to the propulsion assembly and is disposed movably between a position for enabling generation of thrust for take-off, landing and subsonic cruising flight and a position for sending gas generated by the engine 1 only to an engine nozzle for supersonic cruising freight.
摘要翻译：要解决的问题：为具有亚音速构造和完全分离的超音速构造的超音速飞机提供可变循环推进系统。解决方案：该系统包括用于产生废气的装置，至少一个具有排气喷嘴的发动机1，与发动机分离并且没有气体发生器和另外的气体流量分支装置的至少一个单独的辅助推进组件14。气流分支装置分支由发动机产生的废气的至少一部分，将排气的分支部分供给推进组件，并且可移动地设置在用于产生用于起飞和着陆的推力的位置和亚音速巡航飞行和将发动机1产生的气体仅发送到用于超音速巡航运输的发动机喷嘴的位置。

40. 发明专利

JP2001132541A JET ENGINE FOR SUPERSONIC AIRCRAFT 失效
公开(公告)号：JP2001132541A
公开(公告)日：2001-05-15
申请号：JP31938999
申请日：1999-11-10
申请人： NAT AEROSPACE LAB
发明人： FUTAMURA HISAO , TAGUCHI HIDEYUKI
IPC分类号： F02K3/11 , F02C6/02 , F02K3/12
摘要： PROBLEM TO BE SOLVED: To provide a jet engine for a supersonic aircraft capable of flying with supersonic speed while suppressing noise generated in taking-off at a low level, and capable of realizing high combustion efficiency. SOLUTION: A device is composed of a fore placed engine 2 consisting of a turbo fan engine, and an aft placed engine 4 consisting of a turbo fan or a turbo jet disposed backward the fore placed engine, bypass air of the fore placed engine 2 is boosted up by the aft placed engine 4 at the time of supersonic speed flight, and its temperature is raised so as to obtain large driving force. In taking-off, the bypass air is exhausted without boosting up and raising its temperature, and thereby, the taking-off can be operated with low noise.

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