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21. 发明专利

JPH09287520A DOUBLE BYPASS ENGINE 失效
公开(公告)号：JPH09287520A
公开(公告)日：1997-11-04
申请号：JP13734996
申请日：1996-04-24
申请人： NEMOTO ISAMU
发明人： NEMOTO ISAMU
IPC分类号： F02K3/06 , F02K3/12
摘要： PROBLEM TO BE SOLVED: To improve a fuel consumption rate for reducing the emission quantity of NOx by partially extracting a working gass from the output of a high pressure turbine, and bypassing a low pressure turbine to lead an extracted gass into a backward exhaust, in a low bypass ratio turbo-fan serving as a propulsion engine for a supersonic transport airplane. SOLUTION: The outlet of the high pressure turbine HPT of a double bypass engine is connected to a core exhaust duct D, and an extraction valve V is provided at the inlet of an extraction flow path P opened toward the inside of the exhaust duct D. The extraction valve V is opened during supersonic cruising to carry out extraction through the HPT outlet, and a low pressure turbine LPT is bypassed to make the flow rate of HPT working gass more than the flow rate of LPT working gass. Thus the work of a high pressure system is increased without decreasing the work of low pressure system, and moreover the number of compressor revolutions is increased to increase the flow quantity of compressor for decreasing a bypass ratio. On the other hand, the extraction valve V is closed during low speed flight to make the flow quantity of each turbine the same.

22. 发明专利

JP2006194247A Gas turbine engine assembly 审中-公开
标题翻译：气体涡轮发动机总成
公开(公告)号：JP2006194247A
公开(公告)日：2006-07-27
申请号：JP2006000475
申请日：2006-01-05
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： WOLLENWEBER GARY C , TRUCO JOHN B
IPC分类号： F02C6/08 , F02C6/02 , F02C6/12 , F02C7/00 , F02C7/32 , F02K3/04 , F02K3/12
CPC分类号： F02C6/08 , F05D2220/50 , F05D2270/05 , F05D2270/07
摘要： PROBLEM TO BE SOLVED: To provide an aviation gas turbine system capable of obtaining sufficient output even during flight at high altitudes with low air density.
SOLUTION: This gas turbine engine assembly 10 comprises a propelling gas turbine engine 11 having a fan assembly 14 and a core engine assembly 13 located downstream of the fan assembly. The core engine comprises a booster compressor 102, a high pressure compressor 22, a high pressure turbine assembly 24, a booster turbine assembly 104, a low pressure turbine assembly 16 and a power generating auxiliary engine 12 coupled together in serial-flow arrangement such that the booster turbine is rotatably coupled to a booster fan. The auxiliary engine is coupled in communication with the core engine of the propelling gas turbine engine such that a part of air flow 40 entering the propelling engine is extracted for use by the auxiliary engine.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：提供即使在低空气密度的高空飞行期间也能获得足够的输出的航空燃气轮机系统。解决方案：该燃气涡轮发动机组件10包括具有风扇组件14和位于风扇组件下游的核心发动机组件13的推进式燃气涡轮发动机11。核心发动机包括串联流动装置联接在一起的增压压缩机102，高压压缩机22，高压涡轮组件24，升压涡轮组件104，低压涡轮组件16和发电辅助发动机12，使得增压涡轮机可旋转地联接到增压风扇。辅助发动机与推进燃气涡轮发动机的核心发动机联接，使得进入推进发动机的空气流40的一部分被提供供辅助发动机使用。版权所有（C）2006，JPO＆NCIPI

23. 发明专利

JP2004232636A Method and device for actuating gas turbine engine 有权
公开(公告)号：JP2004232636A
公开(公告)日：2004-08-19
申请号：JP2004017793
申请日：2004-01-27
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： WOLLENWEBER GARY CRAIG
IPC分类号： B64D41/00 , F02C6/06 , F02C6/08 , F02K3/02 , F02K3/06 , F02K3/12
CPC分类号： F02K3/12 , F02C6/06 , F02K3/06 , F05D2220/50
摘要： PROBLEM TO BE SOLVED: To provide a gas turbine assembly 10 to be used in an aircraft.
SOLUTION: The gas turbine assembly 10 includes a propulsion gas turbine and an auxiliary power unit 12. The propulsion gas turbine includes a fan 14 and a core engine 11 to generate thrust of the aircraft. A gas turbine engine further includes a bypass duct 50 extended from an outlet of the fan downstream to the core engine. The auxiliary power unit includes at least one turbine, and an inlet connected to the bypass duct of the gas turbine engine in a flow communication state. A part of air flow 52 going into the bypass duct of the gas turbine is introduced to be used in the auxiliary power unit.
COPYRIGHT: (C)2004,JPO&NCIPI

24. 发明专利

JPH10274099A UNIFORM ROTATION CONTROL TYPE COMPLEX STRUCTURE TURBOPLOP ENGINE DEVICE 失效
公开(公告)号：JPH10274099A
公开(公告)日：1998-10-13
申请号：JP8105498
申请日：1998-03-27
申请人： SNECMA
发明人： LOISY JEAN MAURICE
IPC分类号： F02C3/10 , F02C3/113 , F02C7/36 , F02K3/02 , F02K3/12
摘要： PROBLEM TO BE SOLVED: To dissolve a problem of hunching by providing with a complex structure gas generator having low and high pressure, and a propeller, constituting the gas generator by providing with a compressor, and a turbine for driving the compressor, and driving the propeller by at least a high pressure structure part in the gas generator. SOLUTION: A gas generator is provided with a low pressure compressor 1 connected to an annular air taking inlet 2, and the outlet of the low pressure compressor 1 is connected to an annular pipe 3 divided into a plurality of branch pipes 4. Each of branch pipes 4 are jointed again, the downstream end of the branch pipe 4 is constituted as an annular pipe 6 including a first elbow pipe 7 connected to a high pressure compressor 8, and a passing direction of gas flow is changed at 180 degrees in the elbow pipe 7. The outlet of the high pressure compressor 8 is connected to the inside of an annular combustion chamber 9, and high temperature gas generated in the annular combustion chamber 9 is supplied to driving turbines 10, 11 of the high pressure compressor 8 and the low pressure compressor 1 so as to drive the driving turbines 10, 11. The propeller 12 is driven through a reduction gear 13 by the high pressure turbine 10.

25. 发明专利

JPS54158511A PARTIAL SPAN TYPE INLET GUIDE VANE OF ENGINES THAT ARE LATERALLY CONNECTED MUTUALLY 失效
公开(公告)号：JPS54158511A
公开(公告)日：1979-12-14
申请号：JP5156579
申请日：1979-04-27
申请人： GEN ELECTRIC
发明人： ROORIN JIYOOJI KIFUIN SAADO , ONOFUA TAMA MANIYUERU KASUTERU
IPC分类号： F02K3/04 , F02K3/075 , F02K3/12 , F04D29/36

26. 实用新型

CN203604064U 一种涡轮喷气发动机失效
公开(公告)号：CN203604064U
公开(公告)日：2014-05-21
申请号：CN201320699493.3
申请日：2013-11-08
申请人：张文元
发明人：张文元
IPC分类号： F02K3/12
摘要：一种涡轮喷气发动机，主要是副发动机的副尾喷管通过连接管与主发动机的主尾喷管相连通，构成双进气道涡轮喷气发动机，副发动机将从大气中吸进的空气，在副尾喷管内进行速度调整、压缩，使气流的压力和温度升高后，经氧气挥发器形成富氧气流，该富氧气流经膨胀后，以高速从副尾喷管的喷口排出，经连接管喷入主发动机的主尾喷管内，向主发动机的主燃烧室内喷入氧气，使主燃烧室内未充分燃烧的燃气得到充分燃烧，可有效地增加主发动机的动力。从而可有效地提高发动机的推力，能使飞机的爬升高度和飞行航程得到有效地提高。

27. 发明专利

JP4034601B2 Variable cycle propulsion system with mechanical transmission means for supersonic aircraft 有权
公开(公告)号：JP4034601B2
公开(公告)日：2008-01-16
申请号：JP2002170959
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 , F02C7/36 , F02K3/04 , F02K3/075 , F02K3/12
CPC分类号： F02K3/04 , F02C7/36 , F02K3/12 , Y02T50/671

28. 发明专利

JP4034600B2 Variable cycle propulsion system having a compressed air branching means for supersonic aircraft 有权
公开(公告)号：JP4034600B2
公开(公告)日：2008-01-16
申请号：JP2002170958
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： F02C7/36 , F02C3/14 , F02C9/18 , F02K3/02 , F02K3/075 , F02K3/12
CPC分类号： F02K3/025 , F02K3/075 , F02K3/12 , Y02T50/671

29. 发明专利

JP2003206746A MULTI-FAN TYPE CORE ENGINE SEPARATE TYPE TURBOFAN ENGINE 审中-公开
公开(公告)号：JP2003206746A
公开(公告)日：2003-07-25
申请号：JP2002008071
申请日：2002-01-16
申请人： NAT AEROSPACE LAB
发明人： SAITO YOSHIO , ENDO MASANORI , MATSUDA YUKIO , SUGIYAMA SHICHIKEI , TAGASHIRA TAKESHI
IPC分类号： B64C29/00 , F02C1/02 , F02C3/10 , F02C3/13 , F02C6/08 , F02C7/36 , F02K3/00 , F02K3/06 , F02K3/075 , F02K3/077 , F02K3/12
摘要： PROBLEM TO BE SOLVED: To provide a multi-fan type core engine separate type turbofan engine to reduce the manufacturing cost of a turbofan engine with simple structure by using high-pressure air as a working fluid of a turbine driving a fan. SOLUTION: The turbine driving the fan 11 which constitutes a propulsion unit 3 of the multi-fan type core engine separate type turbofan engine 1 is an air turbine 13 driven by supplying a part of high-pressure air compressed by a compressor 5 of a core engine 2 through a duct 9. Since the working fluid of the air turbine 13 driving the fan 11 is not high-temperature combustion gas, it does not need to use an expensive heat-resistant material, can manufacture the propulsion unit 3 at low cost, and can simplify structure and operation control. COPYRIGHT: (C)2003,JPO

30. 发明专利

JP2003137192A VERTICAL TAKING-OFF/LANDING CRAFT 审中-公开
公开(公告)号：JP2003137192A
公开(公告)日：2003-05-14
申请号：JP2001334845
申请日：2001-10-31
申请人： MITSUBISHI HEAVY IND LTD
发明人： KAWAI HIDEJI
IPC分类号： B64C11/00 , B64C15/12 , B64C29/00 , B64D35/00 , F02K3/02 , F02K3/12
摘要： PROBLEM TO BE SOLVED: To provide a vertical taking-off/landing craft using a core separation type turbo fan engine omitting waste by unifying a cruise fan and a lift fan, in which a steering stability is excellent; an output of a propulsion force is possible against all space vectors; and a maneuverability is rich. SOLUTION: The fan engines in the core separation type turbo fan engine are rotatably supported by two shafts in a pitch direction and a roll direction and are disposed at both sides of a front blade and a rear blade provided on the vertical taking-off/landing craft respectively. Hovering and cruising can be carried out by the same fan engine by tilting it by two shafts.

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