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71. 发明申请

US20060269405A1 Modular fan inlet case 有权
标题翻译：模块化风扇进线箱
公开(公告)号：US20060269405A1
公开(公告)日：2006-11-30
申请号：US11140789
申请日：2005-05-31
申请人： Frank Euvino , David Lyders
发明人： Frank Euvino , David Lyders
IPC分类号： F03B11/02
CPC分类号： F02K3/062 , F01D5/147 , F02C7/04 , F05D2230/80 , Y02T50/672 , Y02T50/673
摘要： A modular fan inlet case includes a center ring, an outer ring, and a plurality of struts each coupled at a first end to the center ring, and at a second end to the outer ring. A plurality of shell members are each configured to be removably coupled to a corresponding strut. Preferably, the plurality of shell members each define a longitudinal groove for being received onto the corresponding strut.
摘要翻译：模块化风扇入口壳体包括中心环，外环和多个支柱，每个支柱在第一端连接到中心环，并且在第二端处连接到外环。多个壳体构件被构造成可移除地联接到相应的支柱。优选地，多个壳体构件各自限定用于接收到相应支柱上的纵向凹槽。

72. 发明申请

US20060096272A1 Thrust vectoring aft FLADE engine 有权
公开(公告)号：US20060096272A1
公开(公告)日：2006-05-11
申请号：US10982477
申请日：2004-11-05
申请人： John Baughman , James Johnson
发明人： John Baughman , James Johnson
IPC分类号： F02K3/062
CPC分类号： F02K3/062 , F01D5/022 , F02C3/13 , F02K3/075 , F02K3/077
摘要： An aft FLADE gas turbine engine including a fan section drivenly connected to a low pressure turbine section followed by an aft FLADE turbine having at least one row of aft FLADE fan blades radially extending across a FLADE duct circumscribing the aft FLADE turbine, and at least one thrust vectoring nozzle in pressurized fluid flow receiving communication with the FLADE duct. One embodiment of the engine includes spaced apart right and left hand FLADE exhaust nozzles in pressurized fluid flow receiving communication with the FLADE duct and offset from a main engine exhaust nozzle located downstream of the aft FLADE turbine. Right and left hand valves disposed in right and left hand ducts extending between a FLADE airflow manifold in pressurized fluid flow receiving communication with the FLADE duct may be used to vector thrust. The right and left hand FLADE exhaust nozzle may be fixed or thrust vectoring nozzles.

73. 发明授权

US4927329A Aircraft engine unducted fan blade pitch control system 失效
标题翻译：飞机引擎风扇叶片变桨控制系统
公开(公告)号：US4927329A
公开(公告)日：1990-05-22
申请号：US260645
申请日：1988-10-21
申请人： Gerald B. Kliman , Donald W. Jones
发明人： Gerald B. Kliman , Donald W. Jones
IPC分类号： B64C11/44 , F01D7/00 , F02C3/067 , F02K3/062
CPC分类号： F02K3/062 , F01D7/00 , F05D2260/74 , F05D2260/76 , Y02T50/671
摘要： An electric motor driven blade pitch varying system for the fan blades of an unducted fan type aircraft gas turbine engine utilizes permanent magnet alternating current motors located in the oil sump region of the engine. An alternator driven by the engine generates unregulated variable frequency, variable amplitude power which is rectified and placed on a DC bus. Controlled inverters convert the DC power on the bus to appropriate AC power for the motors. The system incorporates redundancy without significant weight penalty by providing alternators and motors dividing into two independent operating sections on common shafts. Separate electronic circuits are provided to supply power for each sectionalized motor or to rectify power from each alternator section. A common power bus may be used to couple the multiple motors and alternators. The common bus may alternatively receive power from tbe aircraft 400 Hz system or from on-board batteries.
摘要翻译：一种用于风扇型飞机燃气涡轮发动机的风扇叶片的电动机驱动叶片变桨系统利用位于发动机的油底壳区域中的永磁交流电动机。由发动机驱动的交流发电机产生未调节的可变频率，可变幅度功率，其被整流并放置在DC总线上。控制变频器将总线上的直流电源转换为电机的适当交流电源。该系统通过提供在公共轴上分为两个独立操作部分的交流发电机和电动机，实现冗余，而不会显着减轻重量。提供单独的电子电路以为每个分段电动机供电，或者对来自每个交流发电机部分的电力进行整流。可以使用公共电源总线来耦合多个电动机和交流发电机。公共总线可以替代地从飞行器400Hz系统或从车载电池接收电力。

74. 发明授权

US3968647A Multiflow gas turbine power plant 失效
标题翻译：多流燃气轮机发电厂
公开(公告)号：US3968647A
公开(公告)日：1976-07-13
申请号：US467793
申请日：1974-05-07
申请人： Serge Boudigues
发明人： Serge Boudigues
IPC分类号： F02K3/04 , F02K3/062 , F02K3/065 , F02C3/06
CPC分类号： F02K3/062 , F02K3/04 , F02K3/065
摘要： A dual-flow or multiflow gas turbine power plant comprising a jet pipe, ateast two separate flow-ducts each opening into the jet pipe, namely a first flow-ducts through which passes, in operation, a first gas flow and which contains a gas generator of the gas turbine type and an expansion-turbine located downstream of the gas generator, and a second flow-ducts through which passes, in operation, a second gas flow and a mixer device in which the first gas flow leaving the expansion turbine, and the second gas flow, are arranged to be mixed prior to entering the jet pipe, the plant further comprising a recompressor located downstream of the mixer device, in which the mixture of the two gas flows is arranged to be recompressed before entering the jet pipe.
摘要翻译：一种双流或多燃气涡轮发电厂，其包括喷射管，每个至少两个独立的流动管道，每个分开的流动管道通向喷射管，即第一流动管道，在操作中通过第一流动管道流过第一气流，燃气轮机类型的气体发生器和位于气体发生器下游的膨胀涡轮机，以及第二流动管道，其在运行中通过第二气体流和混合器装置，其中离开膨胀涡轮机的第一气流和第二气流布置成在进入喷射管之前混合，所述设备还包括位于混合器装置下游的再压缩机，其中两个气流的混合物布置成在进入射流之前被再压缩管。

75. 发明授权

US3070285A Gas turbine engine 失效
公开(公告)号：US3070285A
公开(公告)日：1962-12-25
申请号：US6628360
申请日：1960-10-31
申请人： ROLLS ROYCE
发明人： ALFRED OLDFIELD THOMAS
IPC分类号： F02K3/062
CPC分类号： F02K3/062

76. 发明授权

US3009318A Turbofan engine with reversible pitch fan 失效
标题翻译：涡轮风扇发动机采用可逆风扇
公开(公告)号：US3009318A
公开(公告)日：1961-11-21
申请号：US2413260
申请日：1960-04-22
申请人： RYAN AERONAUTICAL CO
发明人： RAY SKOFF
IPC分类号： F02K1/66 , F02K3/062
CPC分类号： F02K1/66 , F02K3/062 , Y02T50/671

77. 发明授权

US2989843A Engine for supersonic flight 失效
标题翻译：超音速发动机
公开(公告)号：US2989843A
公开(公告)日：1961-06-27
申请号：US37001953
申请日：1953-07-24
申请人： CURTISS WRIGHT CORP
发明人： ANTONIO FERRI
IPC分类号： F02C6/00 , F02K3/062
CPC分类号： F02C6/003 , F02K3/062 , Y02T50/671

78. 发明申请

US20180209380A1 AIRCRAFT COMPRISING TWO CONTRA-ROTATING FANS TO THE REAR OF THE FUSELAGE, WITH SPACING OF THE BLADES OF THE DOWNSTREAM FAN 审中-公开
公开(公告)号：US20180209380A1
公开(公告)日：2018-07-26
申请号：US15745944
申请日：2016-07-21
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Francois GALLET
IPC分类号： F02K3/072 , F02K1/72 , B64D27/14 , F02K1/66 , F02K3/065
CPC分类号： F02K3/072 , B64D27/14 , F01D7/00 , F02C3/073 , F02K1/52 , F02K1/66 , F02K1/72 , F02K3/062 , F02K3/065 , F05D2220/323 , F05D2240/35 , F05D2250/311 , F05D2260/74 , Y02T50/671 , Y02T50/673
摘要： The invention relates to an aircraft comprising a fuselage (1), which is propelled by a turbine engine with two coaxial fans, namely an upstream fan (7) and a downstream fan (8), driven by two contra-rotating rotors (5, 6) of a power turbine (3). The two fans (7, 8) and the turbine (3) are integrated into a nacelle (14) which projects downstream from the fuselage (1) and through which air flows. According to the invention, at least one of the fans (7, 8) of the aircraft and, in particular, the downstream fan (8) comprises variable-spacing blades, and at least one stator-forming variable-spacing blade ring (25) in the aircraft is placed upstream of the upstream fan (7). The variable-spacing stator blades (25) and the variable-spacing blades of the downstream fan (8) are mutually configured to direct the air flow in a first mode in which the air flows through the nacelle (14) from upstream to downstream and in a second mode in which the air is pushed back upstream through the nacelle (14).

79. 发明授权

US09970386B2 Exhaust stream mixer 有权
公开(公告)号：US09970386B2
公开(公告)日：2018-05-15
申请号：US14298331
申请日：2014-06-06
申请人： United Technologies Corporation
发明人： Lubomir A. Ribarov , James S. Elder
IPC分类号： F02K1/48 , F02K1/38 , B64D27/00 , F02K3/062 , B64D33/04
CPC分类号： F02K1/48 , B64D33/04 , B64D2027/005 , F02K1/386 , F02K3/062 , F05D2240/127 , F05D2260/2212 , Y02T50/672
摘要： An exhaust nozzle for a turbine engine includes multiple daisy style corrugations arranged circumferentially about the exhaust nozzle. Each of the daisy style corrugations has a radially inner base portion and multiple lobes protruding radially outward from the base portion.

80. 发明申请

US20180051627A1 GAS GENERATOR BIFURCATING EXHAUST DUCT TO FREE TURBINE 审中-公开
公开(公告)号：US20180051627A1
公开(公告)日：2018-02-22
申请号：US15239086
申请日：2016-08-17
申请人： United Technologies Corporation
发明人： Jesse M. Chandler , Gabriel L. Suciu
IPC分类号： F02C3/10 , F02C7/36 , F01D25/30 , F02K3/12 , B64D27/10 , B64D33/04 , B64D33/02
CPC分类号： F02C3/10 , B64D27/10 , B64D33/02 , B64D33/04 , F01D25/30 , F02C7/36 , F02K3/062 , F02K3/12 , F05D2220/32 , F05D2250/314 , F05D2260/40311
摘要： A gas turbine engine for an aircraft includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A free turbine is configured to be driven by gas flow from the core engine. A propulsor section aft of the core engine and is driven by the free turbine. An exhaust duct routes exhaust gases from the core engine to the free turbine. The free turbine is disposed aft of the propulsor section and the exhaust duct includes an outlet aft of the propulsor section communicating gas flow to drive the free turbine. An aircraft is also disclosed.

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