公开(公告)号：US20050188676A1

公开(公告)日：2005-09-01

申请号：US10781522

申请日：2004-02-18

申请人： Jean-Pierre Lair

发明人： Jean-Pierre Lair

IPC分类号： B05B12/00 ,  B64D33/04 ,  F01D20060101 ,  F02K1/30 ,  F02K1/34 ,  F02K1/38 ,  F02K3/02

CPC分类号： F02K1/383 ,  F02K1/30 ,  F02K1/34 ,  F02K3/077 ,  Y02T50/671

摘要： An exhaust nozzle includes an outer duct surrounding an inner duct. The inner duct includes a main outlet, and a row of apertures spaced upstream therefrom. The outer duct includes a row of intakes at a forward end, an auxiliary outlet at an aft end, and surrounds the inner duct over the apertures to form a bypass channel terminating at the auxiliary outlet. A row of flaps are hinged at upstream ends to selectively cover and uncover the apertures for selectively bypassing a portion of exhaust flow from the inner duct through the outer duct in confluent streams from both main and auxiliary outlets. When the flaps cover the apertures, the intakes ventilate the bypass channel and discharge flow through the auxiliary outlet.

摘要翻译： 排气喷嘴包括围绕内部管道的外部管道。 内部管道包括主出口和与其上游间隔开的一排孔。 外管道包括在前端的入口排，在后端处的辅助出口，并且围绕孔径围绕内部管道，以形成终止于辅助出口处的旁路通道。 一排襟翼在上游端铰接以选择性地覆盖和露出孔，用于选择性地旁路来自主管和辅助出口的汇合流中的从内管通过外管的排气流的一部分。 当襟翼覆盖孔时，入口通风旁路通道并排出通过辅助出口的流量。

公开(公告)号：US20050109012A1

公开(公告)日：2005-05-26

申请号：US10719884

申请日：2003-11-21

申请人： James Johnson

发明人： James Johnson

IPC分类号： F02K3/077 ,  F02K3/062 ,  F02K3/065 ,  F02K3/02

CPC分类号： F02K3/077 ,  F02K1/386 ,  F02K3/065 ,  F05D2220/327 ,  F05D2250/611

摘要： An aft FLADE gas turbine engine includes a fan section drivenly connected to a low pressure turbine section, a core engine located between the fan section and the low pressure turbine section, a fan bypass duct circumscribing the core engine and in fluid communication with the fan section, and a mixer downstream of the low pressure turbine section and in fluid communication with the fan bypass duct, and an aft FLADE turbine downstream of the mixer. At least one row of aft FLADE fan blades disposed radially outwardly of and connected to the aft FLADE turbine and radially extending across a FLADE duct circumscribing the fan bypass duct. The aft FLADE turbine may be a free turbine or connected to and rotatable with the low pressure turbine section. A power extraction apparatus may be disposed within the engine and drivenly connected to the aft FLADE turbine.

摘要翻译： 后FLADE燃气涡轮发动机包括驱动地连接到低压涡轮机部分的风扇部分，位于风扇部分和低压涡轮机部分之间的核心发动机，围绕核心发动机并与风扇部分流体连通的风扇旁路管道 以及在低压涡轮机部分下游并与风扇旁通管道流体连通的混合器，以及在混合器下游的后FLADE涡轮机。 至少一排后FLADE风扇叶片设置在尾部FLADE涡轮机的径向外部并且连接到尾部FLADE涡轮机，并且径向延伸跨越包围风扇旁路管道的FLADE管道。 后FLADE涡轮机可以是自由涡轮机，或者与低压涡轮机部分连接并可转动。 动力提取装置可以设置在发动机内并且被驱动地连接到后FLADE涡轮。

公开(公告)号：US06792746B2

公开(公告)日：2004-09-21

申请号：US10341390

申请日：2003-01-14

申请人： Yoshio Saito ,  Masanori Endo ,  Yukio Matsuda ,  Nanahisa Sugiyama ,  Takeshi Tagashira

发明人： Yoshio Saito ,  Masanori Endo ,  Yukio Matsuda ,  Nanahisa Sugiyama ,  Takeshi Tagashira

IPC分类号： F02K1100

CPC分类号： F02K3/077 ,  F02C1/02 ,  F02C3/10 ,  F02C3/13 ,  F02C3/14 ,  F02C6/08 ,  F02K3/075 ,  F02K3/11 ,  F02K3/12

摘要： A low-noise separated core engine type turbofan engine is provided in which noise generated by a control propulsion device is reduced by using high pressure air as the working fluid of a turbine for driving a control fan used in the attitude control of the airframe. A control fan 17 of a separated core engine type turbofan engine 1, which is comprised in a control propulsion device 4 provided for attitude control of the aircraft, is driven by an air turbine 19 which uses as working fluid high pressure air compressed by a compressor 6 of the core engine 2 and supplied through a duct 10. The speed of the working fluid which is discharged from the control fan 17 and air turbine 19 is sufficiently low for attitude control and not as high as the speed of the working fluid which is discharged from a propulsion device 3 which is provided for thrust, and thus noise generated by the control propulsion device 4 can be reduced.

摘要翻译： 提供了一种低噪声分离式核心发动机型涡扇发动机，其中通过使用高压空气作为用于驾驶用于机身姿态控制的控制风扇的涡轮机的工作流体来减少由控制推进装置产生的噪声。 分离的核心发动机型涡扇发动机1的控制风扇17包括在用于飞行器的姿态控制的控制推进装置4中，由空气涡轮机19驱动，空气涡轮机19使用作为工作流体的压缩空气，压缩机 并且通过管道10供给。从控制风扇17和空气涡轮19排出的工作流体的速度对于姿态控制而言足够低，而不是工作流体的速度高 从用于推力的推进装置3排出，从而可以减少由控制推进装置4产生的噪音。

公开(公告)号：US20030150206A1

公开(公告)日：2003-08-14

申请号：US10327256

申请日：2002-12-20

发明人： J. Axel Glahn ,  Michael K. Sahm

IPC分类号： F02C006/00

CPC分类号： F02C3/13 ,  B64D33/02 ,  B64D33/04 ,  B64D41/00 ,  F02C7/32 ,  F02K3/075 ,  F02K3/077 ,  Y02T50/44 ,  Y02T50/671

摘要： The present invention relates to an engine integrated auxiliary power unit. The engine comprises a high pressure spool which includes a high pressure compressor connected to a high pressure turbine and a low pressure spool which includes a low pressure compressor connected to a low pressure turbine. The engine further has a system for independently operating the high pressure spool and thus allowing the high pressure spool to function as an auxiliary power unit.

摘要翻译： 本发明涉及发动机一体化辅助动力单元。 发动机包括高压阀芯，其包括连接到高压涡轮机的高压压缩机和包括连接到低压涡轮机的低压压缩机的低压阀芯。 发动机还具有用于独立地操作高压阀芯并因此允许高压阀芯用作辅助动力单元的系统。

公开(公告)号：US5806303A

公开(公告)日：1998-09-15

申请号：US624288

申请日：1996-03-29

申请人： James E. Johnson

发明人： James E. Johnson

IPC分类号： F02K1/30 ,  F02K3/075 ,  F02K3/077 ,  F02K3/105 ,  F02K3/06 ,  F02K1/12

CPC分类号： F02K3/105 ,  F02K1/30 ,  F02K3/075 ,  F02K3/077 ,  Y02T50/671

摘要： A multiple bypass turbofan engine including a core engine assembly has a fan bypass duct radially outward of the core engine assembly and has first and second inlets disposed between forward and aft fans driven by a low pressure turbine and a core engine turbine respectively. An inlet duct having an annular duct wall is disposed radially inward of the bypass duct and connects the second inlet to the bypass duct and has disposed within a supercharger means for compressing air which is drivingly connected to the core turbine. The engine has an duct with an afterburner in an upstream portion and at a downstream end it has an exhaust nozzle with a fixed geometry throat. The nozzle may also have a fixed geometry exhaust nozzle outlet with or without a means for blowing at the throat. One embodiment of the aft fan may have radially inner and outer rows of aft fan vane airfoils separated by a non-rotatable portion of the annular duct wall such that the outer row of aft fan vane airfoils are disposed in the inlet duct and the aft fan vane airfoils are independently variable. Radially inner and outer rows of aft fan rotor blade airfoils are separated by a rotatable portion of the annular duct wall such that the outer row of aft fan rotor blade airfoils are disposed in the inlet duct adjacent to and longitudinally aft of radially inner and outer rows of aft fan vane airfoils, respectively thus providing the supercharger means.

摘要翻译： 包括核心发动机组件的多旁路涡扇发动机发动机具有在核心发动机组件的径向外侧的风扇旁通管道，并且分别设置有由低压涡轮机和核心发动机涡轮机驱动的前后风扇之间的第一和第二入口。 具有环形管道壁的入口管路设置在旁路管道的径向内侧，并将第二入口连接到旁路管道，并且设置在增压器装置中，用于压缩驱动地连接到核心涡轮机的空气。 发动机具有在上游部分中具有后燃器的管道，并且在下游端具有带有固定几何形状喉部的排气喷嘴。 喷嘴还可以具有固定的几何形状排气喷嘴出口，具有或不具有用于在喉部吹气的装置。 后风扇的一个实施例可以具有径向的内排和外排的后风扇叶片翼型件，其通过环形管道壁的不可旋转部分分开，使得外排的后风扇叶片翼型件设置在入口管道和后风扇 叶片翼型可独立变化。 后风扇转子叶片叶片的径向内侧和外侧行由环形管道壁的可旋转部分分开，使得外排风扇转子叶片叶片的外排设置在入口管道中，邻近并纵向向内的径向内外排 的后翼形叶片翼片，分别提供增压装置。

公开(公告)号：US5694768A

公开(公告)日：1997-12-09

申请号：US484083

申请日：1990-02-23

申请人： James Edward Johnson ,  Elmore Verne Sprunger ,  John Robert Simmons

发明人： James Edward Johnson ,  Elmore Verne Sprunger ,  John Robert Simmons

IPC分类号： F02K3/075 ,  F02K3/077 ,  F02K7/16 ,  F02K3/02

CPC分类号： F02K3/077 ,  F02K3/075 ,  F02K7/16

摘要： An improved variable cycle turbofan-ramjet engine is disclosed. The engine includes a split fan assembly, a bypass channel surrounding a core engine and a mode selector valve for selectively bypassing air around an aft fan and the core engine. In a first, single bypass mode of operation, the mode selector valve allows air to flow through both a forward fan and the aft fan, and a portion of which bypasses the core engine. In a second, double bypass mode of operation, the mode selector valve allows air from the forward fan to bypass the aft fan and a portion of the air from the forward fan to bypass the core engine. In a third, ramjet mode of operation, the mode selector vane bypasses air around the aft fan and the core engine and the core engine is shut down for ramjet operation. In the preferred embodiment, the forward fan is allowed to windmill and powers a fuel pump connected thereto for providing fuel to a ram burner of the engine for ramjet operation.

摘要翻译： 公开了一种改进的可变循环涡扇喷气发动机。 发动机包括分体风扇组件，围绕核心发动机的旁通通道和用于选择性地绕过尾风扇和核心发动机的空气的模式选择阀。 在第一个单旁路操作模式中，模式选择阀允许空气流过前风扇和后风扇，其一部分绕过核心发​​动机。 在第二个双旁路操作模式中，模式选择阀允许来自前风扇的空气绕过后风扇和来自前风扇的一部分空气绕过核心发​​动机。 在第三种冲压式操作模式中，模式选择器叶片绕过后风扇绕过空气，并且核心发动机和核心发动机关闭以进行冲压喷射操作。 在优选实施例中，允许前风扇对与其连接的燃油泵进行风力发电，为燃料喷射操作的发动机的冲压燃烧器提供燃料。

公开(公告)号：US4010608A

公开(公告)日：1977-03-08

申请号：US587135

申请日：1975-06-16

申请人： John Robert Simmons

发明人： John Robert Simmons

IPC分类号： F02C9/18 ,  F02K3/02 ,  F02K3/04 ,  F02K3/075 ,  F02K3/077

CPC分类号： F02K3/077 ,  F02K3/075 ,  Y02T50/671

摘要： One or more of the aft stages of the fan section of a gas turbine engine are rotated by the high pressure turbine of a gas generator and the remainder of the fan stages are rotated by a low pressure turbine downstream of the gas generator. This arrangement divides the fan work between the low and high pressure turbines to permit more efficient utilization of the total available turbine capacity, reduction in low pressure turbine workload, increased aft fan stage pressure ratio capability and greater flow and pressure ratio modulation potential for a split fan engine. The invention has a wide range of application for various turbofan configurations including separated and/or mixed flow turbofan engines with separated or close coupled fan sections.

摘要翻译： 燃气涡轮发动机的风扇部分的后级中的一个或多个由气体发生器的高压涡轮机旋转，并且其余的风扇级由气体发生器下游的低压涡轮转动。 这种布置将风机工作分为低压和高压涡轮机之间，以允许更有效地利用总可用的涡轮机容量，降低低压涡轮机工作量，增加后方风扇级压力比能力以及更大的流量和压力比调制电位 风扇发动机。 本发明对于各种涡轮风扇结构具有广泛的应用，包括具有分离或紧密联接的风扇部分的分离式和/或混合式涡轮风扇发动机。

公开(公告)号：US12123350B2

公开(公告)日：2024-10-22

申请号：US17190076

申请日：2021-03-02

申请人： General Electric Company

发明人： Daniel Alan Niergarth ,  Nicholas M. Daggett ,  Steven Douglas Johnson ,  Anand P. Roday ,  Scott Alan Schimmels

IPC分类号： F02C7/18 ,  F02C7/14 ,  F02C7/047 ,  F02K3/077

CPC分类号： F02C7/18 ,  F02C7/14 ,  F02C7/047 ,  F02K3/077 ,  F05D2240/12 ,  F05D2260/213

摘要： A three-stream engine is provided. The three-stream engine includes a fan section, a core engine disposed downstream of the fan section, and a core cowl annularly encasing the core engine and at least partially defining a core duct. A fan cowl is disposed radially outward from the core cowl and annularly encasing at least a portion of the core cowl. The fan cowl at least partially defining an inlet duct and a fan duct. The fan duct and the core duct at least partially co-extending axially on opposite sides of the core cowl. A heat exchanger disposed within the fan duct. The heat exchanger provides for thermal communication between a fluid flowing through fan duct and a motive fluid flowing through the heat exchanger.

公开(公告)号：US20180355749A1

公开(公告)日：2018-12-13

申请号：US15386054

申请日：2016-12-21

申请人： William G. Sheridan

发明人： William G. Sheridan

IPC分类号： F01D13/00 ,  F02C3/107 ,  F02K3/04 ,  F02C7/36 ,  F01D25/20

CPC分类号： F01D13/003 ,  F01D25/20 ,  F02C3/107 ,  F02C6/00 ,  F02C7/36 ,  F02K3/04 ,  F02K3/077 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2260/4031 ,  F05D2260/98

摘要： A propulsion system for an aircraft comprises a gas generator including a turbine driving a main drive shaft, the main drive shaft, in turn, driving at least two fan drive shafts, wherein the at least two fan drive shafts are driven on non-coaxial axes, the fan drive shaft each driving a fan rotor through a fan drive system. A fan lubrication system provides lubrication to each of the fan drive systems.

公开(公告)号：US10060286B2

公开(公告)日：2018-08-28

申请号：US14780341

申请日：2014-02-05

申请人： United Technologies Corporation

发明人： Felix Izquierdo

IPC分类号： F01D17/16 ,  F02C9/22 ,  F02K3/077 ,  F02K3/075 ,  F02C9/20

CPC分类号： F01D17/162 ,  F02C9/20 ,  F02K3/075 ,  F02K3/077 ,  F05D2240/12 ,  F05D2250/44 ,  F05D2260/4031 ,  F05D2260/53 ,  F05D2260/79

摘要： An annular airflow control system for a gas turbine engine includes a sync ring rotatable to move the multiple of contra-rotatable variable vanes through a respective multiple of geared interfaces to throttle an airflow through the multiple of contra-rotatable variable vanes.