公开(公告)号：EP3231710A1

公开(公告)日：2017-10-18

申请号：EP17165810.7

申请日：2017-04-10

Applicant: General Electric Company

Inventor： NIERGARTH, Daniel Alan ,  VONDRELL, Randy M. ,  MILLER, Brandon Wayne ,  MARRINAN, Patrick Michael

IPC: B64D27/26

CPC classification number: F04D25/06 ,  B64C21/06 ,  B64C2230/04 ,  B64D27/24 ,  B64D33/02 ,  B64D2027/026 ,  B64D2033/0226 ,  F02K5/00 ,  F04D19/002 ,  F04D25/028 ,  F04D29/043 ,  F04D29/668 ,  F05D2220/36 ,  F05D2240/20 ,  F05D2240/60 ,  F05D2260/40311 ,  Y02T50/166 ,  Y02T50/62

Abstract: A propulsion system 100 for an aircraft 10 includes an electric propulsion engine configured to be mounted to the aircraft 10 at an aft end of the aircraft 10. The electric propulsion engine includes a power gearbox 336 mechanically coupled to an electric motor 334. The electric propulsion engine further includes a fan 304 rotatable about a central axis 302 of the electric propulsion engine by the electric motor 334 through the power gearbox 336. Moreover, the electric propulsion engine includes an attachment assembly for mounting at least one of the electric motor 334 or the power gearbox 336. The attachment assembly includes a torsional damper for accommodating a torsional vibration of the electric motor 334 or the power gearbox 336.

Abstract translation: 用于飞机10的推进系统100包括电动推进发动机，该电动推进发动机构造成在飞机10的后端安装到飞机10上。电推进发动机包括机械联接到电动机334的动力齿轮箱336.电动推进器 发动机还包括风扇304，风扇304可通过电动机334通过动力齿轮箱336绕电推进发动机的中心轴线302旋转。此外，电推进发动机包括用于安装电动机334或电动机334中的至少一个的附接组件。 附接组件包括用于适应电动机334或动力齿轮箱336的扭转振动的扭转阻尼器。

公开(公告)号：EP2998557B1

公开(公告)日：2017-07-12

申请号：EP14382349.0

申请日：2014-09-17

Applicant: Airbus Operations, S.L.

Inventor： Bailey Noval, Nicolás ,  Llamas Sandín, Raúl

IPC: F02K3/06 ,  F02K5/00 ,  F02C6/20

CPC classification number: F02C6/14 ,  F02C6/20 ,  F02C6/206 ,  F02K3/06 ,  F02K5/00 ,  F05D2220/323 ,  F05D2220/64 ,  F05D2220/76

公开(公告)号：EP3147219A1

公开(公告)日：2017-03-29

申请号：EP16190031.1

申请日：2016-09-22

Applicant: Rolls-Royce Corporation ,  Rolls-Royce North American Technologies, Inc.

Inventor： Armstrong, Michael James ,  Vaisman, Igor

IPC: B64D27/02 ,  F02K3/06 ,  F02K3/077 ,  F02C1/10 ,  F01K23/10 ,  F01K25/10 ,  F02K3/12 ,  F02C6/18

CPC classification number: F02K5/00 ,  B64D27/02 ,  B64D2027/026 ,  F01K23/10 ,  F01K25/103 ,  F02C1/105 ,  F02C6/18 ,  F02C6/206 ,  F02K3/06 ,  F02K3/077 ,  F02K3/12 ,  F05D2210/12 ,  F05D2210/13 ,  F05D2240/40 ,  F05D2250/311 ,  F05D2260/213 ,  Y02T50/675

Abstract: A power and propulsion system (400, 500, 600, 700) includes an air compressor (712, 718), a combustor (724) positioned to receive compressed air from the air compressor (712, 718) as a core stream (726), and a closed-loop system (404, 504, 722) having carbon dioxide as a working fluid that receives heat from the combustor (724) and rejects heat to a cooling stream. The closed-loop system (404, 504, 722) configured to provide power to a fan (718, 732) that provides the cooling stream, and to one or more distributed propulsors (406, 506, 606, 608) that provide thrust to an aircraft.

Abstract translation: 动力和推进系统（400,500,600,700）包括空气压缩机（712,718），定位成将来自空气压缩机（712,718）的压缩空气作为核心流（726）接收的燃烧器（724） 以及具有二氧化碳作为工作流体的闭环系统（404,504,722），其接收来自燃烧器（724）的热量并将热量排除到冷却流。 闭环系统（404,504,722）被配置为向提供冷却流的风扇（718,732）以及向一个或多个分布式推进器（406,506,606,608）提供动力，所述推进器提供推力 一架飞机

公开(公告)号：EP2998557A1

公开(公告)日：2016-03-23

申请号：EP14382349.0

申请日：2014-09-17

Applicant: Airbus Operations, S.L.

Inventor： Bailey Noval, Nicolás ,  Llamas Sandín, Raúl

IPC: F02K3/06 ,  F02K5/00 ,  F02C6/20

CPC classification number: F02C6/14 ,  F02C6/20 ,  F02C6/206 ,  F02K3/06 ,  F02K5/00 ,  F05D2220/323 ,  F05D2220/64 ,  F05D2220/76

Abstract: Propulsion engine (10) comprising at least a first propulsion unit (11) including a first fan (13) encased by a geared ring and a gas turbine engine (15) driving a first shaft (17) connected to the first fan, at least a second propulsion unit (21) including a second fan (23) encased by a geared ring connected to a second shaft (27) operatively coupled to an electric machine (25) and at least an electric storage device (41) connected to it. Said geared rings are configured to transmit torque between the fans so that they can rotate in conjunction (directly or through an intermediate gear) when they are driven by at least one of said first and second shafts. The propulsion engine is arranged for controlling the torque to be supplied to the assembly of the first and second fans by the gas turbine engine and/or by the electric machine acting as a motor or as a generator.

Abstract translation: 至少包括第一推进单元（11）的推进发动机（10），所述第一推进单元（11）包括由齿轮环包围的第一风扇（13）和驱动连接到第一风扇的第一轴（17）的燃气涡轮发动机（15） 第二推进单元（21），包括第二风扇（23），所述第二风扇（23）被连接到可操作地连接到电机（25）的第二轴（27）的齿轮环和至少与其连接的蓄电装置（41）包围。 所述齿轮环构造成在风扇之间传递扭矩，使得当它们被所述第一和第二轴中的至少一个驱动时，它们可以（直接地或通过中间齿轮）一起旋转。 推进发动机布置成用于控制由燃气涡轮发动机和/或用作电动机或发电机的电机供应到第一和第二风扇的组件的扭矩。

公开(公告)号：EP2270326A3

公开(公告)日：2015-02-18

申请号：EP10162389.0

申请日：2010-05-10

Applicant: Rolls-Royce plc

Inventor： Bradbrook, Stephen John

IPC: F02K3/06

CPC classification number: F02K3/04 ,  F02C7/36 ,  F02K5/00 ,  F05D2220/90

Abstract: A propulsive fan system (10) comprises a fan unit (11) comprising a first stage array (12) of rotatable blades (14) upstream of a second stage array (16) of rotatable blades (14). The first stage (12) is coupled to a first drive means (24). The second stage (16) is coupled to a second drive means (26). The first drive means (24) is independently operable of the second drive means (26) during operation of the fan system (10).

公开(公告)号：EP2613033A2

公开(公告)日：2013-07-10

申请号：EP13150123.1

申请日：2013-01-03

Applicant: Hamilton Sundstrand Corporation

Inventor： Ribarov, Lubomir A. ,  Gieras, Jacek F.

IPC: F02C3/067 ,  B64C11/48

CPC classification number: F02C3/067 ,  B64C11/48 ,  F02K3/072 ,  F02K5/00 ,  F05D2260/404 ,  H02K7/14 ,  H02K16/02 ,  Y02T50/66 ,  Y02T50/672

Abstract: A turbomachine (10) comprises a turbine shaft (42), first (36) and second (40) rotors, first (12) and second (14) propulsion stages, and a magnetic stator (38). The first rotor (36) is rotationally coupled to the turbine shaft (42), and coaxially arranged along an axis (C L ). The first propulsion stage (12) is rotationally coupled to the first rotor (36), opposite the turbine shaft (42). The second rotor (40) is coaxially arranged about the first rotor (36), and the second propulsion stage (14) is rotationally coupled to second rotor (40), opposite the turbine shaft (42) and adjacent the first propulsion stage (12). The magnetic stator (38) is coaxially arranged between the first rotor (36) and the second rotor (40), forming a magnetic coupling between the first (36) and second (40) rotors to drive the second propulsion stage (14) in contra-rotation with respect to the first propulsion stage (12).

Abstract translation: 涡轮机（10）包括涡轮轴（42），第一（36）和第二（40）转子，第一（12）和第二（14）推进级以及磁性定子（38）。 第一转子（36）旋转地联接到涡轮轴（42），并且沿着轴线（C L）同轴地布置。 第一推进级（12）与涡轮轴（42）相对旋转地联接到第一转子（36）。 所述第二转子（40）围绕所述第一转子（36）同轴布置，并且所述第二推进级（14）旋转地联接到与所述涡轮轴（42）相对并且邻近所述第一推进级（12）的第二转子（40） ）。 磁性定子（38）同轴地布置在第一转子（36）和第二转子（40）之间，在第一转子（36）和第二转子（40）之间形成磁耦合，以驱动第二推进级 相对于第一推进级（12）的反转。

公开(公告)号：EP2578490A2

公开(公告)日：2013-04-10

申请号：EP12185886.4

申请日：2012-09-25

Applicant: Rolls-Royce plc

Inventor： Brown, Stephen ,  Raffaelli, Lorenzo

IPC: B64C11/00 ,  B64D33/02 ,  B64D29/02

CPC classification number: B64C11/001 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04 ,  F02C7/042 ,  F02K1/09 ,  F02K1/12 ,  F02K5/00

Abstract: This invention relates to a propulsive unit (10) for an aircraft, comprising: a nacelle (12) which defines a duct (20) for channelling an airflow when in use and which provides an outwardly facing surface (14) of the propulsive unit (10), the outwardly facing surface (14) having an aerodynamic shape; a fan unit (16) for accelerating the airflow within the duct (20) when in use; wherein the duct (20) has an inlet (26) and an outlet (28) and the nacelle (12) is operable to adjust the either or both of the area of the inlet (26) and outlet (28) whilst substantially retaining the aerodynamic shape of the outwardly facing surface.

Abstract translation: 本发明涉及一种用于飞行器的推进单元（10），其包括：机舱（12），其限定用于在使用时引导气流并且提供推进单元的向外表面（14）的管道（20） 10），面向外的表面（14）具有空气动力学形状; 风扇单元（16），用于在使用时加速管道（20）内的气流; 其中所述管道（20）具有入口（26）和出口（28），并且所述机舱（12）可操作以调节所述入口（26）和所述出口（28）的所述面积中的一个或两个，同时基本上保持 向外表面的空气动力学形状。

公开(公告)号：EP2270326A2

公开(公告)日：2011-01-05

申请号：EP10162389.0

申请日：2010-05-10

Applicant: Rolls-Royce plc

Inventor： Bradbrook, Stephen John

IPC: F02K1/06 ,  F02K3/06

CPC classification number: F02K3/04 ,  F02C7/36 ,  F02K5/00 ,  F05D2220/90

Abstract: A propulsive fan system (10) comprises a fan unit (11) comprising a first stage array (12) of rotatable blades (14) upstream of a second stage array (16) of rotatable blades (14). The first stage (12) is coupled to a first drive means (24). The second stage (16) is coupled to a second drive means (26). The first drive means (24) is independently operable of the second drive means (26) during operation of the fan system (10).

Abstract translation: 推进式风扇系统（10）包括风扇单元（11），风扇单元（11）包括可旋转叶片（14）的第一级阵列（12），其可旋转叶片（14）的第二级阵列（16）的上游。 第一级（12）耦合到第一驱动装置（24）。 第二级（16）耦合到第二驱动装置（26）。 在风扇系统（10）的操作期间，第一驱动装置（24）可独立地可操作于第二驱动装置（26）。

公开(公告)号：EP1785614A2

公开(公告)日：2007-05-16

申请号：EP06255653.5

申请日：2006-11-02

Applicant: Pratt & Whitney Canada Corp.

Inventor： Dooley, Kevin Allan ,  Youssef, Nashed

IPC: F02C7/268 ,  F02C7/32 ,  F02K1/15 ,  F02K5/00 ,  F01D19/00

CPC classification number: F02C7/268 ,  F01D15/10 ,  F02C7/262 ,  F02C7/32 ,  F02K5/00 ,  F05D2220/76

Abstract: The system is used for taxiing an aircraft and comprises at least one multi-spool gas turbine engine (10), the engine (10) having an electrical motor (30) in a torque-driving engagement with a low pressure spool (22) of the engine (10). The low pressure spool (22) has a propulsor (12) connected thereon to generate thrust when rotated. A controller (34) is connected to the electrical motor (30) and an electrical power source (32) to control an amount of electrical power provided from the power source (32) to the electrical motor (30) so as to drive the propulsor (12) and cause at least a major portion of the thrust to be generated by the propulsor (12) for moving the aircraft during taxiing.

Abstract translation: 该系统用于滑行飞行器并且包括至少一个多线轴燃气涡轮发动机（10），发动机（10）具有电动马达（30），该马达与电动马达（30）的扭矩驱动接合，低压阀芯（22） 发动机（10）。 低压阀芯（22）具有连接在其上的推进器（12），以在旋转时产生推力。 控制器（34）连接到电动机（30）和电源（32），以控制从电源（32）到电动机（30）提供的电力的量，以驱动推进器 （12），并且使推进器（12）产生至少大部分的推力用于在滑行期间移动飞行器。

公开(公告)号：EP1664505A2

公开(公告)日：2006-06-07

申请号：EP04770456.4

申请日：2004-08-30

Applicant: Newton Propulsion Technologies Ltd.

Inventor： ROM, Haim ,  ROM, Guy

IPC: F02C1/00

CPC classification number: F01C11/004 ,  F01C1/20 ,  F01C11/008 ,  F01C21/008 ,  F02C3/055 ,  F02K5/00

Abstract: An engine system is disclosed which comprises a first volumetric device, at least one second volumetric device, and a transmission in engagement with two adjacent volumetric devices. The transmission has a ratio designed to cause the at least one second volumetric device to rotate at a higher angular velocity than the first volumetric device, inducing expansion of a compressible fluid during continuous flow from the first volumetric device to the at least one second volumetric device while performing work.