公开(公告)号：EP4403760A2

公开(公告)日：2024-07-24

申请号：EP24160112.9

申请日：2016-09-02

申请人： Jetoptera, Inc.

发明人： EVULET, Andrei

IPC分类号： F02C3/32

CPC分类号： B64C9/38 ,  B64C15/00 ,  B64C21/00 ,  B64D27/10 ,  B64C21/04 ,  F02K1/36 ,  F02K1/002 ,  F02C3/04 ,  F02C6/04 ,  F05D2220/9020130101 ,  B64D27/18 ,  B64D29/02 ,  B64D33/02 ,  B64D33/04 ,  B64D2033/027320130101 ,  Y02T50/30 ,  Y02T50/40 ,  Y02T50/60 ,  Y02T50/10 ,  B64U30/10 ,  B64U10/25 ,  B64U20/65 ,  B64U50/15

摘要： A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

公开(公告)号：EP3148880A1

公开(公告)日：2017-04-05

申请号：EP15799545.7

申请日：2015-05-22

申请人： Sikorsky Aircraft Corporation

发明人： LAMB, JR. Donald William

IPC分类号： B64D33/04

CPC分类号： B64D33/04 ,  B64C27/04 ,  F02K1/002 ,  F05D2220/329 ,  Y02T50/6765

摘要： An exhaust system for a rotary wing aircraft includes a diffuser located at an airframe of the rotary wing aircraft and operably connected to an engine of the rotary wing aircraft, and a chimney extending upwardly from a diffuser wall. A door is movably positioned at the diffuser to selectively direct an engine exhaust flow through the diffuser or through the chimney. A rotary wing aircraft includes an airframe, a rotor system positioned at the airframe and rotatable about a rotor axis, and an engine operably connected to the rotor system to drive rotation of the rotor system. The aircraft includes an engine exhaust system including a diffuser positioned at the airframe and operably connected to the engine, a chimney extending upwardly from a diffuser wall, and a door positioned at the diffuser to selectively direct an engine exhaust flow through the diffuser or through the chimney.

摘要翻译： 用于旋转翼飞行器的排气系统包括位于旋翼机飞行器的机身处并可操作地连接到旋翼飞机的发动机的扩散器和从扩散壁向上延伸的烟囱。 门可移动地定位在扩散器处，以选择性地引导发动机排气流过扩散器或通过烟囱。 旋转翼飞行器包括机身，位于机身处并可围绕转子轴线旋转的转子系统，以及可操作地连接到转子系统以驱动转子系统的旋转的发动机。 该飞机包括发动机排气系统，该发动机排气系统包括位于机身处并可操作地连接到发动机的扩散器，从扩散器壁向上延伸的烟囱以及位于扩散器处的门，以选择性地引导发动机排气流过扩散器或通过 烟囱。

公开(公告)号：EP1918563B1

公开(公告)日：2016-03-09

申请号：EP07253231.0

申请日：2007-08-16

申请人： United Technologies Corporation

发明人： Farah, Jorge I. ,  Cintron, Jose ,  Hickman, Jason

IPC分类号： F02K1/82 ,  F02K1/80

CPC分类号： F02K1/822 ,  F02K1/002 ,  F02K1/04 ,  F02K1/80 ,  F02K1/82 ,  F02K1/825 ,  F05D2220/328 ,  F05D2220/90 ,  F05D2230/64 ,  F05D2260/30 ,  Y02T50/671 ,  Y02T50/675

公开(公告)号：EP2659118A1

公开(公告)日：2013-11-06

申请号：EP11853835.4

申请日：2011-12-24

申请人： Rolls-Royce North American Technologies, Inc.

发明人： LERG, Bryan, Henry

IPC分类号： F02K1/40

CPC分类号： F02K1/28 ,  F02K1/002 ,  F02K1/008 ,  F05D2250/713 ,  F05D2270/18

摘要： One embodiment of the present invention is a unique flight vehicle. Another embodiment is a unique propulsion system. Another embodiment is a unique thrust vectoring system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for flight vehicles, propulsion systems and thrust vectoring systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.

公开(公告)号：EP2239428A3

公开(公告)日：2013-09-11

申请号：EP10158248.4

申请日：2010-03-29

申请人： General Electric Company

发明人： Merchant, Laxmikant ,  Rajesh, Prabhakaran Saraswathi

IPC分类号： F01D25/30 ,  F02K1/00

CPC分类号： F01D25/30 ,  B64D33/04 ,  B64D33/06 ,  F02K1/002 ,  F05D2210/42 ,  F05D2260/97 ,  Y02T50/671

摘要： An exhaust system for gas turbine engine (12) is provided that reduces turbulence and backflow within the exhaust system and, thus, increases the efficiency of the turbine engine (12). In various embodiments, the system includes an exhaust plenum (32) that provides a gradual expansion of the exhaust gases. The exhaust plenum (32) may also include one or more flow splitters (84, 130) that further reduce turbulence in the plenum or symmetrical arrangements and provide a more uniform gas flow in the plenum and other downstream exhaust components.

公开(公告)号：EP1956224A3

公开(公告)日：2011-09-07

申请号：EP08250456.4

申请日：2008-02-07

申请人： United Technologies Corporation

发明人： Baran, Kenneth C.

IPC分类号： F02K1/00 ,  F02K1/12

CPC分类号： F02K3/06 ,  F02K1/002 ,  F02K1/1207 ,  Y10T74/2101

摘要： A fan variable area nozzle (FVAN) (42) includes a flap assembly which varies a fan nozzle exit area through a cam drive ring (58). The flap assembly generally includes a multiple of flaps (50), flap linkages (52) and an actuator system (54). The actuator system (54) rotationally translates the cam drive ring (58) relative an engine centerline axis which results in a follower of the flap linkage (52) following a cam surface (86) to pivot each flap (50) such that the flap assembly dilates about the circumferential hinge line. Rotation of the cam drive ring (58) adjusts dilation of the entire fan nozzle exit area in a symmetrical manner. Another cam drive ring (58' Fig 5A) includes a multiple of movable cams (84) which engages the follower of the flap linkage (52) of each flap (50) such that pivotable movement of a particular number of the multiple of movable cams (84) about a respective cam pivot results in vectoring of the FVAN (42).

公开(公告)号：EP2157306A2

公开(公告)日：2010-02-24

申请号：EP09168405.0

申请日：2009-08-21

申请人： Lockheed Martin Corporation (Maryland Corp.)

发明人： Boespflug, Matthew Patrick ,  Steenburgh, Dennis ,  Saddoughi, Seyed Gholami ,  Bennett, Grover Andrew

IPC分类号： F02K7/02

CPC分类号： F02C5/02 ,  F02K1/002 ,  F02K1/28 ,  F02K7/075 ,  F05D2240/40 ,  F05D2250/311 ,  F05D2260/16 ,  F05D2270/18 ,  F23R7/00 ,  Y02T50/671

摘要： Pulse detonation/deflagration apparatus (30, 30') for providing enhanced pressure wave operating frequency and/or magnitude, and methods of increasing the frequency or the magnitude of deflagration to detonation waves (37), are provided. A pulse detonation/deflagration apparatus (30, 30') can include a main/outer pulse detonation/deflgration actuator/engine (31) with multiple smaller internal combustion chambers or tubes (33) positioned inside the cavity of the main/outer actuator/engine (31) with each performing the function of individual pulse detonation/deflagration actuator/engines (31), The output pressure waves (37) created by the internal combustion chambers or tubes (33) can be utilized for propulsion or for controlling large scale flows, where needed.

公开(公告)号：EP1256705B1

公开(公告)日：2006-05-03

申请号：EP02253254.3

申请日：2002-05-09

申请人： GENERAL ELECTRIC COMPANY

发明人： Ausdenmoore, Robert Michael ,  Renggli, Bernard James

IPC分类号： F02K1/12

CPC分类号： F02K1/002 ,  Y02T50/671

公开(公告)号：EP0882647B1

公开(公告)日：2005-07-27

申请号：EP98109745.4

申请日：1998-05-28

申请人： Boeing North American, Inc.

发明人： Hollowell, Steven J. ,  Robinson, Michael R.

IPC分类号： B64C39/00 ,  B64C25/00 ,  F02K1/00 ,  B64C15/02

CPC分类号： F02K1/002 ,  B64C15/02 ,  B64C25/001 ,  B64C2025/005 ,  Y02T50/671

公开(公告)号：EP1240420B1

公开(公告)日：2005-05-11

申请号：EP00989152.4

申请日：2000-12-22

申请人： SAAB AB

发明人： BERGLUND, Hans ,  WEILAND, Carleric

IPC分类号： F02K1/40 ,  F02K9/97

CPC分类号： F02K1/002 ,  F02K1/008 ,  F02K1/1207

摘要： An outlet device for a jet engine (2) includes an outlet channel (3), which has an upstream end (3') for being connected to the jet engine and a downstream end (3'') and which defines a main flow direction (a) for a jet from the jet engine. The outlet channel has in the proximity of the downstream end an elongated shape, seen in a section across the flow direction, and includes at least two outlet portions (4, 5, 6), which are separated from each other, for a respective outlet flow of said jet. A first outlet portion (5, 6) includes means for controlling the outlet direction of the outlet flow in a first plane and a second outlet portion (4) includes means for controlling the outlet direction of the outlet flow in a second plane, which forms an angle to the first plane. An aircraft may include such an outlet device.