公开(公告)号：EP2215341B1

公开(公告)日：2018-07-11

申请号：EP08842021.1

申请日：2008-10-24

申请人： Gulfstream Aerospace Corporation

发明人： CONNERS, Timothy, R.

IPC分类号： F02C7/04

CPC分类号： B64D33/02 ,  B64D29/00 ,  B64D33/06 ,  B64D2033/026 ,  B64D2033/0273 ,  F02C7/042 ,  F02C7/045 ,  F02K3/025 ,  F02K7/16 ,  F05D2220/80 ,  Y02T50/672 ,  Y10T137/0368 ,  Y10T137/0536

摘要： A supersonic inlet with a cowl lip may be configured to capture the conic shock and exhibit a zero or substantially zero cowl angle. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a supersonic aircraft while allowing for an increase in engine pressure recovery and a subsequent improvement in generated thrust by the engine.

公开(公告)号：EP2233727B1

公开(公告)日：2017-12-13

申请号：EP10250566.6

申请日：2010-03-25

申请人： United Technologies Corporation

发明人： Jarmon, David C.

IPC分类号： F02K7/10 ,  F01D25/08 ,  F02K1/82 ,  F02K9/64 ,  F02K9/97 ,  F02K7/16 ,  F02K7/14 ,  F02C6/18 ,  F01D13/00 ,  B64D33/02 ,  B64C30/00 ,  F02C7/224 ,  B64D37/34 ,  B64D33/08

CPC分类号： F02K7/14 ,  B64C30/00 ,  B64D33/08 ,  B64D37/34 ,  B64D2033/026 ,  F01D13/00 ,  F02C6/18 ,  F02C7/224 ,  F02K1/822 ,  F02K7/16 ,  F02K9/64 ,  F02K9/972 ,  F05D2220/80 ,  F05D2250/15 ,  F05D2260/205 ,  F05D2260/38 ,  F05D2260/52 ,  Y02T50/44

摘要： An apparatus includes a thermoelectric (TE) device (82), a gas flow conduit (80) proximate to one side of the thermoelectric device, a plurality of flexible tubes (84) proximate to a second side of the thermoelectric device, and a spring (86) to control contact force between the flexible tubes and the thermoelectric device. The spring comprises a coil spring at least partially circumscribing the gas flow conduit. The thermoelectric device converts a temperature differential between the flexible tubes and the gas flow conduit into electrical energy.

公开(公告)号：EP2084061B1

公开(公告)日：2016-12-14

申请号：EP07873759.0

申请日：2007-10-10

申请人： Aerion Corporation

发明人： CHASE, James, D. ,  GARZON, German, Andres

IPC分类号： B64C30/00

CPC分类号： B64C30/00 ,  B64D27/20 ,  B64D29/04 ,  B64D33/02 ,  B64D2033/026 ,  Y02T50/44

公开(公告)号：EP2703624B1

公开(公告)日：2016-11-09

申请号：EP12777288.7

申请日：2012-04-28

申请人： Otkrytoe Akcionernoe Obschestvo Aviacionnaya Holdingovaya Kompaniya Suhoi

发明人： DAVIDENKO, Aleksandr Nikolaevich ,  STRELETS, Mihail Yurievich ,  RUNISHEV, Vladimir Aleksandrovich ,  BIBIKOV, Sergey Yurievich ,  POLYAKOVA, Natalya Borisovna ,  SUTSKEVER, Anatoly Isaakovich ,  KOSITSIN, Aleksandr Anatolevich ,  GAVRIKOV, Andrey Yurievich ,  STEPANOV, Vladimir Alekseevich

IPC分类号： F02C7/042 ,  B64D33/02 ,  F02C7/057

CPC分类号： F02C7/042 ,  B64D33/02 ,  B64D2033/026 ,  F02C7/057 ,  F05D2220/80 ,  Y10T137/0536

公开(公告)号：EP2744995A4

公开(公告)日：2015-04-29

申请号：EP12825921

申请日：2012-08-17

申请人： GULFSTREAM AEROSPACE CORP

发明人： CONNERS TIMOTHY R ,  HENNE PRESTON A ,  HOWE DONALD C

IPC分类号： F02C7/04 ,  B64D33/02 ,  F02K1/04 ,  F02K1/46 ,  F02K3/02

CPC分类号： F02K1/46 ,  B64D33/02 ,  B64D2033/026 ,  B64D2033/0273 ,  B64D2033/0286 ,  F02C7/00 ,  F02C7/04 ,  F02C7/045 ,  F02K1/04 ,  F02K1/34 ,  F02K3/02 ,  F02K7/00 ,  F02K7/10 ,  F02K7/16 ,  F02K7/20 ,  F05D2210/12 ,  F05D2220/323 ,  F05D2220/80 ,  F05D2230/60 ,  F05D2250/70 ,  F05D2260/96 ,  Y10T29/49346 ,  Y10T137/0536

摘要： An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.

公开(公告)号：EP2215341A4

公开(公告)日：2012-10-24

申请号：EP08842021

申请日：2008-10-24

申请人： GULFSTREAM AEROSPACE CORP

发明人： CONNERS TIMOTHY R

IPC分类号： F02C7/04

CPC分类号： B64D33/02 ,  B64D29/00 ,  B64D33/06 ,  B64D2033/026 ,  B64D2033/0273 ,  F02C7/042 ,  F02C7/045 ,  F02K3/025 ,  F02K7/16 ,  F05D2220/80 ,  Y02T50/672 ,  Y10T137/0368 ,  Y10T137/0536

摘要： A supersonic inlet with a cowl lip may be configured to capture the conic shock and exhibit a zero or substantially zero cowl angle. The inlet may be configured to employ a relaxed isentropic compression surface and an internal bypass. The nacelle bypass may prevent flow distortions, introduced by the capture of the conic shock, from reaching the turbomachinery, thereby allowing the cowl angle to be reduced to zero or substantially zero. Such a cowl angle may reduce the inlet's contribution to the overall sonic boom signature for a supersonic aircraft while allowing for an increase in engine pressure recovery and a subsequent improvement in generated thrust by the engine.

公开(公告)号：EP2233727A2

公开(公告)日：2010-09-29

申请号：EP10250566.6

申请日：2010-03-25

申请人： United Technologies Corporation

发明人： Jarmon, David C.

IPC分类号： F02K7/10 ,  F01D25/08

CPC分类号： F02K7/14 ,  B64C30/00 ,  B64D33/08 ,  B64D37/34 ,  B64D2033/026 ,  F01D13/00 ,  F02C6/18 ,  F02C7/224 ,  F02K1/822 ,  F02K7/16 ,  F02K9/64 ,  F02K9/972 ,  F05D2220/80 ,  F05D2250/15 ,  F05D2260/205 ,  F05D2260/38 ,  F05D2260/52 ,  Y02T50/44

摘要： An apparatus includes a thermoelectric (TE) device (82), a gas flow conduit (80) proximate to one side of the thermoelectric device, a plurality of flexible tubes (84) proximate to a second side of the thermoelectric device, and a spring (86) to control contact force between the flexible tubes and the thermoelectric device. The spring comprises a coil spring at least partially circumscribing the gas flow conduit. The thermoelectric device converts a temperature differential between the flexible tubes and the gas flow conduit into electrical energy.

公开(公告)号：EP2084061A2

公开(公告)日：2009-08-05

申请号：EP07873759.0

申请日：2007-10-10

申请人： Aerion Corporation

发明人： CHASE, James, D. ,  GARZON, German, Andres

IPC分类号： B64C30/00

CPC分类号： B64C30/00 ,  B64D27/20 ,  B64D29/04 ,  B64D33/02 ,  B64D2033/026 ,  Y02T50/44

摘要： Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following X0) a region just ahead of the lip X1) substantially to said lip. A non-uniform shock system is created that generates a central region of nearly isentropic compression and relatively ram recovery and an outer region of reduced ram recovery but entailing reduced cowl angle and drag. Translating cowl structure and also nozzle integration with the fuselage contour to reduce boat tail drag are also provided.

公开(公告)号：EP1243782A3

公开(公告)日：2005-03-02

申请号：EP02075713.4

申请日：2002-02-22

申请人： THE BOEING COMPANY

发明人： Seidel, Gerhard E.

IPC分类号： F02K1/38 ,  F02C7/04 ,  B64D33/02

CPC分类号： F02C7/04 ,  B64C2039/105 ,  B64D33/02 ,  B64D2033/026 ,  F02K3/04 ,  Y02T50/12

摘要： A dual boundary layer engine inlet for a turbofan propulsion engine of an aircraft having a first air inlet positioned generally within the boundary layer flowing around the exterior surface of the aircraft. A first passageway fluidly interconnects the first air inlet and the turbofan propulsion engine to provide air from the boundary layer to the bypass to reduce aerodynamic drag. A second air inlet is positioned generally outside of the boundary layer. This second passageway fluidly interconnecting the second air inlet and the turbofan propulsion engine to provide air outside of the boundary layer to the core and compressor of the turbofan engine to maintain engine efficiency.

公开(公告)号：EP1351855A2

公开(公告)日：2003-10-15

申请号：EP02736479.3

申请日：2002-01-17

申请人： The Boeing Company

发明人： NELSON, Chester P.

IPC分类号： B64C15/00

CPC分类号： B64C1/0009 ,  B64C1/26 ,  B64C3/10 ,  B64C3/32 ,  B64C30/00 ,  B64C39/12 ,  B64C2001/0045 ,  B64C2211/00 ,  B64D27/18 ,  B64D29/02 ,  B64D2033/026 ,  Y02T50/12 ,  Y02T50/44

摘要： An integrated and modular high-speed aircraft (200) and method of design and manufacture. The aircraft (200) can have a supersonic or near-sonic cruise Mach number. In one embodiment, the aircraft (200) can include an aft body integrated with a delta wing (204) and a rearwardly-tapering fuselage (202) to define a smooth forward-to-rear area distribution. A propulsion system (206), including an engine (216), inlet (220), and exhaust nozzle (222) can be integrated into the aft body to be at least partially hidden behind the wing (204). In one embodiment, the entrance of the inlet can be positioned beneath the wing (204), and the exit of the nozzle (222) can be positioned at or above the wing (204). An S-shaped inlet duct (221) can deliver air to the aft-mounted integrated engine.

摘要翻译： 集成和/或模块化高速飞机及其设计和制造方法。 飞机可以具有超音速或近声波巡航马赫数。 在一个实施例中，飞行器可以包括与三角翼和向后渐缩的机身一体化的后体，以限定顺利的前后区域分布。 包括发动机，入口和排气喷嘴的推进系统可以集成到后体中至少部分地隐藏在机翼后面。 在一个实施例中，入口的入口可以定位在机翼的下方，并且喷嘴的出口可以定位在机翼上方或上方。 S形入口管道可以将空气输送到后部安装的集成发动机。 飞机可以包括安装在后面的电梯，机翼安装的电梯和用于俯仰控制的前置安装的卡车。 飞机的构造可以是模块化的，以利用近声和超音速结构之间的共同点。