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1. 发明授权

EP4028667B1 MANTELSTROMTRIEBWERK MIT MINDESTENS EINER DREHMOMENTSTUFE 有权
公开(公告)号：EP4028667B1
公开(公告)日：2024-10-30
申请号：EP20772240.6
申请日：2020-09-09
IPC分类号： F04D29/32
CPC分类号： B64C27/20 , B64D33/02 , B63H5/10 , B63H5/14 , B63H1/16 , F02K3/077 , F02K3/072 , F02K3/068 , F04D29/324 , F04D19/024 , B64C11/001 , B64C11/48 , B64C37/00 , B64C29/0033

2. 发明授权

EP3088720B1 Nozzle for jet engines 有权
公开(公告)号：EP3088720B1
公开(公告)日：2018-09-12
申请号：EP16166208.5
申请日：2016-04-20
申请人： Rolls-Royce North American Technologies, Inc.
发明人： PESYNA, Kenneth M.
IPC分类号： F02K1/12 , F02K3/077 , F02K3/075
CPC分类号： F02K1/12 , F02C3/04 , F02K1/123 , F02K3/06 , F02K3/075 , F02K3/077 , F05D2220/32 , F05D2240/128
摘要： An exhaust system or nozzle for use in a gas turbine engine is disclosed herein. The exhaust system is adapted to adjust various streams of pressurized air produced by the gas turbine engine to control operation of the gas turbine engine.

3. 发明公开

EP2574758A3 Conformal inlet apparatus for a gas turbine engine 审中-公开
公开(公告)号：EP2574758A3
公开(公告)日：2018-08-01
申请号：EP12186257.7
申请日：2012-09-27
申请人： General Electric Company
发明人： Powell, Brandon Flowers , Tersmette, Trevor Andrew , Spencer, Craig Bradley
IPC分类号： F02C7/04 , F02K3/06 , F02K3/077 , F02K3/075
CPC分类号： F02C7/04 , F02K3/075 , F02K3/077 , Y02T50/671 , Y10T137/0536
摘要： An inlet apparatus for a gas turbine engine includes: a fan duct adapted to surround at least one row of rotating fan blades, the fan duct having a circular frontal area, and defining a first inlet plane; and an outer duct surrounding the fan duct, the outer duct including: a first frontal area shape at the first inlet plane which defines, cooperatively with an exterior of the fan duct, at least one lobe through which air can pass; and a second frontal area shape at a second inlet plane located axially downstream from the forward end which is circular, and which defines, cooperatively with an exterior of the fan duct, an annulus through which air can pass.

4. 发明授权

EP1597472B1 CONFLUENT EXHAUST NOZZLE 有权
公开(公告)号：EP1597472B1
公开(公告)日：2018-06-20
申请号：EP04785726.3
申请日：2004-02-19
申请人： THE NORDAM GROUP, Inc.
发明人： LAIR, Jean-Pierre
IPC分类号： F02K3/02 , F02K1/38 , F02K3/077 , F02K3/06 , F02K1/34 , F02K1/46 , F02K1/70 , F02K1/06
CPC分类号： F02K1/06 , F02K1/34 , F02K1/46 , F02K1/70 , F02K3/06 , F02K3/077
摘要： A gas turbine engine exhaust nozzle includes a nacelle having an inlet and main outlet at opposite ends, and a main duct extending therebetween. A secondary bypass duct extends radially through the nacelle upstream of the main outlet and includes an unobstructed secondary inlet joined to the main duct, and a secondary outlet surrounding the main outlet for collectively discharging exhaust flow in confluent streams.

5. 发明公开

EP3318742A1 INTERCOOLED COOLING AIR HEAT EXCHANGER ARRANGEMENT 有权转让
标题翻译：中冷空气热交换器安装
公开(公告)号：EP3318742A1
公开(公告)日：2018-05-09
申请号：EP17200678.5
申请日：2017-11-08
申请人： United Technologies Corporation
发明人： STAUBACH, Joseph B. , SNAPE, Nathan
IPC分类号： F02K3/077 , F02C7/18
CPC分类号： F02C7/185 , F02C3/04 , F02C9/18 , F02K3/077 , F05D2220/32 , F05D2260/212 , F05D2260/213 , Y02T50/675
摘要： An intercooled cooling system (100;200;300) for a gas turbine engine (20) is provided. The intercooled cooling system includes a plurality of cooling stages (110,115;210,215;310,315) in fluid communication with an air stream utilized for cooling. A first cooling stage (110;210;310) of the plurality of cooling stages is fluidly coupled to a bleed port (145) of a compressor of the gas turbine engine to receive and cool bleed air with the air stream to produce a cool bleed air. The intercooled cooling system also includes a pump (105) fluidly coupled to the first cooling stage (110;210;310) to receive the cool bleed air and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage (115;215;315) of the plurality of cooling stages is fluidly coupled to the pump (105) to receive and cool the pressurized cool bleed air to produce an intercooled cooling air, which is provided to the gas turbine engine (20).
摘要翻译：提供了用于燃气涡轮发动机（20）的中间冷却系统（100; 200; 300）。中冷冷却系统包括与用于冷却的空气流体流体连通的多个冷却级（110,115; 210,215; 310,315）。多个冷却级中的第一冷却级（110; 210; 310）流体联接到燃气涡轮发动机的压缩机的排放端口（145），以接收和冷却排放的空气与空气流，以产生冷排放空气。中冷冷却系统还包括与第一冷却级（110; 210; 310）流体连接的泵（105），以接收冷的放气并增加冷放气的压力以产生加压的冷放气。多个冷却级中的第二冷却级（115; 215; 315）流体联接至泵（105）以接收并冷却加压的冷抽气以产生中冷冷却空气，该冷空气被提供至燃气涡轮发动机（20）。

7. 发明授权

EP2009262B1 Gas turbine with multiple gas flow paths 有权转让
公开(公告)号：EP2009262B1
公开(公告)日：2017-05-03
申请号：EP08251270.8
申请日：2008-03-31
申请人： United Technologies Corporation
发明人： Kupratis, Daniel B.
IPC分类号： F02C7/36 , F02K3/077
CPC分类号： F02C7/36 , F02K3/077

8. 发明公开

EP2984316A4 GEARED ANNULAR AIRFLOW ACTUATION SYSTEM FOR VARIABLE CYCLE GAS TURBINE ENGINES 有权转让
标题翻译：环形齿气流控制系统与可变循环燃气涡轮发动机
公开(公告)号：EP2984316A4
公开(公告)日：2016-06-01
申请号：EP14839244
申请日：2014-02-05
申请人： UNITED TECHNOLOGIES CORP
发明人： IZQUIERDO FELIX
IPC分类号： F02C7/057 , F02C7/042 , 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.

9. 发明公开

EP2998558A1 Multi-fan engine with an enhanced power transmission 有权
标题翻译：多风扇马达mit verbesserterKraftübertragung
公开(公告)号：EP2998558A1
公开(公告)日：2016-03-23
申请号：EP14382350.8
申请日：2014-09-17
申请人： Airbus Operations, S.L.
发明人： Bailey Noval, Nicolás , Llamas Sandín, Raúl
IPC分类号： F02K3/06 , F02K3/077 , F02C7/36
CPC分类号： F02C3/107 , F02C7/36 , F02K3/06 , F02K3/077 , F05D2220/32 , F05D2260/4031 , F16H1/20
摘要： A multi-fan engine comprising a gas turbine engine (11), a casing (17) and a plurality of fans (15) encased by geared rings (31) and connected mechanically to adjacent fans so that the power generated by the gas turbine engine (11) is transmitted through a shaft (13) to one of the fans which distributes the power to its adjacent fans through the geared connection. An alternative embodiment includes intermediate gears (33) connecting adjacent fans which can be retracted by the action of linear actuators (34) disengaging thereby the mechanical connection between fans (15). The invention also refers to an aircraft provided with fuselage-mounted multi-fan engines (10) arranged so that the boundary layer airflow is captured by the fans.
摘要翻译：一种多风扇发动机，包括燃气涡轮发动机（11），壳体（17）和由齿轮环（31）包围的多个风扇（15），并且机械地连接到相邻的风扇，使得由燃气涡轮发动机（11）通过轴（13）传递到通过齿轮连接将动力分配到其相邻风扇的风扇之一。替代实施例包括连接相邻风扇的中间齿轮（33），其可以通过线性致动器（34）的作用而缩回，从而使风扇（15）之间的机械连接脱离。本发明还涉及一种设置有机身安装的多风扇发动机（10）的飞行器，其布置成使得边界层气流被风扇捕获。

10. 发明授权

EP2580121B1 NACELLE DE TURBOREACTEUR 有权
标题翻译：涡喷GONDEL
公开(公告)号：EP2580121B1
公开(公告)日：2016-03-09
申请号：EP11735460.5
申请日：2011-06-09
申请人： Aircelle
发明人： BOUTEILLER, Xavier , BLIN, Laurent Albert
IPC分类号： F02K3/077 , F02K1/34 , F02C9/18 , F02C7/045 , F02C3/13 , B64D33/02
CPC分类号： F02K1/34 , B64D33/02 , B64D2033/0206 , B64D2033/0286 , F02C3/13 , F02C7/045 , F02C9/18 , F02K3/077 , F05D2260/96 , Y02T50/672

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