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1. 发明授权

EP1992807B1 Variable geometry nacelle for an aircraft engine and corresponding operating method 有权转让
标题翻译：缆车与用于飞机发动机的可变几何形状和操作方法对应
公开(公告)号：EP1992807B1
公开(公告)日：2016-09-07
申请号：EP08251734.3
申请日：2008-05-16
申请人： United Technologies Corporation
发明人： Jain, Ashok K.
IPC分类号： F02C7/042 , F02K3/06 , F02K1/42 , F02K3/077
CPC分类号： F02C7/042 , B64D33/02 , B64D2033/0226 , B64D2033/0286 , F02K1/42 , F02K3/06 , F02K3/077 , Y10T137/0536

2. 发明授权

EP2061964B1 TURBOFAN ENGINE HAVING INNER FIXED STRUCTURE INCLUDING DUCTED PASSAGES 有权转让
标题翻译：用铁丝经文风力发电厂在内部结构坚固
公开(公告)号：EP2061964B1
公开(公告)日：2015-03-04
申请号：EP06816748.5
申请日：2006-10-12
申请人： United Technologies Corporation
发明人： KOHLENBERG, Gregory, A.
IPC分类号： F01D17/10 , B64D33/02 , F02K3/075 , F02K1/42 , F02K1/06 , F02K1/12 , F02K1/62
CPC分类号： F02K1/1207 , B64D2033/024 , F01D17/105 , F02K1/06 , F02K1/42 , F02K1/62 , F02K3/075

3. 发明公开

EP2061964A1 TURBOFAN ENGINE HAVING INNER FIXED STRUCTURE INCLUDING DUCTED PASSAGES 有权转让
标题翻译：用铁丝经文风力发电厂在内部结构坚固
公开(公告)号：EP2061964A1
公开(公告)日：2009-05-27
申请号：EP06816748.5
申请日：2006-10-12
申请人： United Technologies Corporation
发明人： KOHLENBERG, Gregory, A.
IPC分类号： F02K3/075 , F02K3/077 , F02K1/12 , F02K1/42
CPC分类号： F02K1/1207 , B64D2033/024 , F01D17/105 , F02K1/06 , F02K1/42 , F02K1/62 , F02K3/075
摘要： A gas turbine engine system includes a fan bypass passage (27), a core nacelle (28) having an inner fixed structure (40) within the fan bypass passage, a passage (42) extending through the inner fixed structure, and a duct nozzle (48). The passage includes an inlet (44) for receiving a fan airflow (F2) from the fan bypass passage and an outlet (46) for discharging the fan airflow. The duct nozzle includes a variable cross-sectional exit area (50) for controlling the fan airflow within the passage and is selectively moveable to influence the variable cross-sectional exit area.

4. 发明公开

EP1367249A1 Deployable segmented exhaust nozzle for a jet engine 有权
标题翻译： Entraaltbare segmentierteAbgasdüsefürein Strahltriebwerk
公开(公告)号：EP1367249A1
公开(公告)日：2003-12-03
申请号：EP03076298.3
申请日：2003-05-01
申请人： THE BOEING COMPANY
发明人： Nesbitt, Eric H. , Butler, G. W. , Reed, David H.
IPC分类号： F02K1/38 , F02K1/42 , F02K1/46 , F02K1/48
CPC分类号： F02K1/48 , F02K1/46 , F05D2300/505 , Y02T50/672
摘要： An exhaust flow nozzle for a jet engine having a plurality of flow altering components extending from a lip portion of a secondary exhaust nozzle that are movable between first and second positions. In the first position the flow altering components are disposed substantially parallel to an exhaust gas flow path and thereby do not produce drag or a reduction of thrust from the engine. In the second position the flow altering components bend or are deformed to project into the exhaust gas flow path exiting from the secondary exhaust nozzle. The flow altering components are comprised of a shape-memory alloy material which deforms in response to heat. One or more additional layers of material are bonded or otherwise coupled to the shape-memory alloy layer of each flow altering component to assist in returning the shape-memory alloy layer to its unheated shape.
摘要翻译：一种用于喷气发动机的排气流动喷嘴，具有从第二和第二位置可移动的二次排气喷嘴的唇部延伸的多个流动变化部件。在第一位置，流动改变部件基本上平行于废气流动路径设置，从而不产生来自发动机的阻力或减小推力。在第二位置，流动改变部件弯曲或变形以伸入从二次排气喷嘴排出的废气流动路径。流动变化部件包括响应于热而变形的形状记忆合金材料。一个或多个另外的材料层被粘合或以其他方式耦合到每个流动改变部件的形状记忆合金层，以帮助将形状记忆合金层返回到其未加热的形状。

5. 发明授权

EP3180506B1 EXHAUST ARRANGEMENT FOR AIRCRAFT HAVING SENSOR 有权
公开(公告)号：EP3180506B1
公开(公告)日：2019-05-01
申请号：EP15832217.2
申请日：2015-08-14
申请人： Mcgee, Craig S. , Fritcher, Sam R.
发明人： Mcgee, Craig S. , Fritcher, Sam R.
IPC分类号： F02K1/00 , F02K1/42 , F02K1/52 , B64D33/04

6. 发明公开

EP3180506A1 EXHAUST ARRANGEMENT FOR AIRCRAFT HAVING SENSOR 有权
标题翻译：具有传感器的飞机的排气装置
公开(公告)号：EP3180506A1
公开(公告)日：2017-06-21
申请号：EP15832217.2
申请日：2015-08-14
申请人： Mcgee, Craig S. , Fritcher, Sam R.
发明人： Mcgee, Craig S. , Fritcher, Sam R.
IPC分类号： F02K1/00 , F02K1/42 , F02K1/52
CPC分类号： B64D33/04 , B64D27/14 , B64D47/08 , F01D25/30 , F02K1/78
摘要： An exhaust arrangement is for an aircraft having sensing equipment and a front prop engine. An extension mounts on the underside along an edge of the fuselage to direct exhaust from the engine's exhaust pipes to a point to or past the sensing equipment typically exposed at the mid-section of the aircraft. An extension inlet mounts adjacent the pipe and defines a funnel or conical orifice not directly affixed to the pipe. One or more conductors for the extension then extend from the inlet to convey the exhaust to an outlet of the extension. Preferably, multiple conductors can be used with an expansion joint provided between them. The outlet preferably diverts exhaust away from the tail end of the aircraft. To mount the extension to the aircraft, several arrangements of supports including rods, lugs, angles, and the like hold the extension in vertical, lateral, and axial directions to the aircraft.
摘要翻译：排气装置用于具有感测设备和前支柱发动机的飞机。延伸部分安装在机身边缘的下侧，以将排气从发动机的排气管引导至或通过通常暴露在飞机中部的传感设备的点。延伸入口安装在管道附近，并确定了不直接固定在管道上的漏斗或锥形孔口。用于延伸部的一个或多个导体然后从入口延伸以将排气传送到延伸部的出口。优选地，多个导体可以与设置在它们之间的膨胀接头一起使用。出口优选地将排气从飞机的尾端转移开。为了将延伸部分安装到飞机上，包括杆，凸耳，角度等在内的多种支撑装置将飞行器的垂直，横向和轴向方向上的延伸部分保持住。

7. 发明授权

EP2157305B1 Gas turbine engine with variable area fan nozzle 有权转让
标题翻译：具有可变风扇喷嘴的燃气涡轮发动机
公开(公告)号：EP2157305B1
公开(公告)日：2014-02-26
申请号：EP09251654.1
申请日：2009-06-26
申请人： United Technologies Corporation
发明人： Zamora, Sean P. , Murphy, Michael Joseph
IPC分类号： F02K1/42 , F02K1/46 , F02K1/82 , F02K3/075 , F02K3/077
CPC分类号： F02K3/077 , F02K1/42 , F02K1/46 , F02K1/825 , F02K3/075

8. 发明公开

EP2074319A1 GAS TURBINE ENGINE WITH A VARIABLE EXIT AREA FAN NOZZLE, NACELLE ASSEMBLY OF SUCH A ENGINE, AND CORRESPONDING OPERATING METHOD 有权转让
标题翻译：具有可变吹塑喷嘴出口横截面，GONDEL布置，例如发电设备的涡轮机和相应的工作方法
公开(公告)号：EP2074319A1
公开(公告)日：2009-07-01
申请号：EP06825870.6
申请日：2006-10-12
申请人： United Technologies Corporation
发明人： BALTAS, Constantine , HAUSER, Joseph R.
IPC分类号： F02K1/50 , F02K1/70 , F02K1/42
CPC分类号： F02K1/70 , F02K1/42 , F02K1/50
摘要： A turbofan engine includes a fan variable area nozzle having a multiple of vents through a fan nacelle and a sleeve system movable relative to the vents by an actuator system. The fan variable area nozzle changes the effective area of the fan nozzle exit area to permit efficient operation at predefined pressure ratios. The vents include a grid structure which directs and smoothes the airflow therethrough as well as to reduce noise generation.

9. 发明公开

EP0868596A4 SOUND SUPPRESSOR EXHAUST STRUCTURE 失效
标题翻译：排气消声器
公开(公告)号：EP0868596A4
公开(公告)日：2000-04-19
申请号：EP97945166
申请日：1997-05-13
申请人： NORTHROP GRUMMAN CORP
发明人： RALPH C JR , BARD WILLIAM D , SCHEIN DAVID B
IPC分类号： F01N1/08 , F02K1/42 , F02K1/82 , F01N1/14 , F02K1/40
CPC分类号： F02K1/42 , F02K1/827 , Y02T50/671
摘要： A sound suppressor exhaust structure (10) for a jet engine. The exhaust structure has a nozzle body (12) having a generally cylindrical forward intake opening (14) to accomodate an aft end of a jet engine, and a generally quadrilateral aft exit opening (16). An openable sound suppression chamber is situated aft of the exit opening and is formed by two opposing enclosure structures (18, 20) each having a major surface (22, 24) and each hingedly attached in a clamshell manner to the nozzle body (12). The opening enclosure structures (18, 20) are indefinitely movable between an open and a closed configuration such that, when the enclosure structures (18, 20) are closed, a chamber having a generally quadrilateral cross section is defined and situated aft of the exit opening. Each enclosure structure (18, 20) has a major surface (22, 24) through which are substantially uniformly disposed a plurality of small apertures (38) such that from about 15 % to about 25 % per square foot of each major surface is void and from about 45 to 65 apertures are provided per square foot. The apertures (38) here defined are small and tightly spaced to thereby beneficially result in agressive noise suppression as well as structural light weight.

10. 发明授权

EP2938867B1 FLOW DIVERTER TO REDIRECT SECONDARY FLOW 有权转让
公开(公告)号：EP2938867B1
公开(公告)日：2020-04-22
申请号：EP13867393.4
申请日：2013-12-17
申请人： United Technologies Corporation
发明人： CHUONG, Conway , CARELLA, John, A.
IPC分类号： F02C7/28 , F02K1/42 , F01D5/08 , F01D9/06 , F01D11/00

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