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1. 发明申请

US20180230909A1 CERAMIC MATRIX COMPOSITE TURBINE EXHAUST CASE FOR A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20180230909A1
公开(公告)日：2018-08-16
申请号：US15947890
申请日：2018-04-09
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Ioannis Alvanos , Brian D. Merry
IPC分类号： F02C7/20 , F02K1/04 , F01D9/04 , F01D25/30
CPC分类号： F02C7/20 , F01D9/041 , F01D25/30 , F02K1/04 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y10T29/4932
摘要： A gas turbine engine according to an example of the present disclosure includes, among other things, a turbine case extending along a turbine axis and a CMC turbine exhaust case mounted to the turbine case. The CMC turbine exhaust case includes a CMC core nacelle aft portion, a CMC tail cone connected to the CMC core nacelle aft portion, and a multiple of CMC turbine exhaust case struts extending between the CMC core nacelle aft portion and the CMC tail cone. The CMC core nacelle aft portion, the CMC tail cone and the turbine case are arranged along the turbine axis. The CMC turbine exhaust case is mounted to the turbine case at a flange such that the CMC tail cone is axially spaced apart from the turbine case relative to the turbine axis.

2. 发明申请

US20180223693A1 CERAMIC MATRIX COMPOSITE TURBINE EXHAUST ASSEMBLY FOR A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20180223693A1
公开(公告)日：2018-08-09
申请号：US15424930
申请日：2017-02-06
申请人： United Technologies Corporation
发明人： Gabriel L. Suciu , Brian Merry , Ioannis Alvanos
IPC分类号： F01D25/30 , F02K1/04 , F02K3/06
CPC分类号： F01D25/30 , F01D9/02 , F02C3/04 , F02K1/04 , F02K1/48 , F02K3/06 , F05D2240/14 , F05D2260/96 , F05D2300/6033 , Y02T50/672
摘要： A turbine exhaust assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a turbine exhaust case comprised of CMC material and attachable to a turbine case, a tail cone comprised of CMC material that has a leading edge and a trailing edge, and an exhaust mixer comprised of CMC material and coupled to the turbine exhaust case. The exhaust mixer has a plurality of lobes arranged about the tail cone to define an exhaust flow path. A plurality of struts extend from the tail cone to support the exhaust mixer at a location aft of the leading edge of the tail cone. A method of assembling a propulsion system is also disclosed.

3. 发明授权

US10006309B2 Exhaust diffuser for a gas turbine 有权
公开(公告)号：US10006309B2
公开(公告)日：2018-06-26
申请号：US14498201
申请日：2014-09-26
申请人： ANSALDO ENERGIA IP UK LIMITED
发明人： Willy Heinz Hofmann , Philipp Schaefer
IPC分类号： F01D25/30 , F02K1/04 , F01D9/02 , F01D25/28 , F02C7/20
CPC分类号： F01D25/30 , F01D9/02 , F01D25/28 , F02C7/20 , F02K1/04 , F05B2250/711 , F05B2250/712 , F05B2250/713 , F05D2240/90
摘要： An exhaust diffuser for a gas turbine includes an annular duct. A row of struts is arranged in the duct. In a region downstream of the trailing edges of the struts, the cross-sectional area of the duct decreases to a local minimum and then increases again towards the outlet end of the duct. Thereby the gas flow is locally accelerated downstream of the struts. This stabilizes the boundary layer of the flow in this region and leads to a marked increase in pressure recovery for a wide range of operating conditions.

4. 发明授权

US09816461B2 Exhaust centerbody for a turbine engine 有权
公开(公告)号：US09816461B2
公开(公告)日：2017-11-14
申请号：US14339846
申请日：2014-07-24
申请人： SNECMA
发明人： Guillaume Pouyau , Nicolas Sirvin
IPC分类号： F02K1/04 , F02K1/82 , F01D25/30 , F01D5/14 , B64D33/04 , F01D17/10 , F01D17/14 , F01D25/04 , B21D53/84 , B23P23/00
CPC分类号： F02K1/04 , B21D53/84 , B23P23/00 , B64D33/04 , F01D5/143 , F01D17/10 , F01D17/141 , F01D17/145 , F01D25/04 , F01D25/30 , F02K1/82 , Y02T50/671 , Y02T50/673 , Y10T29/49323
摘要： An exhaust centerbody for a turbine engine is provided. The centerbody includes a truncated downstream part, which is connected to an upstream part by an annular ridge marking a discontinuity between the outer surfaces of the upstream and downstream parts. The outer surface of the downstream part has a substantially conical general shape, of which the tip is oriented downstream and is positioned in the region of the axis A, the axial half-section of this outer surface defining a line of which the upstream end part is substantially tangential to a straight line passing through the ridge and forming a non-zero angle α with a tangent to the outer surface of the upstream part, in the region of the ridge, and of which the downstream end part is substantially tangential to a straight line passing through the tip and forming a non-zero angle β with the axis A.

5. 发明申请

US20170167296A1 Metallic Attachment System Integrated into a Composite Structure 审中-公开
公开(公告)号：US20170167296A1
公开(公告)日：2017-06-15
申请号：US14964752
申请日：2015-12-10
申请人： General Electric Company
发明人： Bernard James Renggli
IPC分类号： F01D25/26 , B32B3/06 , B32B3/26 , B32B5/26 , F01D25/28 , F01D25/24
CPC分类号： F01D25/26 , B32B3/06 , B32B3/266 , B32B5/26 , B32B2260/023 , B32B2260/046 , B32B2262/105 , B32B2605/18 , C04B35/80 , C04B2235/48 , C04B2235/616 , F01D25/005 , F01D25/243 , F01D25/28 , F02K1/04 , F02K1/80 , F05D2230/22 , F05D2230/31 , F05D2230/60 , F05D2260/31 , F05D2300/175 , F05D2300/603 , F05D2300/6033 , F16B2200/506 , Y02T50/672
摘要： The present disclosure is directed to a composite component defining a component aperture extending between a first surface and a second surface. The composite component includes an insert having an insert annular wall positioned in the component aperture. The insert annular wall defines an insert aperture therethrough. An insert flange extends radially outwardly from the insert annular wall and contacts the first surface of the composite component. The insert flange includes a diameter about 1.5 times to about 5 times greater than a smallest diameter of the component aperture defined by the composite component.

6. 发明申请

US20160200443A1 ISOSTATIC SUSPENSION OF A TURBOJET BY REAR DOUBLE SUPPORT 有权
标题翻译：通过后面的双重支持静止停止涡轮
公开(公告)号：US20160200443A1
公开(公告)日：2016-07-14
申请号：US14914349
申请日：2014-08-21
申请人： SNECMA
发明人： Francois Robert Bellabal , Francois Gallet , Mathieu Ange Poisson
IPC分类号： B64D27/26 , B64D27/16 , F02K1/04
CPC分类号： F01D25/16 , B64D27/16 , B64D27/26 , B64D2027/266 , F02C7/20 , F02K1/04 , F02K3/06 , F05D2220/323 , Y02T50/672
摘要： The invention relates to a bypass turbojet comprising an exhaust housing having a central hub (13) and connecting means (11) that can transmit the forces generated by the turbojet to the structure of the aircraft that it propels, said connection means being two arms extending radially from the central hub in order to cross the cold flow of said turbojet and being characterised in that they are secured to said central hub and positioned in a diametrically opposed manner in relation to each other. An additional connection means (14) extends between the hub (13) and the area (9) for securing the exhaust housing to the structure (12) of the aircraft in order to transmit the exceptional dimensioning loads, said connection means being on standby during normal use, without any transmission of force between said hub and said area.
摘要翻译：本发明涉及一种旁通涡轮喷气发动机，其包括具有中心轮毂（13）和连接装置（11）的排气壳体，该连接装置可将由涡轮喷气发生的力传递到其所推进的飞行器的结构，所述连接装置是两个臂径向地从中心轮毂排出以便穿过所述涡轮喷气发动机的冷流，并且其特征在于它们固定到所述中心轮毂并相对于彼此以直径相对的方式定位。另外的连接装置（14）在轮毂（13）和区域（9）之间延伸，用于将排气罩固定到飞行器的结构（12），以便传递异常尺寸的载荷，所述连接装置在正常使用，在所述轮毂和所述区域之间没有任何的力传递。

7. 发明申请

US20160076448A1 AIR INLET ARRANGEMENT AND METHOD OF MAKING THE SAME 审中-公开
公开(公告)号：US20160076448A1
公开(公告)日：2016-03-17
申请号：US14952309
申请日：2015-11-25
申请人： Gulfstream Aerospace Corporation
发明人： Timothy R. Conners , Preston A. Henne , Donald C. Howe
IPC分类号： F02C7/04 , F02K3/02 , F02K1/46
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.

8. 发明申请

US20150167491A1 GAS TURBINE ENGINE COMPRISING A COMPOSITE COMPONENT AND A METAL COMPONENT WHICH ARE CONNECTED BY A FLEXIBLE FIXING DEVICE 有权
标题翻译：包含复合部件的气体涡轮发动机和由柔性固定装置连接的金属部件
公开(公告)号：US20150167491A1
公开(公告)日：2015-06-18
申请号：US14410180
申请日：2013-06-12
申请人： SNECMA
发明人： Antoine Jean-Philippe Beaujard , Jacques Rene Bart
IPC分类号： F01D25/00 , F01D25/24 , F02C7/20
CPC分类号： F01D25/005 , F01D25/24 , F01D25/243 , F02C7/20 , F02K1/04 , F02K1/80 , F05D2230/642 , Y02T50/672
摘要： A gas turbine engine for propulsion of an aircraft, the engine extending axially from upstream to downstream and including a composite part, a metal part, and a device for flexible fixing of the parts, the fixing device including: a flexible connecting element including a first fixing portion connected to the metal part by an axial connection and a second fixing portion connected to the composite part by an axial connection, the connecting element including an axially extending free end; and a rigid locking element including a fixing portion connected to the metal part by an axial connection and an axially extending free end, the free end of the locking element being aligned radially with the free end of the connecting element to limit deformation of the connecting element while the engine is in operation.
摘要翻译：一种用于推进飞行器的燃气涡轮发动机，所述发动机从上游到下游轴向延伸并且包括复合部件，金属部件和用于部件的柔性固定的装置，所述固定装置包括：柔性连接元件，包括第一固定部分通过轴向连接连接到金属部分，第二固定部分通过轴向连接连接到复合部件，连接元件包括轴向延伸的自由端; 以及刚性锁定元件，其包括通过轴向连接和轴向延伸的自由端连接到金属部件的固定部分，锁定元件的自由端与连接元件的自由端径向对准，以限制连接元件的变形而发动机正在运行。

9. 发明申请

US20150152788A1 GAS TURBINE ENGINE COMPRISING AN EXHAUST CONE ATTACHED TO THE EXHAUST CASING 有权
标题翻译：气体涡轮发动机，包括排放在排气管上的排气
公开(公告)号：US20150152788A1
公开(公告)日：2015-06-04
申请号：US14403305
申请日：2013-06-20
申请人： SNECMA
发明人： Mario Cesar De Sousa , Baghdad Achbari , Benoit Argemiro Matthieu Debray , Sylvain Pichon , Gregory Ghosarossian-Prillieux , Frederic Noel , Nicolas Pommier , Mathieu Ange Poisson
IPC分类号： F02C7/32 , F01D25/30
CPC分类号： F02C7/32 , F01D25/24 , F01D25/30 , F02K1/04 , F02K1/80 , F05D2220/32 , F05D2230/60 , F05D2240/91
摘要： An assembly including an exhaust casing and an exhaust cone for a gas turbine engine, each including an axial annular flange, the two flanges being inserted into one another, one being radially external and the other radially internal, and held together by a mechanical attachment, and the assembly further including a guide by which, during operation of assembling the annular flanges to each other, the exhaust cone is in a predetermined angular position relative to the exhaust casing.
摘要翻译：一种包括用于燃气涡轮发动机的排气罩和排气锥的组件，每个包括轴向环形凸缘，两个凸缘彼此插入，一个在径向外部，另一个径向内部，并通过机械附件保持在一起，并且所述组件还包括引导件，通过所述引导件，在将所述环形凸缘彼此组装的操作期间，所述排气锥体相对于所述排气外壳处于预定的角度位置。

10. 发明申请

US20150050072A1 PANEL ATTACHMENT SYSTEM 有权
标题翻译：面板附件系统
公开(公告)号：US20150050072A1
公开(公告)日：2015-02-19
申请号：US14337524
申请日：2014-07-22
申请人： ROLLS-ROYCE PLC
发明人： Paul Robert HAYTON
IPC分类号： F16B5/00
CPC分类号： F16B5/00 , F01D25/28 , F02C7/20 , F02K1/04 , F02K1/80 , F02K1/82 , F05D2230/54 , F05D2250/18 , F05D2300/5021 , Y10T403/32951
摘要： A panel attachment device for removably connecting a panel to a casing comprises a first bracket, a second bracket, and a link. The link has a first end and an opposite second end, with the first end being removably connected to the first bracket and the second end being removably connected to the second bracket. Each of the first end and second ends is located by, and rotatable relative to, the first bracket and second bracket respectively to thereby constrain the panel relative to the casing.
摘要翻译：用于将面板可拆卸地连接到壳体的面板附接装置包括第一支架，第二支架和连杆。连杆具有第一端和相对的第二端，第一端可移除地连接到第一支架，而第二端可移除地连接到第二支架。第一端部和第二端部中的每一个分别位于第一支架和第二支架上并且可相对于第一支架和第二支架旋转，从而相对于壳体约束板。

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