公开(公告)号：US09488106B2

公开(公告)日：2016-11-08

申请号：US14241246

申请日：2012-08-24

Applicant: Mathieu Gaillot ,  Jean Bertucchi ,  Matthieu Leyko

Inventor： Mathieu Gaillot ,  Jean Bertucchi ,  Matthieu Leyko

IPC: F02C7/20 ,  B64C7/02 ,  B64D27/26

CPC classification number: F02C7/20 ,  B64C7/02 ,  B64D27/26 ,  B64D2027/266

Abstract: In an assembly including a bypass turbine engine and an attachment system attaching the turbine engine to an aircraft structure, the attachment system includes a mast, at least two rear attachments connecting the mast to two rear attachment points of the turbine engine, and a rear covering covering the rear attachments and providing a streamlined fairing. The rear covering includes two side walls, each including a first portion extending along and in proximity of the mast and extending rearwards, and a second portion projecting sideways relative to the first portion towards its outside, to cover the rear attachments. Each second portion is substantially a bulge and is connected to the first portion along a curved connection line extending between front and rear points situated substantially level with an inner longitudinal edge of the first portion to minimize the impact on a flow of bypass stream leaving the bypass passage.

Abstract translation: 在包括旁通涡轮发动机和将涡轮发动机附接到飞行器结构的附接系统的组件中，附接系统包括桅杆，将桅杆连接到涡轮发动机的两个后连接点的至少两个后部附件和后盖 覆盖后部附件并提供流线型整流罩。 后盖包括两个侧壁，每个侧壁包括沿着桅杆延伸并且在桅杆附近向后延伸的第一部分，以及相对于第一部分朝向其外部侧向突出的第二部分，以覆盖后部附件。 每个第二部分基本上是凸起的并且沿着弯曲的连接线连接到第一部分，弯曲的连接线在前部和后部点之间延伸，其基本上与第一部分的内部纵向边缘大致水平，以最小化对离开旁路的旁路流的影响 通道。

公开(公告)号：US09488105B2

公开(公告)日：2016-11-08

申请号：US13885710

申请日：2011-11-30

Applicant: Andreas Böttcher ,  Timothy A. Fox ,  Daniel W. Garan ,  Thomas Grieb ,  Jens Kleinfeld ,  Tobias Krieger ,  Stephen A. Ramier ,  David M. Ritland ,  Marcus Zurhorst

Inventor： Andreas Böttcher ,  Timothy A. Fox ,  Daniel W. Garan ,  Thomas Grieb ,  Jens Kleinfeld ,  Tobias Krieger ,  Stephen A. Ramier ,  David M. Ritland ,  Marcus Zurhorst

IPC: F02C7/22 ,  F23R3/28 ,  F02C7/20

CPC classification number: F02C7/20 ,  F23R3/283 ,  F23R3/286 ,  F23R2900/00005 ,  F23R2900/00012 ,  F23R2900/00017 ,  Y10T29/49229

Abstract: An assembly for a gas turbine is presented. The assembly includes a gas supply pipe passing through a bore in a flange of the gas turbine for supplying gas to a combustion chamber of the gas turbine and a sleeve surrounding the gas supply pipe, having a first end and a second end, wherein the first end is sealingly coupled to the gas supply pipe, and wherein the sleeve is adapted to be sealingly coupled to the flange at the second end such that the sleeve extends along a thickness of the flange.

Abstract translation: 提出了一种燃气轮机组件。 组件包括通过燃气轮机的凸缘中的孔的气体供应管，用于将气体供应到燃气轮机的燃烧室，以及围绕气体供应管的套管，其具有第一端和第二端，其中第一 端部密封地联接到气体供应管，并且其中套筒适于在第二端处密封地联接到凸缘，使得套筒沿着凸缘的厚度延伸。

公开(公告)号：US09456472B2

公开(公告)日：2016-09-27

申请号：US13716244

申请日：2012-12-17

Applicant: ROLLS-ROYCE PLC

Inventor： Justin Dalton ,  Paul Broughton ,  Richard Peace ,  Gary Alan Skinner ,  Robin Charles Kennea

IPC: B23P6/00 ,  B60R16/02 ,  F02C7/00 ,  F02C7/047 ,  F02C7/12 ,  F02C7/20 ,  F02C7/224 ,  F02C7/32 ,  F24H1/10 ,  H01R12/00 ,  H02G1/00 ,  H02G3/02 ,  H02G3/32 ,  H02G1/02 ,  H05B3/28 ,  B64C3/34 ,  B60R16/08 ,  F02C7/141 ,  F02C7/16 ,  H02G3/04 ,  H05B1/02

CPC classification number: H05B3/28 ,  B23P6/005 ,  B60R16/00 ,  B60R16/02 ,  B60R16/0207 ,  B60R16/0215 ,  B60R16/08 ,  B64C3/34 ,  B64D29/08 ,  F02C7/00 ,  F02C7/047 ,  F02C7/12 ,  F02C7/141 ,  F02C7/16 ,  F02C7/20 ,  F02C7/224 ,  F02C7/32 ,  F05D2260/30 ,  F05D2300/603 ,  F16M13/02 ,  F24H1/105 ,  H01R12/00 ,  H01R12/51 ,  H01R12/515 ,  H01R12/57 ,  H01R12/59 ,  H01R12/592 ,  H01R12/61 ,  H02G1/00 ,  H02G3/00 ,  H02G3/02 ,  H02G3/04 ,  H02G3/0487 ,  H02G3/32 ,  H05B1/0236 ,  H05K1/0393 ,  H05K7/20 ,  H05K2201/029 ,  Y02T50/672 ,  Y10T29/49002 ,  Y10T29/49117 ,  Y10T29/49234 ,  Y10T29/49236 ,  Y10T29/49238 ,  Y10T156/10

Abstract: The present invention provides a rigid raft formed of rigid composite material. The raft has an electrical system and/or a fluid system embedded therein. The raft further has a tank for containing liquid integrally formed therewith. The tank can be formed of the rigid composite material. The tank can be for a gas turbine engine.

Abstract translation: 本发明提供由刚性复合材料形成的刚性筏。 筏具有嵌入其中的电气系统和/或流体系统。 筏还具有用于容纳与其一体形成的液体的罐。 罐可以由刚性复合材料形成。 该罐可用于燃气涡轮发动机。

公开(公告)号：US20160265440A1

公开(公告)日：2016-09-15

申请号：US15068294

申请日：2016-03-11

Applicant: ANSALDO ENERGIA SWITZERLAND AG

Inventor： Stephen Wilder Jorgensen ,  Joshua R. McNally ,  Heinz Gerber ,  Davide Aratori ,  Douglas Anthony Pennel ,  Daniel Seng

IPC: F02C7/20

CPC classification number: F02C7/20 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2230/70 ,  F23R3/60

Abstract: A mounting and dismounting device for a liner of a gas turbine includes two inner rails attached at the turbine housing and each one having a first straight portion, two straight outer rails releasably attached at the turbine housing, wherein the adjacent free ends of the inner and outer rails can be positioned in full alignment one to the other. The rails are adapted to support the liner to be moveable in its axial direction. The inner rails include a second straight portion connected to the first straight portion through a curved portion wherein the axis of the second straight portion is parallel to the axis of the combustion gas passageway.

Abstract translation: 一种用于燃气涡轮机衬套的安装和拆卸装置，包括安装在涡轮机壳体处的两个内轨道，每个内轨道具有第一直线部分，两个直立的外轨道可释放地附接在涡轮机壳体上，其中， 外轨可以一个对准地完全对准。 轨道适于支撑衬套以在其轴向方向上可移动。 内轨道包括通过弯曲部分连接到第一直线部分的第二直线部分，其中第二直线部分的轴线平行于燃烧气体通道的轴线。

公开(公告)号：US20160245171A1

公开(公告)日：2016-08-25

申请号：US15047362

申请日：2016-02-18

Applicant: Pratt & Whitney Canada Corp.

Inventor： Sylvain LAMARRE ,  Mike FONTAINE ,  Andre JULIEN ,  Michael GAUL ,  Jean THOMASSIN ,  Lazar MITROVIC ,  Ilya B. MEDVEDEV ,  Sergey USIKOV ,  Andrey ZOLOTOV

IPC: F02C3/10 ,  F02B39/04 ,  F02B37/00

CPC classification number: F02C3/10 ,  F02B37/004 ,  F02B39/04 ,  F02C7/20 ,  F02C7/25 ,  F05D2220/40 ,  Y02T50/53

Abstract: A compound engine assembly with an engine core including at least one internal combustion engine, a turbine section, and a compressor having an outlet in fluid communication with an inlet of the engine core. A casing is connected to the turbine section, compressor and engine core. A mount cage is connected to mounts attached to the casing between the compressor and a hot zone including the turbine section and exhaust pipe(s). The struts are separated from the hot zone by at least one firewall. The mount cage may include a plurality of struts all extending from the mounts away from the turbine section and engine core. The casing may be a gearbox module casing through which the turbine shaft in engaged with the engine shaft. The mount cage may be completely contained within an axial space with the turbine section and exhaust pipe(s) being located outside of the axial space.

Abstract translation: 具有包括至少一个内燃机，涡轮部分和具有与发动机芯的入口流体连通的出口的压缩机的发动机芯的复合发动机组件。 壳体连接到涡轮部分，压缩机和发动机核心。 安装架连接到在压缩机和包括涡轮部分和排气管的热区之间附接到壳体的安装件。 支柱通过至少一个防火墙与热区隔开。 安装架可以包括多个支柱，其全部从支架延伸离开涡轮部分和发动机芯。 壳体可以是齿轮箱模块壳体，涡轮轴通过该外壳与发动机轴接合。 安装架可以完全容纳在轴向空间内，涡轮部分和排气管位于轴向空间的外部。

公开(公告)号：US20160245105A1

公开(公告)日：2016-08-25

申请号：US14629090

申请日：2015-02-23

Applicant: United Technologies Corporation

Inventor： Jorge I. Farah ,  John T. Ols

IPC: F01D9/04 ,  F01D25/24 ,  F01D11/00

CPC classification number: F01D9/041 ,  F01D9/042 ,  F01D9/065 ,  F01D11/005 ,  F01D25/162 ,  F01D25/24 ,  F01D25/28 ,  F02C7/20 ,  F05D2220/3213 ,  F05D2230/21 ,  F05D2240/12 ,  F05D2240/55 ,  F05D2240/80 ,  F05D2260/31

Abstract: A gas turbine engine includes a core flow path that extends axially about an engine axis. A turbine section is arranged in the core flow path. A mid-turbine frame includes multiple circumferentially spaced vanes that extend radially between and interconnect inner and outer flow path surfaces that define a portion of the core flow path. The vanes and inner and outer flow path surfaces are provided by a unitary, one-piece cast structure. The inner flow path surface provides inlet and exit inner diameters relative to the engine axis. The outer flow path surface provides inlet and exit outer diameters relative to the engine axis. The inner flow path surface extends an axial length from the inlet inner diameter to the exit inner diameter. A ratio of the exit outer diameter to the axial length is greater than 3.0 to 1.

Abstract translation: 燃气涡轮发动机包括围绕发动机轴线轴向延伸的铁心流路。 涡轮部分布置在核心流动路径中。 中间涡轮机框架包括多个周向间隔开的叶片，其在限定芯流动路径的一部分之间径向延伸并且互连内部和外部流动路径表面。 叶片和内部和外部流动路径表面由单一的一体式铸造结构提供。 内部流路表面相对于发动机轴线提供入口和出口内径。 外部流路表面相对于发动机轴线提供入口和出口外径。 内部流路表面从入口内径延伸到出口内径的轴向长度。 出口外径与轴向长度之比大于3.0比1。

公开(公告)号：US20160244178A1

公开(公告)日：2016-08-25

申请号：US15026555

申请日：2014-08-29

Applicant: United Technologies Corporation

Inventor： Brett Colin Bonner ,  Eric Andrew Nager

IPC: B64D33/04 ,  F01D25/30 ,  B64D41/00 ,  F01D25/28

CPC classification number: B64D33/04 ,  B64D41/00 ,  B64D2041/002 ,  F01D25/28 ,  F01D25/30 ,  F02C7/20 ,  F02K1/04 ,  F05D2220/50 ,  F05D2230/60 ,  F05D2230/644 ,  F05D2250/241 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/30

Abstract: An exhaust system for an aircraft includes an exhaust duct configured to be inserted within a plurality of leaf springs of an aircraft. The exhaust duct is configured to be in fluid communication with the auxiliary power unit for conveying exhaust from the auxiliary power unit to an exhaust exit, the exhaust duct including at least one exhaust bracket for movably mounting the exhaust duct to an airframe. An alignment system is configured to be operatively connected to the exhaust duct.

Abstract translation: 用于飞行器的排气系统包括被配置为插入飞行器的多个板簧内的排气管道。 排气管被构造成与辅助动力单元流体连通，用于将排气从辅助动力单元输送到排气出口，排气管道包括至少一个排气支架，用于将排气管可移动地安装到机身上。 对准系统被配置为可操作地连接到排气管。

公开(公告)号：US20160230657A9

公开(公告)日：2016-08-11

申请号：US14684272

申请日：2015-04-10

Applicant: Dynamo Micropower Corporation

Inventor： Jason How-Ring Ethier ,  Ivan Wang ,  Erik Herold ,  Alyssa M. Hatch

IPC: F02C6/18 ,  F02C7/27 ,  F02C3/04 ,  F02C7/264 ,  F02C7/22 ,  F02C7/232 ,  F02C7/04 ,  F02C9/00 ,  F02C7/20 ,  F02C7/06 ,  F02C7/08 ,  F02C7/12 ,  F02C7/224 ,  F02C7/268 ,  F02C6/00

CPC classification number: F02C6/18 ,  F02C3/04 ,  F02C3/22 ,  F02C3/24 ,  F02C6/00 ,  F02C7/04 ,  F02C7/06 ,  F02C7/08 ,  F02C7/12 ,  F02C7/20 ,  F02C7/22 ,  F02C7/224 ,  F02C7/232 ,  F02C7/264 ,  F02C7/268 ,  F02C7/27 ,  F02C9/00 ,  F05D2220/32 ,  F05D2220/74 ,  F05D2220/76 ,  Y02E20/14 ,  Y10T29/4932

Abstract: The present disclosure describes a micro gas turbine flameless heater, in which the heat is generated by burning fuel in a gas turbine engine, and the heater output air mixture is generated by transferring the heat in the gas turbine exhaust to the cold air drawn from the ambient environment. The present disclosure also describes component geometries and system layout for a gas turbine power generation unit that is designed for simple assembly, disassembly, and component replacement. The present disclosure also allows for quick removal of the rotating components of the gas turbine engine in order to reduce assembly and maintenance time. Furthermore, the present disclosure describes features that help to maintain safe operating temperatures for the bearings and structures of the gas turbine engine power turbine. Lastly, the present disclosure describes features of a fuel capture system that allow the injection of wellhead gas, which typically is a mixture of gaseous and liquid fuels, into the combustion chamber, and also describes methods of incorporating afterburners in the gas turbine engine, such that the gas turbine engine system can use wellhead gas to power equipment and reduce emissions from flaring in oil and gas applications.

公开(公告)号：US09410441B2

公开(公告)日：2016-08-09

申请号：US13613904

申请日：2012-09-13

Applicant: Ian Alexander Macfarlane

Inventor： Ian Alexander Macfarlane

IPC: F02C7/20 ,  F01D11/08 ,  F01D25/24 ,  F02C6/20

CPC classification number: F02C3/10 ,  B64D27/10 ,  F01D11/08 ,  F01D25/246 ,  F02C6/206 ,  F02C7/20 ,  F05D2230/642 ,  F05D2250/411 ,  Y10T29/49236

Abstract: A turboprop engine including an annular outer case including a mount ring for attachment to an aircraft along a plane to transfer loads from a propeller and having an annular flange extending radially inwardly therefrom within the plane, an annular turbine support case received within the outer case and connected to the outer case only through a direct connection with the annular flange allowing a limited relative pivoting motion between the turbine support case and the mount ring, and a turbine section including a rotor closely surrounded by a shroud with an annular tip clearance being defined therebetween, the shroud being directly connected to and located by the turbine support case. A method of isolating a turbine shroud from propeller loads in a propeller engine is also disclosed.

Abstract translation: 一种涡轮螺旋桨发动机，其包括环形外壳，其包括用于沿着平面附接到飞行器的安装环，以从螺旋桨传输载荷并具有在平面内径向向内延伸的环形凸缘;容纳在外壳内的环形涡轮机支撑壳体， 仅通过与环形凸缘的直接连接连接到外壳，允许在涡轮机支撑壳体和安装环之间进行有限的相对枢转运动，以及包括被护罩紧密包围的转子的涡轮部分，其间限定有环形顶端间隙 ，所述护罩直接连接到所述涡轮机支撑壳体并由所述涡轮机支撑壳体定位。 还公开了一种将涡轮机罩与螺旋桨发动机中的螺旋桨负载隔离的方法。

公开(公告)号：US20160215698A1

公开(公告)日：2016-07-28

申请号：US14527860

申请日：2014-10-30

Applicant: Siemens Energy, Inc.

Inventor： Andrew Carlson ,  William W. Pankey

IPC: F02C7/20

CPC classification number: F01D25/28 ,  F01D9/023 ,  F02C7/20 ,  F05D2230/642 ,  F05D2240/90 ,  F05D2250/241 ,  F05D2260/31 ,  F23R3/60

Abstract: A support arrangement (10) for a transition piece (12) of a gas turbine engine (14). The support arrangement includes a mounting bracket (16) for the transition piece and a pin (18) supporting the mounting bracket in an interior (20) of the gas turbine engine and extending through an opening (22) in a casing (24) to an exterior (26) of the as turbine engine. The support arrangement further includes a spherical washer (28, 38) positioned between the pin and either the mounting bracket or the casing

Abstract translation: 一种用于燃气涡轮发动机（14）的过渡件（12）的支撑装置（10）。 支撑装置包括用于过渡件的安装支架（16）和将燃料涡轮发动机的内部（20）支撑安装支架的销（18），并延伸穿过壳体（24）中的开口（22）至 作为涡轮发动机的外部（26）。 支撑装置还包括定位在销和安装支架或壳体之间的球形垫圈（28,38）