公开(公告)号：US11976591B2

公开(公告)日：2024-05-07

申请号：US18174390

申请日：2023-02-24

申请人： DOOSAN ENERBILITY CO., LTD.

发明人： Young Do Lee

IPC分类号： F02C7/045 ,  F01D9/04 ,  F01D25/28 ,  F04D29/54

CPC分类号： F02C7/045 ,  F01D9/047 ,  F01D25/28 ,  F04D29/54 ,  F04D29/541 ,  F05D2260/96

摘要： An air inlet manifold and a gas turbine including the same, capable of preventing transmission of vibration from the gas turbine to the air inlet manifold, while at the same time preventing air leakage, and the air inlet manifold is installed to be spaced apart from the compressor and relatively movable, as the anti-vibration pad in a compressed state is interposed between the air inlet manifold and the compressor.

公开(公告)号：US20240141799A1

公开(公告)日：2024-05-02

申请号：US17979477

申请日：2022-11-02

申请人： Siemens Energy Global GmbH & Co. KG

发明人： Florian Lang ,  Oliver Rottländer ,  Andreas Müller ,  Mark Grasso ,  Torsten Löber

IPC分类号： F01D15/10 ,  F01D25/28

CPC分类号： F01D15/10 ,  F01D25/285 ,  F05D2220/766 ,  F05D2230/70

摘要： The invention relates to a method for removing a rotor (100) of a generator (4) in a turbine plant (1) in which the generator (4) is driven by at least one turbine (7), in particular a gas turbine or steam turbine, in which the turbine (7) is opened and the rotor (39) of the turbine (7) is removed, and only then is the rotor of the generator (4) pulled out of the generator (4) so that it is located in the lower housing half of the turbine (7).

公开(公告)号：US20240117758A1

公开(公告)日：2024-04-11

申请号：US18045620

申请日：2022-10-11

申请人： General Electric Company

发明人： Christopher David Runkel ,  István Bacsa

IPC分类号： F01D25/28 ,  B66C1/66

CPC分类号： F01D25/285 ,  B66C1/66 ,  F05D2230/60

摘要： A handling system includes an elongated member including a first end and a second end, and a first bend therein. The elongated member is positioned in a slot of the turbine shroud. A base retention member extends from the first end of the elongated member to engage and retain a first end portion of the turbine shroud on the elongated member, and a sliding retainer is configured to slidingly receive the elongated member. The sliding retainer is shaped and sized to slidingly engage in the slot and selectively retain a second end portion of the turbine shroud in a handling position on the elongated member. A lock is coupled to the sliding retainer and selectively movable between a locked position in which the lock retains the sliding retainer in the handling position and an unlocked position in which the sliding retainer slides freely on the elongated member.

公开(公告)号：US11952909B2

公开(公告)日：2024-04-09

申请号：US17519271

申请日：2021-11-04

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Enguerrand Frédéric De Agostini ,  Carlos Alves De Matos ,  Florian Chauvel ,  Baptiste Eparvier ,  Mathias Gagliardo ,  Abner Wysidi

IPC分类号： F01D25/28 ,  F01D9/04 ,  F01D11/12 ,  F01D25/00 ,  F01D25/24 ,  B23P21/00

CPC分类号： F01D25/285 ,  F01D9/042 ,  F01D11/122 ,  F01D25/002 ,  F01D25/24 ,  B23P21/004 ,  F05D2230/644 ,  F05D2230/68 ,  F05D2240/14 ,  F05D2250/283

摘要： An installation for pre-assembling the turbine stators of a turbine each formed of several juxtaposed sectors, includes: an input carriage for conveying sectors intended to form the turbine stators. Each sector includes side faces provided with slots and being associated with a given turbine stator; an output carriage having various trays, each associated with a turbine stator; an automated device for inserting sealing pads configured to interact with a sector conveyed by an automated convey pallet, comprising a robot arm for inserting sealing pads into the slots in a side face of the sector; and another robot arm for gripping a sector equipped with pads from a pallet and depositing it on the tray associated with the turbine stator to pre-assemble the turbine stator.

公开(公告)号：US11927106B2

公开(公告)日：2024-03-12

申请号：US18088196

申请日：2022-12-23

申请人： Raytheon Technologies Corporation

发明人： Anthony R. Bifulco ,  David A. Topol

IPC分类号： F01D25/28 ,  F01D9/06 ,  F01D25/24

CPC分类号： F01D25/28 ,  F01D9/06 ,  F01D25/24 ,  F05D2240/14 ,  F05D2250/191 ,  F05D2260/30 ,  F05D2260/606 ,  F05D2260/96

摘要： A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A fan case surrounds the fan rotor. A core engine has a compressor section and includes a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of aft connecting members rigidly connected to the fan case, and to the core engine. A plurality of fan exit guide vanes are rigidly connected to the fan case, with the fan exit guide vanes including structural fan exit guide vanes which are rigidly connected to the core engine, and non-structural fan exit guide vanes, and the non-structural fan exit guide vanes being provided with an acoustic feature to reduce noise.

公开(公告)号：US20240052778A1

公开(公告)日：2024-02-15

申请号：US17951619

申请日：2022-09-23

申请人： General Electric Company

发明人： Nageswar Rao Ganji ,  Ravindra Shankar Ganiger ,  Hiranya Kumar Nath ,  Ambika Shivamurthy ,  Trevor H. Wood

IPC分类号： F02C6/08 ,  F01D25/04 ,  F01D25/28

CPC分类号： F02C6/08 ,  F01D25/04 ,  F01D25/28 ,  F05D2260/606 ,  F05D2260/963 ,  F05D2250/131

摘要： Variable bleed valves with struts for aerodynamic stability are described. An apparatus described herein includes a variable bleed valve port, and a strut disposed within the variable bleed valve port, the strut defining a plane and a plurality of holes disposed perpendicularly to the plane, the plurality of holes disposed in a pattern to dampen an acoustic response associated with the variable bleed valve port.

公开(公告)号：US20240026798A1

公开(公告)日：2024-01-25

申请号：US18255025

申请日：2021-12-01

申请人： SAFRAN NACELLES

发明人： Hazem KIOUA ,  Thomas MARLAY ,  Charles-Antoine LAMPAERT ,  Pierre-Alain REBOUL

IPC分类号： F01D11/00 ,  F02C7/04 ,  F01D25/24 ,  F01D25/28

CPC分类号： F01D11/003 ,  F02C7/04 ,  F01D25/243 ,  F01D25/28 ,  F05D2220/323 ,  F05D2260/31

摘要： A propulsion unit for an aircraft includes a gas generator; an air inlet; and a sealing system inserted axially between the air inlet and the gas generator. The sealing system has at least: a compression ring with a first axial end configured for mechanical connection to one of the gas generator and the air inlet. The compression ring also has a second opposite axial end configured to be axially separated from the other of the gas generator and the air inlet by an annular space. An annular seal is mounted in the space and configured to be axially compressed by reduction of the axial dimension of said space.

公开(公告)号：US11859505B2

公开(公告)日：2024-01-02

申请号：US17617700

申请日：2020-08-18

申请人： Mitsubishi Power, Ltd.

发明人： Makoto Kondo ,  Katsuhisa Hamada

IPC分类号： F01D5/24 ,  F01D25/24 ,  F01D25/28 ,  F01D11/24 ,  F01D19/00 ,  F01D25/10

CPC分类号： F01D25/243 ,  F01D25/28 ,  F01D11/24 ,  F01D19/00 ,  F01D25/10 ,  F05D2220/31 ,  F05D2240/14

摘要： This steam turbine is provided with: a steam turbine rotor which extends in an axial direction; a pair of bearings which support the steam turbine rotor in such a way as to be capable of rotating about the axial direction; a steam turbine casing which encloses the steam turbine rotor between the pair of bearings; a casing support unit which supports the steam turbine casing from below; and a first heating unit which is provided on the casing support unit and which is capable of heating the casing support unit.

公开(公告)号：US11821330B1

公开(公告)日：2023-11-21

申请号：US17746541

申请日：2022-05-17

申请人： Pratt & Whitney Canada Corp.

发明人： Nicholas Guglielmin ,  Kenneth Parkman

IPC分类号： F01D25/24 ,  F01D25/28

CPC分类号： F01D25/243 ,  F01D25/28 ,  F05D2230/64 ,  F05D2230/70 ,  F05D2240/14 ,  F05D2260/31

摘要： A structure for a gas turbine engine includes a first engine component, a second engine component and fasteners. The component apertures include first fastener apertures and intergroup apertures. The first fastener apertures are arranged into a plurality of groups. The first group is formed by N1-number of the first fastener apertures. The second group is formed by N2-number of the first fastener apertures where the N2-number is different than the N1-number. Each of the intergroup apertures is disposed circumferentially between and adjacent a respective circumferentially neighboring pair of the groups. The second engine component includes a surface and second fastener apertures. The surface axially engages the first engine component and covers the intergroup apertures. The fasteners attach the first engine component and the second engine component together. Each of the fasteners is mated with one of the first fastener apertures and one of the second fastener apertures.

公开(公告)号：US11808662B2

公开(公告)日：2023-11-07

申请号：US16981815

申请日：2019-03-20

申请人： Safran Aircraft Engines

发明人： Jean-Luc Verniau ,  Gilles Polo Filisan ,  Adnan Sozuan ,  Simon Paris

IPC分类号： G01M15/14 ,  F01D25/28 ,  G01M9/06

CPC分类号： G01M15/14 ,  F01D25/285 ,  G01M9/065 ,  F05D2260/83

摘要： A device for measuring the characteristics of an air flow in an annular passage of a turbo-machine. The device includes a rod which extends along a first axis and carries means for measuring air flow characteristics. The rod also sealingly engages and slides in a first tubular part extended by a second tubular part. The second tubular part sealingly passes along the first axis through a slider mounted in a slide for sliding along a second axis perpendicular to the first axis. The rod engages the second tubular part with an annular clearance.