公开(公告)号：US11746674B2

公开(公告)日：2023-09-05

申请号：US17288387

申请日：2019-04-02

Applicant: Shanghai Electric Power Generation Equipment Co., Ltd.

Inventor： Minjin Tang ,  Yifeng Hu ,  Kai Cheng

IPC: F01D25/12 ,  F01D5/02 ,  F01D25/14 ,  F01D25/26 ,  F01D3/04

CPC classification number: F01D25/12 ,  F01D3/04 ,  F01D5/02 ,  F01D25/14 ,  F01D25/26 ,  F05D2220/31 ,  F05D2240/52 ,  F05D2260/20 ,  F05D2300/17

Abstract: A steam turbine and a method for internally cooling the same. The steam turbine includes an outer casing and an inner casing; a rotor having a balancing piston, the rotor being rotatably mounted inside the inner casing; and a steam flow channel formed between the inner casing and the rotor. Moving blades fitted with the rotor and stationary blades fitted with the inner casing are alternately arranged to form multiple stages of blade groups, and an interlayer for steam to circulate is formed between the inner casing and the outer casing. The multiple stages of blade groups include a first set blade staging and a second set blade staging; and the top of the balancing piston is provided with a first chamber and a second chamber. A first channel disposed in the inner casing connects the flow passage downstream of the first set blade staging to the first chamber; and a second channel connects the second chamber to the interlayer and connects the interlayer to the flow passage downstream of the second set blade staging.

公开(公告)号：US20230203959A1

公开(公告)日：2023-06-29

申请号：US18000065

申请日：2021-05-26

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Jean CAHEN ,  Cyril Leo BENOIT ,  Jean-Philippe MALLAT-DESMORTIERS ,  Romain NOSELLI ,  Mireya SANCHEZ GOMEZ

IPC: F01D9/04 ,  F01D25/00

CPC classification number: F01D9/041 ,  F01D25/005 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2240/12 ,  F05D2300/17

Abstract: A turbine nozzle for a turbine engine, including two annular walls extending about the same axis, the walls being connected to each other by blades having an aerodynamic profile, the nozzle being divided into sectors and including several nozzle sectors arranged circumferentially end-to-end about a longitudinal axis. The blades include first blades made from a first metal alloy, and second blades made from a second metal alloy different from the first alloy, each nozzle sector including first blades and second blades. The invention also relates to a turbine engine, in particular of an aircraft, including at least one such nozzle. The invention also relates to a method for manufacturing such a nozzle in which each of the sectors is produced, for example, by additive manufacturing.

公开(公告)号：US20230203951A1

公开(公告)日：2023-06-29

申请号：US17996340

申请日：2020-04-15

Applicant: Siemens Energy Global GmbH & Co. KG

Inventor： Mitch Kibsey ,  Megan Schaenzer

IPC: F01D5/14 ,  B33Y80/00 ,  B33Y10/00 ,  B22F10/28 ,  B22F5/04 ,  F01D5/28

CPC classification number: F01D5/147 ,  B33Y80/00 ,  B33Y10/00 ,  B22F10/28 ,  B22F5/04 ,  F01D5/28 ,  B22F2301/15 ,  F05D2250/184 ,  F05D2220/32 ,  F05D2300/17

Abstract: An auxetic (NPR) structure includes a plurality of vertical intersecting dimpled sheets, each dimpled sheet exhibiting a negative Poisson's ratio, each dimpled sheet intersects two adjacent dimpled sheets creating a rectangular tubular structure, and having a portion of each dimpled sheet projecting outward from its intersection with an adjacent dimpled sheet, the amplitude of each dimple on the plurality of dimpled sheets is such that no overhanging surface of the dimpled sheet exceeds an angle threshold for printability without support structures.

公开(公告)号：US10041400B2

公开(公告)日：2018-08-07

申请号：US15160119

申请日：2016-05-20

Applicant: BorgWarner Inc.

Inventor： Andrew Taylor ,  Andrew Thompson

IPC: F02B39/00 ,  F01D25/28 ,  F01D25/16 ,  F02B39/14 ,  F01D25/00 ,  F01D25/12 ,  F01D25/18

CPC classification number: F02B39/005 ,  F01D5/085 ,  F01D5/088 ,  F01D25/005 ,  F01D25/08 ,  F01D25/12 ,  F01D25/125 ,  F01D25/16 ,  F01D25/18 ,  F01D25/28 ,  F02B39/14 ,  F05D2220/40 ,  F05D2240/61 ,  F05D2260/20 ,  F05D2260/207 ,  F05D2260/232 ,  F05D2300/16 ,  F05D2300/1606 ,  F05D2300/1614 ,  F05D2300/17

Abstract: A turbocharger rotor shaft assembly and associated turbocharger that includes at least one turbine rotor member having a first face and an opposed second face; and a rotor shaft having a first end and an opposed second end distal from the first end, wherein the rotor shaft is connected to the at least one turbine rotor at a location proximate to the first end and projects outward therefrom, the rotor shaft having an outwardly oriented face and an interior chamber defined therein, the interior chamber having an interior chamber volume. The turbocharger rotor shaft also includes at least one thermal transfer material contained in the interior chamber of the rotor shaft that has a thermal conductivity value that is greater than the thermal conductivity value of the material of construction of the rotor shaft.

公开(公告)号：US09976427B2

公开(公告)日：2018-05-22

申请号：US14721847

申请日：2015-05-26

Applicant: United Technologies Corporation

Inventor： Joshua Daniel Winn ,  David A. Niezelski

IPC: F01D5/28 ,  F01D5/22 ,  F01D5/14 ,  F01D11/00

CPC classification number: F01D5/28 ,  F01D5/147 ,  F01D5/22 ,  F01D11/006 ,  F05D2300/17

Abstract: The present disclosure provides systems for preventing improper installation of a damper seal. In various embodiments, an airfoil assembly may comprise a platform, an airfoil extending from the platform, and a platform tab. The airfoil may comprise a gaspath face and a non-gaspath face. The non-gaspath face may at least partially define a cavity. The airfoil may comprise a pressure side and a suction side. The platform tab may be located adjacent to the suction side of the airfoil. The platform tab may extend from the platform in the opposite direction as the airfoil and may be configured to prevent a damper seal tab from being inserted radially inwards of the platform tab.

公开(公告)号：US20180100404A1

公开(公告)日：2018-04-12

申请号：US15287284

申请日：2016-10-06

Applicant: United Technologies Corporation

Inventor： James W. Taubler ,  Peter E. Gunderson ,  Sunny Anant Patel ,  Andrew P. Boursy

IPC: F01D11/00 ,  F16J15/447 ,  F16J15/16 ,  F02C3/04 ,  F01D25/12 ,  F01D5/06

CPC classification number: F01D11/001 ,  F01D5/06 ,  F01D5/081 ,  F01D11/005 ,  F01D25/12 ,  F02C3/04 ,  F05B2260/20 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2230/10 ,  F05D2230/13 ,  F05D2230/31 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2300/17 ,  F16J15/162 ,  F16J15/447 ,  Y02T50/676

Abstract: An air seal may comprise an annular ring defined by at least a proximal surface, a distal surface, an aft side and a forward side. A channel may be disposed in the forward side of the air seal and/or the aft side of the air seal and may extend between the proximal surface and the distal surface. An additional channel extending from at least one of the forward side or the aft side may be disposed in the distal surface. The channel and the additional channel may be circumferentially in line. The channels may define a flow path for direction cooling air from a proximal side of the air seal to a distal side of the air seal.

公开(公告)号：US20170232506A1

公开(公告)日：2017-08-17

申请号：US15515339

申请日：2014-10-15

Applicant: Siemens Aktiengesellschaft

Inventor： Ching-Pang Lee

IPC: B22D25/02 ,  B33Y10/00 ,  F01D5/18 ,  B22C1/00 ,  B22C9/24 ,  B22D29/00 ,  B28B1/00 ,  B33Y80/00

CPC classification number: B22D25/02 ,  B22C1/00 ,  B22C9/06 ,  B22C9/24 ,  B22D17/22 ,  B22D29/001 ,  B28B1/001 ,  B33Y10/00 ,  B33Y80/00 ,  F01D5/187 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2230/22 ,  F05D2300/17 ,  F05D2300/20

Abstract: A die cast system in which an external shell and an internal core usable to form a component of a gas turbine engine are formed together is disclosed. In at least one embodiment, the external shell and internal core may be formed from at the same time via a selective laser melting process, thus eliminating the need for using the conventional lost-wax casting system. In at least one embodiment, the external shell and internal core may be formed a ceramic material that may support receiving molten metal to form a turbine component. Once formed, the external shell and internal core may be removed to reveal the turbine component.

公开(公告)号：US09724780B2

公开(公告)日：2017-08-08

申请号：US14297406

申请日：2014-06-05

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Amandine Miner ,  David K Jan ,  Don Mittendorf ,  Jason Smoke

IPC: B23K31/02 ,  B23K20/02 ,  B23K1/00 ,  B23P15/00 ,  B23K20/14 ,  B23K20/22 ,  B23K20/26 ,  F01D5/30 ,  F01D5/34 ,  B23K20/00 ,  B23K101/00

CPC classification number: B23K20/028 ,  B23K1/00 ,  B23K1/0018 ,  B23K20/002 ,  B23K20/021 ,  B23K20/023 ,  B23K20/14 ,  B23K20/22 ,  B23K20/26 ,  B23K31/02 ,  B23K2101/001 ,  B23P15/006 ,  F01D5/3061 ,  F01D5/34 ,  F05D2220/323 ,  F05D2230/236 ,  F05D2230/60 ,  F05D2300/17 ,  F05D2300/606 ,  F05D2300/607 ,  Y10T29/49323

Abstract: Dual alloy turbine rotors and methods for manufacturing the same are provided. The dual alloy turbine rotor comprises an assembled blade ring and a hub bonded to the assembled blade ring. The assembled blade ring comprises a first alloy selected from the group consisting of a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy. The hub comprises a second alloy. The method comprises positioning a hub within a blade ring to define an interface between the hub and the blade ring. The interface is a non-contacting interface or a contacting interface. The interface is enclosed by a pair of diaphragms. The interface is vacuum sealed. The blade ring is bonded to the hub after the vacuum sealing step.

公开(公告)号：US20170198601A1

公开(公告)日：2017-07-13

申请号：US14993140

申请日：2016-01-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Michael N. Task ,  Mark A. Boeke ,  Jeffrey R. Levine ,  Russell J. Bergman

IPC: F01D25/00 ,  C23C14/16 ,  F01D9/04 ,  C23C14/35 ,  C23C14/30 ,  C22C19/05 ,  C23C14/08

CPC classification number: F01D25/005 ,  C22C19/05 ,  C22C19/056 ,  C22C19/057 ,  C23C14/083 ,  C23C14/16 ,  C23C14/30 ,  C23C14/35 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/3455 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/312 ,  F05D2230/313 ,  F05D2230/90 ,  F05D2240/128 ,  F05D2260/231 ,  F05D2300/17 ,  F05D2300/175 ,  F05D2300/182 ,  F05D2300/2118 ,  F05D2300/611

Abstract: A gas turbine engine component comprising a nozzle segment, the nozzle segment comprising at least one substrate having a surface. A metallic bondcoat is coupled to the surface of the substrate. An yttria-stabilized zirconia thermal barrier coating is coupled to the metallic bondcoat opposite the surface.

公开(公告)号：US20170159607A1

公开(公告)日：2017-06-08

申请号：US15440311

申请日：2017-02-23

Applicant: United Technologies Corporation

Inventor： Truc Luong ,  Keegan M. Martin

IPC: F02K1/80 ,  F02K1/12

CPC classification number: F02K1/805 ,  F02K1/1223 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2300/17

Abstract: A divergent flap seal includes a flap seal body with a spine, the flap seal body manufactured of a non-metallic material. A mount is engaged with the spine at the dovetail interface and a resilient member at the dovetail interface.