公开(公告)号：US20240309765A1

公开(公告)日：2024-09-19

申请号：US18121146

申请日：2023-03-14

申请人： Raytheon Technologies Corporation

发明人： David E. Bitter ,  S. Bret Bonarrigo ,  William John Oldach ,  William C. Sheridan ,  Matthew Michael Massaro

IPC分类号： F01D5/18

CPC分类号： F01D5/18 ,  F05D2230/237

摘要： A hollow vane assembly including an open body including an interior; at least one cover support structure formed in said open body proximate the interior; a cover brazed to the open body to form at least one flow passage; and at least one ply formed in the cover.

公开(公告)号：US20240133311A1

公开(公告)日：2024-04-25

申请号：US18546534

申请日：2022-02-14

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Jérôme Claude George LEMONNIER ,  Franck Davy BOISNAULT ,  Antoine Bruno VAN NOORT

IPC分类号： F01D11/12 ,  F01D11/02

CPC分类号： F01D11/122 ,  F01D11/02 ,  F05D2230/237 ,  F05D2230/60

摘要： A distributor for a turbine of a turbomachine. The distributor includes a radially inner platform, a blade and a root which is coated with a track made of an abradable material. According to the invention, the distributor includes a leakage gas reintroduction duct. The duct includes an inlet through the track made of an abradable material, an outlet opening through a downstream surface of the root, and a duct intermediate portion which extends from the inlet up to the outlet. The duct intermediate portion is orientated with a tangential component.

公开(公告)号：US11952918B2

公开(公告)日：2024-04-09

申请号：US17868911

申请日：2022-07-20

申请人： General Electric Company

发明人： Matthew Troy Hafner ,  John M. Matthews ,  Zachary John Snider

IPC分类号： F01D9/04 ,  F01D5/18

CPC分类号： F01D9/044 ,  F01D5/187 ,  F01D5/188 ,  F01D5/189 ,  F01D9/041 ,  F05D2230/237 ,  F05D2240/81 ,  F05D2260/201 ,  F05D2260/2214

摘要： A stator vane includes a platform that defines an opening. The stator vane further includes an airfoil that has a leading edge, a trailing edge, a suction side wall, and a pressure side wall. The airfoil extends radially between a base and a tip. At least one of the base or the tip includes a protrusion. The protrusion extends into the opening of the platform such that the platform surrounds the protrusion of the airfoil. The stator vane further includes a braze joint disposed between and fixedly coupling the platform and the protrusion of the airfoil. The stator vane further includes a cooling circuit defined in at least one of the protrusion or the platform to cool the braze joint.

公开(公告)号：US20240044257A1

公开(公告)日：2024-02-08

申请号：US17880832

申请日：2022-08-04

申请人： General Electric Company

发明人： Ya-tien Chiu ,  Giridhar Jothiprasad ,  David V. Parker ,  Michael Macrorie

IPC分类号： F01D9/04

CPC分类号： F01D9/041 ,  F05D2240/12 ,  F05D2220/3216 ,  F05D2230/237

摘要： A stator structure including a plurality of stator blades and redirection structures including a first portion and a second portion, the first portion disposed on a front edge surface of a stator hub and a second portion disposed on a facing of the stator hub is provided. The stator hub includes the facing and the front edge surface, the facing being disposed generally perpendicular to the casing, and the front edge surface is disposed generally perpendicular to the facing. During operation of a turbine engine a core air flow moves along the longitudinal axis and past the plurality of stator blades, and a leakage air flow moves in a direction different to the core air flow, the redirection structures are effective to redirect the leakage air flow to merge into the core air flow.

公开(公告)号：US20230398621A1

公开(公告)日：2023-12-14

申请号：US18454365

申请日：2023-08-23

申请人： General Electric Company

发明人： Raghavendra Rao Adharapurapu ,  Michael Francis Xavier Gigliotti, Jr. ,  David Edwin Budinger ,  Pazhayannur Ramanathan Subramanian ,  Jeffrey Jon Schoonover

IPC分类号： B23K1/00 ,  B23K35/30 ,  C22C45/04 ,  F01D25/00 ,  F01D25/24 ,  F01D5/28 ,  F01D5/00

CPC分类号： B23K1/0018 ,  B23K35/3033 ,  C22C45/04 ,  F01D25/005 ,  F01D25/24 ,  F01D5/282 ,  F01D5/005 ,  F05D2230/237 ,  B23K2101/001

摘要： A nickel-based braze alloy composition is described, including nickel, about 1 weight % to about 5 weight % boron (B); and about 1 weight % to about 20 weight % germanium (Ge). The composition is free of any silicon. Superalloy articles that contains a crack or other type of void or gap filled with the nickel-based braze alloy composition are also described, along with methods for filling such a gap. Related articles of manufacture and brazing processes to join metal components are also disclosed.

公开(公告)号：US11826830B2

公开(公告)日：2023-11-28

申请号：US16916722

申请日：2020-06-30

申请人： GENERAL ELECTRIC COMPANY

发明人： Sandip Dutta ,  Zachary Snider ,  Srikanth Chandrudu Kottilingam ,  Stephen Wassynger ,  Joseph Moroso

IPC分类号： F01D9/04 ,  B22F5/04 ,  F01D25/12 ,  B22F7/08 ,  F01D5/14 ,  B22F10/28 ,  F04D29/66

CPC分类号： B22F5/04 ,  B22F7/08 ,  F01D5/147 ,  F01D9/041 ,  F01D9/044 ,  F01D25/12 ,  B22F10/28 ,  F04D29/666 ,  F05D2220/32 ,  F05D2230/21 ,  F05D2230/22 ,  F05D2230/237 ,  F05D2230/31 ,  F05D2230/50 ,  F05D2240/128 ,  F05D2240/80 ,  F05D2240/81 ,  F05D2260/202 ,  Y02P10/25

摘要： At least one turbine component for a gas turbine includes a base component formed by casting and an article. The base component includes a platform. The article on the upper surface of the platform is formed by additive manufacturing. The article has a proximal face sized and shaped to cover at least a portion of the upper surface of the platform of the turbine component and a contoured distal face opposite the proximal face. The contoured distal face has a contour surface serving as at least a portion of a hot gas path surface of the turbine component. The contour surface is arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface based on a clock mounting location of the turbine component in a turbine.

公开(公告)号：US11819966B2

公开(公告)日：2023-11-21

申请号：US17828751

申请日：2022-05-31

申请人： Raytheon Technologies Corporation

发明人： Guolin Oo ,  Garimella Balaji Rao

IPC分类号： B23K1/00 ,  B23K3/08 ,  B23K101/02 ,  F01D11/00 ,  F01D11/12 ,  B23K101/00 ,  B23P6/00

CPC分类号： B23P6/002 ,  B23K1/0014 ,  B23K1/0018 ,  B23K3/087 ,  B23K2101/001 ,  B23K2101/02 ,  F01D11/001 ,  F01D11/127 ,  F05D2230/237 ,  F05D2230/80 ,  F05D2240/55

摘要： A method of applying a braze component to a honeycomb structure may comprise: applying at least a partial vacuum within a chamber, the chamber defined at least partially by a vacuum device and a cover, the honeycomb structure disposed within the chamber, the braze component disposed between the honeycomb structure and the cover; pulling the cover towards the braze component in response to applying the partial vacuum; and pulling the braze component into a plurality of hexagonal cells defined by the honeycomb structure in response to pulling the cover towards the braze component.

公开(公告)号：US11795828B2

公开(公告)日：2023-10-24

申请号：US17594071

申请日：2020-03-16

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Matthieu Simon ,  Jean-Luc Bacha ,  Paul Danre ,  Léandre Ostino

IPC分类号： F01D5/18 ,  F01D9/06

CPC分类号： F01D5/189 ,  F01D9/065 ,  F05D2230/237 ,  F05D2240/30 ,  F05D2260/201

摘要： A blade for a turbomachine intended to be disposed about an axis while extending radially between a radially outer end and a radially inner end, the blade having at least one cooling cavity opening out to the radially outer end of the blade and to the radially inner end of the blade, the blade having at least a first tubular liner and at least a second tubular liner each engaged in the cavity, the radially outer end of the first liner opening out to the radially outer end of the blade, and the radially inner end of the second liner opening out to the radially inner end of the blade.

公开(公告)号：US20230323776A1

公开(公告)日：2023-10-12

申请号：US18043484

申请日：2021-08-26

申请人： SAFRAN AIRCRAFT ENGINES ,  SAFRAN CERAMICS

发明人： Lucien Henri Jacques QUENNEHEN ,  Sébastien Serge Francis CONGRATEL ,  Matthieu Arnaud GIMAT

IPC分类号： F01D5/28 ,  F01D9/04 ,  C04B37/00

CPC分类号： F01D5/282 ,  F01D9/04 ,  C04B37/003 ,  F05D2300/603 ,  F05D2230/237 ,  C04B2237/38 ,  C04B2237/60 ,  C04B2237/64

摘要： A turbomachine part of an annular assembly includes a structural body and a connecting edge integral with the structural body. Each connecting edge includes at least one groove intended to receive a sealing tab. Each connecting edge is made of composite material including a fibrous reinforcement consisting of randomly-oriented short fibres, the reinforcement being densified by a ceramic matrix.

公开(公告)号：US11692446B2

公开(公告)日：2023-07-04

申请号：US17448661

申请日：2021-09-23

申请人： Rolls-Royce North American Technologies, Inc. ,  Rolls-Royce Corporation

发明人： Matthew T. Kush ,  Michael Wood ,  Scott Nelson ,  Joseph Peter Henderkott

IPC分类号： B22F5/04 ,  F01D5/18 ,  B23K1/00 ,  B22F10/22 ,  B33Y80/00 ,  B22F5/00 ,  B22F7/00 ,  B23K101/00

CPC分类号： F01D5/187 ,  B22F5/00 ,  B22F5/04 ,  B22F7/00 ,  B22F10/22 ,  B23K1/0018 ,  B33Y80/00 ,  B23K2101/001 ,  F05D2230/22 ,  F05D2230/237 ,  F05D2230/31 ,  Y10T29/49337

摘要： A method for forming a component for a gas turbine engine may include forming a first portion of the component that includes a cast metal or metal alloy, forming a second portion of the component that includes presintered preform defining at least one support structure, positioning the second portion on the first portion to define an assembly such that the first portion and the second portion define at least one cooling channel therebetween, and heating the assembly to join the first portion and the second portion and form the component.