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公开(公告)号：US12117019B2
公开(公告)日：2024-10-15
申请号：US18301692
申请日：2023-04-17
Applicant: General Electric Company
Inventor： Trevor Wood , Kishore Ramakrishnan
CPC classification number: F04D29/544 , F01D9/042 , F04D29/667 , F02C3/04 , F05D2220/323 , F05D2230/80 , F05D2240/121 , F05D2240/122 , F05D2260/96
Abstract: Disclosed examples include an airfoil comprising: a pressure side and a suction side that are coupled together at a substantially radial trailing edge of the airfoil, wherein the substantially radial trailing edge is downstream from a leading edge, the leading edge including a sweep feature of a variable chord length, the variable chord length to include: a first increase in chord length and a decrease in chord length along a radial length from a hub end of the airfoil to an opposite tip end of the airfoil; and a second increase in chord length along the radial length from the hub end to the opposite tip end, the second increase different than the first increase.
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公开(公告)号：US20240280024A1
公开(公告)日：2024-08-22
申请号：US18171533
申请日：2023-02-20
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Nicholas Joseph Kray , Arthur William Sibbach
CPC classification number: F01D5/147 , F01D5/282 , F05D2220/36 , F05D2240/121 , F05D2240/303 , F05D2300/603
Abstract: A turbine engine with an engine core defining an engine centerline and comprising a rotor and a stator. The turbine engine including a set of composite airfoils circumferentially arranged about the engine centerline and defining at least a portion of the rotor. An airfoil in the set of composite airfoils including a composite portion extending chordwise between a composite leading edge and a trailing edge and a leading edge protector coupled to the composite portion.
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公开(公告)号：US11879346B2
公开(公告)日：2024-01-23
申请号：US17629375
申请日：2020-06-29
Applicant: Siemens Energy Global GmbH & Co. KG
Inventor： Harald Kunte , Robert Kunte , Karen Lee , Michael Wagner
CPC classification number: F01D25/12 , F01D5/186 , F01D9/041 , F05D2230/80 , F05D2240/121 , F05D2240/15 , F05D2240/81 , F05D2260/202
Abstract: A method for upgrading a gas turbine, the method includes: a) removing all guide vanes of the first guide vane stage; b) replacing the removed guide vanes of the first guide vane stage with new or reconditioned guide vanes, wherein blade platforms of the new or reconditioned guide vanes are provided with cooling air bores which fluidically connect a cooling air supply duct to the annular gap and open into the annular gap, and wherein the cooling air bores are arranged in such a manner that more cooling air bores open into regions of an annular gap that are arranged radially inwards from leading edges of the guide vanes than in other regions of the annular gap.
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公开(公告)号：US20230383660A1
公开(公告)日：2023-11-30
申请号：US17804572
申请日：2022-05-30
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Ali Azmi , Karan Anand , Alexandre Capron , Tammy Yam , Sylvain Claude , Krishna Prasad Balike , Anthony Robert Bruni , Juan Ignacio Ruiz-Gopegui Gonzalez , Carlos Valbuena Merino , Ignacio Javier Ucin Jarne
CPC classification number: F01D9/04 , F01D5/141 , F05D2240/121 , F05D2220/323 , F05D2300/121 , F05D2300/171 , F05D2230/60 , F05D2250/312
Abstract: An aircraft engine, has: an upstream stator having upstream stator vanes circumferentially distributed about a central axis; and a downstream stator having downstream stator vanes circumferentially distributed about the central axis, the downstream stator located downstream of the upstream stator relative to an airflow flowing within a core gaspath of the aircraft engine, a number of the upstream stator vanes being different than a number of the downstream stator vanes, the downstream stator vanes including: a first vane made of a first material, a major portion of a leading edge of the first vane circumferentially overlapped by one of the upstream stator vanes, and a second vane made of a second material having a greater stiffness, strength, and/or ductility than that of the first material, a major portion of a leading edge of the second vane exposed via a spacing defined between two of the upstream stator vanes.
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公开(公告)号：US20230340885A1
公开(公告)日：2023-10-26
申请号：US18343013
申请日：2023-06-28
Inventor： Elzbieta Kryj-Kos , Piotr Jerzy Kulinski , Pawel Adam Lewicki , Ruolong Ma , Wendy Wenling Lin , Patrick Keene Clements
IPC: F01D9/02
CPC classification number: F01D9/02 , F05D2230/31 , F05D2240/121 , F05D2250/185
Abstract: A method of electroforming an airfoil comprising an airfoil body. The method comprising electroforming a metal edge shell over a filler, located at a leading edge of the airfoil body, and over the airfoil body. The filler can be encapsulated within the metal edge shell and the metal edge shell has a sculpted leading edge defining a non-linear pattern.
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Patent Agency Ranking
公开(公告)号：US11788419B1
公开(公告)日：2023-10-17
申请号：US17887870
申请日：2022-08-15
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jonas Banhos , Ravon Venters , Russell Kim , Raymond Surace , James T. Roach
CPC classification number: F01D5/187 , F01D5/282 , F01D5/284 , F05D2240/121 , F05D2240/303 , F05D2300/6033
Abstract: A ceramic matrix composite airfoil includes a high-pressure surface and a low-pressure surface connected at a leading edge and a trailing edge. The high-pressure surface and the low-pressure surface extend from a first end to a second end. A leading edge cooling passage includes an inlet portion, a midspan portion and an outlet portion. A cross-sectional flow area of the midspan portion is less than a cross-sectional flow area of either the inlet portion or the outlet portion.
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公开(公告)号：US20230228200A1
公开(公告)日：2023-07-20
申请号：US17578885
申请日：2022-01-19
Applicant: Rolls-Royce North American Technologies Inc.
Inventor： Robert W. Heeter
IPC: F01D9/04
CPC classification number: F01D9/041 , F05D2240/121 , F05D2300/501
Abstract: An engine section stator for a gas turbine engine having a compressor, a combustor, and a turbine. The engine section stator includes an inner band, an outer band spaced radially outwardly from the inner band, and a series of spaced apart aerofoils extending the inner and outer bands. The engine section stator includes a stiffness feature that extends away from one of the inner and outer bands of the engine section stator. The stiffness feature configured to increase the high cycle fatigue strength of the aerofoils without impeding airflow passing between the inner and outer bands.
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公开(公告)号：US20190120063A1
公开(公告)日：2019-04-25
申请号：US15791464
申请日：2017-10-24
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Carey Clum , Timothy J. Jennings
CPC classification number: F01D5/186 , F01D5/141 , F01D5/187 , F05D2220/32 , F05D2240/121 , F05D2240/303 , F05D2260/201 , F05D2260/202
Abstract: Airfoils bodies having a first end, a second end, a leading edge, and a trailing edge with a leading edge channel having a first channel wall and a second channel wall that join at a channel base to define the leading edge channel. The leading edge channel extends in a radial direction along the leading edge. A first leading edge impingement cavity is located proximate the leading edge and the first channel wall defines a portion of the first leading edge impingement cavity and a second leading edge impingement cavity with the second channel wall forming a portion of the second leading edge impingement cavity. A first leading edge impingement hole is formed in the first channel wall and angled such that air flowing from the first leading edge impingement cavity and through the first leading edge impingement hole impinges upon a portion of the second channel wall.
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公开(公告)号：US20180135437A1
公开(公告)日：2018-05-17
申请号：US15354055
申请日：2016-11-17
Applicant: UNITED TECHNOLOGIES CORPORATION
CPC classification number: F01D5/284 , B23P15/04 , B32B18/00 , C04B2235/6028 , C04B2237/38 , C04B2237/62 , C04B2237/84 , F01D5/147 , F01D5/187 , F01D5/282 , F01D9/041 , F01D9/042 , F01D9/065 , F01D25/12 , F04D29/388 , F04D29/542 , F05D2220/32 , F05D2230/60 , F05D2240/121 , F05D2240/303 , F05D2260/201 , F05D2260/202 , F05D2260/204 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: A method of fabricating a ceramic turbine engine article includes building a wall of the article from preceramic layers, wherein the building includes arranging the preceramic layers around one or more sacrificial core elements, converting the preceramic layers to ceramic, and removing the one or more sacrificial core elements to leave one or more cavities in the wall.
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公开(公告)号：US09951635B2
公开(公告)日：2018-04-24
申请号：US14659854
申请日：2015-03-17
Applicant: Rolls-Royce Deutschland Ltd & Co KG
Inventor： Volker Guemmer
CPC classification number: F01D9/041 , F01D5/146 , F01D9/00 , F01D9/02 , F01D9/042 , F01D25/24 , F01D25/246 , F04D29/542 , F04D29/544 , F04D29/64 , F04D29/644 , F05D2240/121 , F05D2240/122 , Y02T50/673
Abstract: A blade row group arrangeable in a main flow path of a fluid-flow machine and including N adjacent member blade rows firmly arranged relative to one another both in the meridional direction and in the circumferential direction is provided. Here, a front member blade row with front blades having a leading edge and a trailing edge as well as a rear member blade row with rear blades having a leading edge and a trailing edge are provided, and the blade row group has two main flow path boundaries. It is provided that the profile of the blades of the member blade rows is firmly connected at at least one of the two main flow path boundaries to a base.
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