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公开(公告)号：US20190292914A1
公开(公告)日：2019-09-26
申请号：US15933582
申请日：2018-03-23
Applicant: General Electric Company
Inventor： William Scott Zemitis , Jacob Charles Perry, II , Melbourne James Myers , Ajay Gangadhar Patil , Richard Ryan Pilson
Abstract: A turbine rotor blade including an airfoil having a tip shroud, the tip shroud having leading and trailing edges, the leading edge having a leading edge profile including first and second scalloped sections substantially in accordance with X and Y coordinate values in a Cartesian coordinate system at points 1-6 and 11-25, respectively, as set forth in Table I, where X and Y are distances in inches from an origin and, when points 1-6 and points 11-25 are connected by smooth, continuing arcs, the points define the first and second scalloped sections, respectively, of the leading edge profile of the tip shroud.
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公开(公告)号：US20180230816A1
公开(公告)日：2018-08-16
申请号：US15431939
申请日：2017-02-14
Applicant: General Electric Company
Inventor： William Scott Zemitis , Richard Ryan Pilson , Melbourne James Myers
CPC classification number: F01D5/20 , F01D5/225 , F01D11/08 , F01D25/24 , F05B2240/11 , F05D2240/81 , F05D2260/20 , F05D2260/30
Abstract: A turbine blade includes an airfoil that extends from a root end to a tip end, and a tip shroud extending from the tip end. The tip shroud includes a shroud plate that includes a pressure side edge. The pressure side edge includes a primary contact surface configured to couple against an adjacent tip shroud, and a notch extending at least partially downstream from the primary contact surface.
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23.发明公开公开(公告)号：US20240159154A1
公开(公告)日：2024-05-16
申请号：US18379433
申请日：2023-10-12
Applicant: General Electric Company
CPC classification number: F01D5/225 , F01D5/005 , F01D5/141 , F01D5/143 , F05D2220/30 , F05D2220/3213 , F05D2230/80 , F05D2240/30 , F05D2250/74
Abstract: A turbine blade tip shroud has a first cutter tooth extending from a tip rail from one of the upstream side and the downstream side of the tip rail and adjacent the leading edge of the body. The tip shroud also includes a second cutter tooth extending from the tip rail from the other side of the tip rail at a position axially distant from the first cutter tooth. The cutter teeth are thus axially offset. The tip shroud can be initially manufactured with this shape or may be modified from a used tip shroud having, for example, opposing cutter teeth near a leading edge of a body of the tip shroud. Various tip shroud surface profiles, which are expressed in terms of Cartesian coordinates, are also provided.
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24.发明授权公开(公告)号：US11821336B2
公开(公告)日：2023-11-21
申请号：US17691377
申请日：2022-03-10
Applicant: General Electric Company
CPC classification number: F01D5/225 , F01D5/005 , F01D5/141 , F01D5/143 , F05D2220/30 , F05D2220/3213 , F05D2230/80 , F05D2240/30 , F05D2250/74
Abstract: A turbine blade tip shroud has a first cutter tooth extending from a tip rail from one of the upstream side and the downstream side of the tip rail and adjacent the leading edge of the body. The tip shroud also includes a second cutter tooth extending from the tip rail from the other side of the tip rail at a position axially distant from the first cutter tooth. The cutter teeth are thus axially offset. The tip shroud can be initially manufactured with this shape or may be modified from a used tip shroud having, for example, opposing cutter teeth near a leading edge of a body of the tip shroud. Various tip shroud surface profiles, which are expressed in terms of Cartesian coordinates, are also provided.
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Patent Agency Ranking
公开(公告)号：US11713685B2
公开(公告)日：2023-08-01
申请号：US17651827
申请日：2022-02-21
Applicant: General Electric Company
Inventor： Derek Kanoa Tan , William Scott Zemitis , Richard Ryan Pilson , Felipe Roman-Morales , Brian Stephen Gray
Abstract: A tip shroud includes a pair of opposed, axially extending wings configured to couple to an airfoil at a radially outer end thereof. The tip shroud also includes a tip rail extending radially from the pair of opposed, axially extending wings. Tip shroud surface profiles may be of the downstream and/or upstream side of the tip rail, a leading Z-notch of the tip shroud, and/or downstream radially inner surface of a wing. The surface profiles may have a nominal profile substantially in accordance with at least part of Cartesian coordinate values of X and Y, and perhaps Z and a thickness, set forth in a respective table. The radially inner surface of the wing may define a protrusion extending along the radially outer end of the airfoil, the suction side fillet, and a radial inner surface of the wing to an axial edge of the wing.
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公开(公告)号：US10947898B2
公开(公告)日：2021-03-16
申请号：US15431859
申请日：2017-02-14
Applicant: General Electric Company
Abstract: A turbine blade includes an airfoil that includes a root end and a tip end. The tip end is radially spaced from the root end. A tip shroud extends from the tip end. The tip shroud includes a shroud plate. The shroud plate includes a plurality of undulating ridges.
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公开(公告)号：US20180230828A1
公开(公告)日：2018-08-16
申请号：US15431968
申请日：2017-02-14
Applicant: General Electric Company
Inventor： William Scott Zemitis , Richard Ryan Pilson , Felipe Roman-Morales , Melbourne James Myers
CPC classification number: F01D5/3007 , F05D2250/74 , F05D2260/96 , Y02T50/673
Abstract: A turbine blade includes an airfoil that extends radially between a root end and a tip end, a platform coupled to the root end, and a shank that extends radially inwardly from the platform. The shank includes a downstream cover plate and a downstream angel wing that extends axially from the downstream cover plate. A portion of the downstream cover plate radially outward of the downstream angel wing defines an approximately linear profile. The turbine blade also includes a dovetail region that extends radially inwardly from the shank. A profile of a portion of the downstream cover plate radially inward of the downstream angel wing is recessed relative to the linear profile.
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公开(公告)号：US20180230819A1
公开(公告)日：2018-08-16
申请号：US15431918
申请日：2017-02-14
Applicant: General Electric Company
Inventor： William Scott Zemitis , Richard Ryan Pilson , Melbourne James Myers
CPC classification number: F01D5/225 , Y02T50/671
Abstract: A turbine blade includes an airfoil that extends from a root end to a tip end, and a tip shroud extending from the tip end. The tip shroud includes a shroud rail that includes a series of regions along a circumferential width of the shroud rail. The series of regions includes a first edge region adjacent to a suction side edge of the tip shroud, and a wide region. A thickness of the wide region is greater than a thickness of the first edge region.
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公开(公告)号：US10035329B2
公开(公告)日：2018-07-31
申请号：US15621606
申请日：2017-06-13
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Yan Cui , Srikanth Chandrudu Kottilingam , Brian Lee Tollison , Timothy Neal Pletcher , Richard Ryan Pilson
CPC classification number: B32B15/01 , B22F5/009 , B22F5/04 , B22F7/062 , B22F2007/047 , B22F2007/068 , B23K1/0018 , B23K9/04 , B23K10/027 , B23K15/0086 , B23K26/34 , B23K2101/001 , B23K2101/04 , B23K2101/06 , B23K2101/34 , B23K2103/26
Abstract: A hybrid article is disclosed including a coating circumscribing the lateral surface of a hollow core having a core material and a channel disposed within the lateral surface. The coating includes about 35% to about 95% of a first metallic material, and about 5% to about 65% of a second metallic material with a lower melting point than the first metallic material. A method for forming the hybrid article is disclosed including disposing the hollow core in a die, forming a gap between the lateral surface and the die, introducing a slurry having the metallic materials into the gap, and sintering the slurry, forming the coating. A method for closing an aperture of an article is disclosed including inserting the hybrid article into the aperture, and brazing the hybrid article to the article, welding the aperture with the hybrid article serving as weld filler, or a combination thereof.
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