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公开(公告)号：US20220325629A1
公开(公告)日：2022-10-13
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：US20210301670A1
公开(公告)日：2021-09-30
申请号：US16835492
申请日：2020-03-31
Applicant: General Electric Company
Inventor： Martin James Jasper , Jan Agudo , Melbourne James Myers , Richard Ryan Pilson , Christopher W. Kester
IPC: F01D5/28
Abstract: An airfoil includes a root and a tip, which define a span of the airfoil therebetween. The airfoil also includes a leading edge and a trailing edge downstream of the leading edge along a flow direction. The leading edge and the trailing edge each extend across the span of the airfoil from the root to the tip. The airfoil further includes a pressure side surface and a suction side surface. The airfoil also includes a thermal barrier coating on the pressure side surface and the suction side surface. The thermal barrier coating includes a base layer and a top coat. A thickness of the base layer varies across each of the pressure side surface and the suction side surface with a maximum thickness of the base layer at the leading edge.
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公开(公告)号：US10683765B2
公开(公告)日：2020-06-16
申请号：US15431994
申请日：2017-02-14
Applicant: General Electric Company
Inventor： William Scott Zemitis , Richard Ryan Pilson , Felipe Roman-Morales , Melbourne James Myers , Kevin Lee Worley
Abstract: A method of modifying a shank of a turbine blade from an initial profile to an undercut profile includes removing a first portion of material from an underside of a downstream angel wing of the turbine blade. The downstream angel wing extends axially from a downstream cover plate of the shank. The method also includes removing a second portion of material from a generally axially-extending portion of the downstream cover plate adjacent a dovetail of the turbine blade.
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公开(公告)号：US20180230806A1
公开(公告)日：2018-08-16
申请号：US15431859
申请日：2017-02-14
Applicant: General Electric Company
CPC classification number: F02C3/04 , F01D5/20 , F01D5/225 , F05D2240/307 , F05D2240/81 , F05D2250/183 , F05D2250/611 , F05D2260/20 , Y02T50/673 , Y02T50/676
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：US20140161625A1
公开(公告)日：2014-06-12
申请号：US13711241
申请日：2012-12-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Xiuzhang James Zhang , Adebukola Oluwaseun Benson , Richard Ryan Pilson , Stephen William Tesh
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2230/11 , F05D2250/232 , F05D2250/25 , F05D2250/323
Abstract: Systems and devices configured to cool turbine components in a turbine by passing a cooling flow through the turbine component via a cooling passage with a variable diameter are disclosed. In one embodiment, a turbine component includes: at least one elongated cooling passage extending from a root of the bucket to a tip of the bucket, wherein the elongated cooling passage has a variable diameter along a length of the bucket.
Abstract translation: 公开了通过使冷却流通过涡轮机部件经由具有可变直径的冷却通道来冷却涡轮机中的涡轮机部件的系统和装置。 在一个实施例中，涡轮机部件包括：从铲斗的根部延伸到铲斗的尖端的至少一个细长的冷却通道，其中细长的冷却通道沿铲斗的长度具有可变的直径。
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Patent Agency Ranking
公开(公告)号：US11692447B1
公开(公告)日：2023-07-04
申请号：US17860504
申请日：2022-07-08
Applicant: General Electric Company
Inventor： Brian Stephen Gray , Richard Ryan Pilson , William Scott Zemitis , Dustin James Hall , Derek Kanoa Tan
CPC classification number: F01D5/225 , F01D5/141 , F01D5/143 , F05D2220/30 , F05D2220/3212 , F05D2240/30 , F05D2250/74
Abstract: A tip shroud may include a platform to couple to an airfoil having a pressure side and a suction side. A front tip rail and a rear tip rail extend radially from the platform with each including a downstream side, an upstream side, and an origin(s). Each of the downstream side and the upstream side of the rear tip rail and the downstream side of the front tip rail has a shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, Z set forth in a respective table and originating at a selected origin. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the X, Y, Z values by a minimum rear tip rail X-wise extent expressed in units of distance. The X, Y, Z values are connected by lines to define each respective surface profile.
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公开(公告)号：US20220307376A1
公开(公告)日：2022-09-29
申请号：US17651824
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 a 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：US11156103B2
公开(公告)日：2021-10-26
申请号：US16725654
申请日：2019-12-23
Applicant: General Electric Company
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 cover plate. The cover plate includes an outer surface, an opposite inner surface, and a contoured face that at least partially defines a damper pin slot. The contoured face extends from the outer surface to a first blend edge. The cover plate also includes a blended surface that extends from the first blend edge to a second blend edge. The second blend edge intersects with the inner surface.
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公开(公告)号：US20200277864A1
公开(公告)日：2020-09-03
申请号：US16725654
申请日：2019-12-23
Applicant: General Electric Company
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 cover plate. The cover plate includes an outer surface, an opposite inner surface, and a contoured face that at least partially defines a damper pin slot. The contoured face extends from the outer surface to a first blend edge. The cover plate also includes a blended surface that extends from the first blend edge to a second blend edge. The second blend edge intersects with the inner surface.
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公开(公告)号：US10519785B2
公开(公告)日：2019-12-31
申请号：US15431950
申请日：2017-02-14
Applicant: General Electric Company
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 cover plate. The cover plate includes an outer surface, an opposite inner surface, and a contoured face that at least partially defines a damper pin slot. The contoured face extends from the outer surface to a first blend edge. The cover plate also includes a blended surface that extends from the first blend edge to a second blend edge. The second blend edge intersects with the inner surface.
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