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公开(公告)号：US11946386B2
公开(公告)日：2024-04-02
申请号：US18340483
申请日：2023-06-23
Applicant: General Electric Company
Inventor： William Scott Zemitis , Robert Tomasz Liskiewicz
IPC: F01D5/14
CPC classification number: F01D5/141 , F05D2240/307
Abstract: Various embodiments include a turbine blade having an airfoil with a tip shroud having a forwardmost tip rail having one or more pressure side and suction side bevel surfaces and pressure side and suction side scallop surfaces. The surfaces have a nominal profile substantially in accordance Cartesian coordinate values of X, Y and Z set forth in various tables herein. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a tip rail length expressed in units of distance. The X, Y and Z values are connected by smooth continuing arcs that are joined smoothly with one another to form the nominal profile that defines the suction side scallop surface, the pressure side scallop surface, the suction side bevel surface, or the pressure side bevel surface.
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公开(公告)号：US11506064B2
公开(公告)日：2022-11-22
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：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：US11255198B1
公开(公告)日：2022-02-22
申请号：US17343864
申请日：2021-06-10
Applicant: General Electric Company
Inventor： William Scott Zemitis , James Tyson Balkcum, III
Abstract: A tip shroud for a turbine blade of a gas turbine system includes a body coupled to a radial outer end of an airfoil of the turbine blade. The tip shroud may include at least one circumferentially extending tip rail. A first edge wall of the tip shroud extends axially and radially outwardly from the body along at least one of a leading circumferential-facing edge or a trailing circumferential-facing edge of the body and includes a circumferentially facing surface. Cooling passages are defined in the body and extend circumferentially therein to cool an area near the first edge wall. The tip shroud includes an exit surface adjacent the first edge wall, where the exit surface includes an exit opening through which at least one of cooling passages exits the body. The exit surface is angled relative to the circumferentially facing surface of the first edge wall in a range of 15° to 80°.
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公开(公告)号：US20210087979A1
公开(公告)日：2021-03-25
申请号：US16575785
申请日：2019-09-19
Applicant: General Electric Company
Inventor： Travis J Packer , Brad Wilson VanTassel , William Scott Zemitis
IPC: F02C9/22
Abstract: A vane of a turbine system is provided. The vane includes: an internal cavity configured to receive a flow of cooling fluid; a variable thickness wall adjacent the internal cavity; and an impingement plate separating the variable thickness wall from the internal cavity, the impingement plate including a plurality of apertures for directing the cooling fluid into an impingement cavity and against the variable thickness wall, wherein the impingement plate is configured to follow a contour of the variable thickness wall.
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Patent Agency Ranking
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：US20180230817A1
公开(公告)日：2018-08-16
申请号：US15387975
申请日：2016-12-22
Applicant: General Electric Company
Inventor： Richard Gordon Rollings , Kevin Leon Bruce , William Scott Zemitis
Abstract: A method for modifying an airfoil shroud located at a tip of an airfoil is provided. A locating step locates a reference location in a first end edge. The reference location includes a portion of a fillet. A seal rail extends circumferentially along a radially outer surface of the airfoil shroud. The fillet extends along the radially outer surface and is positioned directly adjacent to the seal rail. A forming step forms a compound relief cut in the fillet without performing a weld process on the airfoil shroud to remove the reference location. The compound relief cut has a first cut having a first radius extending from the seal rail towards the first end edge, and a second cut having a second radius extending from an end of the first cut to the first end edge. Modifying the airfoil shroud is complete following forming the compound relief cut.
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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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9.发明申请公开(公告)号：US20220341332A1
公开(公告)日：2022-10-27
申请号：US17691377
申请日：2022-03-10
Applicant: General Electric Company
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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公开(公告)号：US11162432B2
公开(公告)日：2021-11-02
申请号：US16575785
申请日：2019-09-19
Applicant: General Electric Company
Inventor： Travis J Packer , Brad Wilson VanTassel , William Scott Zemitis
Abstract: A vane of a turbine system is provided. The vane includes: an internal cavity configured to receive a flow of cooling fluid; a variable thickness wall adjacent the internal cavity; and an impingement plate separating the variable thickness wall from the internal cavity, the impingement plate including a plurality of apertures for directing the cooling fluid into an impingement cavity and against the variable thickness wall, wherein the impingement plate is configured to follow a contour of the variable thickness wall.
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