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1.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：US10683759B2
公开(公告)日：2020-06-16
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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3.发明授权公开(公告)号：US10265792B2
公开(公告)日：2019-04-23
申请号：US15806565
申请日：2017-11-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Yan Cui , Srikanth Chandrudu Kottilingam , Brian Lee Tollison , Timothy Neal Pletcher , Richard Ryan Pilson
IPC: B23K1/00 , B22F7/06 , B22F5/04 , B23F5/00 , B23K9/04 , B23K15/00 , B23K35/36 , B23K35/02 , B32B15/01 , C23C30/00 , B22F5/00 , B23K10/02 , B23K26/34 , F01D5/14 , F01D5/28 , B22F7/04 , B23K101/00
Abstract: A hybrid article is disclosed including a coating disposed on and circumscribing the lateral surface of a core having a core material. The coating includes about 35% to about 95% of a first metallic material having a first melting point, and about 5% to about 65% of a second metallic material having a second melting point lower than the first melting point. The coating is sinter-bonded to the core. A method for forming the hybrid article is disclosed including disposing the core in a die, introducing a slurry having the metallic materials into a gap between the lateral surface and the die, 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 both.
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公开(公告)号：US11629603B2
公开(公告)日：2023-04-18
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：US10704392B2
公开(公告)日：2020-07-07
申请号：US15933568
申请日：2018-03-23
Applicant: General Electric Company
Inventor： William Scott Zemitis , Melbourne James Myers , Richard Ryan Pilson , Jacob Charles Perry, II
Abstract: A turbine rotor blade including an airfoil, tip shroud, and fillet formed therebetween. The fillet defines a fillet profile variable about the intersection for connecting the tip shroud and airfoil and facilitating aerodynamic airflow. The fillet includes a pressure side fillet. The pressure side fillet comprises a pressure side fillet profile per points within a first set of points of X, Y and Z coordinate values in a Cartesian coordinate system, as set forth in Table I, where X, Y and Z are distances in inches from an origin and, when the points are connected by smooth, continuing arcs, the points define the pressure side fillet profile of the pressure side fillet. The first set of points includes points between and including point 1 and point 50 of each reference plane between and including a reference plane H and a reference plane W, as set forth in Table I.
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Patent Agency Ranking
公开(公告)号：US20190292913A1
公开(公告)日：2019-09-26
申请号：US15933568
申请日：2018-03-23
Applicant: General Electric Company
Inventor： William Scott Zemitis , Melbourne James Myers , Richard Ryan Pilson , Jacob Charles Perry, II
Abstract: A turbine rotor blade including an airfoil, tip shroud, and fillet formed therebetween. The fillet defines a fillet profile variable about the intersection for connecting the tip shroud and airfoil and facilitating aerodynamic airflow. The fillet includes a pressure side fillet. The pressure side fillet comprises a pressure side fillet profile per points within a first set of points of X, Y and Z coordinate values in a Cartesian coordinate system, as set forth in Table I, where X, Y and Z are distances in inches from an origin and, when the points are connected by smooth, continuing arcs, the points define the pressure side fillet profile of the pressure side fillet. The first set of points includes points between and including point 1 and point 50 of each reference plane between and including a reference plane H and a reference plane W, as set forth in Table I.
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公开(公告)号：US10400610B2
公开(公告)日：2019-09-03
申请号：US15431939
申请日：2017-02-14
Applicant: General Electric Company
Inventor： William Scott Zemitis , Richard Ryan Pilson , Melbourne James Myers
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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公开(公告)号：US20180230829A1
公开(公告)日：2018-08-16
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：US20180230820A1
公开(公告)日：2018-08-16
申请号：US15431950
申请日：2017-02-14
Applicant: General Electric Company
CPC classification number: F01D5/24 , B21D53/78 , F01D5/143 , F01D5/16 , F01D5/22 , F01D5/26 , F01D5/3015 , F01D25/06 , F05D2240/80 , F05D2260/96
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：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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