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公开(公告)号：US20220205364A1
公开(公告)日：2022-06-30
申请号：US17137536
申请日：2020-12-30
Applicant: General Electric Company
Inventor： Brian Stephen Gray , Michael Anthony Wondrasek , Jan Emeric Agudo
Abstract: A turbomachine component includes a platform, a shank, and an airfoil. The platform includes a pressure side slash face and a suction side slash face. The shank extends radially inward from the platform. The airfoil extends radially outward from the platform. The airfoil includes a leading edge and a trailing edge. A cooling circuit is defined within the shank and the airfoil. The cooling circuit further includes a plurality of exit channels disposed along the trailing edge of the airfoil. The cooling circuit further includes at least one bypass conduit that extends from an inlet disposed in the cooling circuit to an outlet positioned on the pressure side slash face. The at least one bypass conduit being positioned radially inward of the plurality of exit channels.
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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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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：US12123319B2
公开(公告)日：2024-10-22
申请号：US17137536
申请日：2020-12-30
Applicant: General Electric Company
Inventor： Brian Stephen Gray , Michael Anthony Wondrasek , Jan Emeric Agudo
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2240/81 , F05D2260/2214 , F05D2260/232 , F05D2260/606
Abstract: A turbomachine component includes a platform, a shank, and an airfoil. The platform includes a pressure side slash face and a suction side slash face. The shank extends radially inward from the platform. The airfoil extends radially outward from the platform. The airfoil includes a leading edge and a trailing edge. A cooling circuit is defined within the shank and the airfoil. The cooling circuit further includes a plurality of exit channels disposed along the trailing edge of the airfoil. The cooling circuit further includes at least one bypass conduit that extends from an inlet disposed in the cooling circuit to an outlet positioned on the pressure side slash face. The at least one bypass conduit being positioned radially inward of the plurality of exit channels.
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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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