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公开(公告)号：US11066934B1
公开(公告)日：2021-07-20
申请号：US16824977
申请日：2020-03-20
Applicant: General Electric Company
Inventor： Alexander Stein , Mark Steven Honkomp , Mehmet Suleyman Ciray
IPC: F01D5/12
Abstract: The present application provides a turbine rotor blade including an airfoil shape and a trailing edge shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, while the trailing edge profile is defined by Table II. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in the unit of distance (e.g., inches). The X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
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公开(公告)号：US11066935B1
公开(公告)日：2021-07-20
申请号：US16824959
申请日：2020-03-20
Applicant: General Electric Company
Inventor： Alexander Stein , Mark Steven Honkomp , Mehmet Suleyman Ciray
IPC: F01D5/14
Abstract: Rotor blades and turbomachines are provided. A rotor blade includes a platform and an airfoil extending radially from a root proximate the platform to a tip. The airfoil includes a leading edge and a trailing edge. The airfoil further includes a pressure side surface extending between the leading edge and the trailing edge. The airfoil also includes a suction side surface disposed opposite the pressure side surface and extending between the leading edge and the trailing edge. The leading edge, the trailing edge, the pressure side surface, and the suction side surface collectively define a first profile at the tip and a second profile radially inward from the tip. The first profile includes a suction side overhang, a pressure side overhang, and a pressure side underhang relative to the second profile.
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公开(公告)号：US20170306765A1
公开(公告)日：2017-10-26
申请号：US15137341
申请日：2016-04-25
Applicant: General Electric Company
Inventor： Jalindar Appa Walunj , Mark Steven Honkomp
CPC classification number: F01D5/187 , F01D5/147 , F02C7/12 , F05D2220/32 , F05D2240/304 , F05D2240/35 , F05D2250/184 , F05D2260/202 , F05D2260/2212
Abstract: The present disclosure is directed to an airfoil for a gas turbine rotor blade. The airfoil includes a pressure side wall and a suction side wall connected to the pressure side wall at a leading edge portion and a trailing edge portion. The pressure side wall and the suction side wall collectively define an internal cavity within the airfoil. A plurality of pins is disposed within the internal cavity. The trailing edge portion defines a first cooling passage having a first inlet spaced apart from a first outlet by a first length and a second cooling passage comprising a second inlet spaced apart from a second outlet by a second length. The first length is greater than the second length.
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公开(公告)号：US11629601B2
公开(公告)日：2023-04-18
申请号：US16835476
申请日：2020-03-31
Applicant: General Electric Company
Inventor： Mark Steven Honkomp , William Scott Zemitis , Melbourne James Myers , Jacob Charles Perry, II
IPC: F01D5/18
Abstract: A rotor blade for a turbomachine is provided. The rotor blade includes a platform, an airfoil extending from the platform, and a cooling circuit extending within the platform and the airfoil. The cooling circuit includes a plurality of cooling passages defined by a plurality of ribs. The plurality of ribs includes an offset rib.
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公开(公告)号：US10982553B2
公开(公告)日：2021-04-20
申请号：US16207995
申请日：2018-12-03
Applicant: General Electric Company
Abstract: A tip for a turbine component, turbine rotor blade or tip of a blade, is disclosed. The tip includes a tip plate configured to be coupled at a tip end of an airfoil chamber; and a tip rail extending radially from the tip plate, the tip rail disposed near or at a periphery of the tip plate. The trip rail includes a cooling structure constituting at least a portion of the tip rail. The cooling structure is in fluid communication with the airfoil chamber, and includes a plurality of repeating, three dimensional unit cells. Each unit cell defines a flow passage that is in fluid communication with the flow passage of at least one other unit cell. The flow passages of the 3D unit cells create a tortuous cooling passage in at least a portion of the tip rail.
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Patent Agency Ranking
公开(公告)号：US10934852B2
公开(公告)日：2021-03-02
申请号：US16208001
申请日：2018-12-03
Applicant: General Electric Company
Inventor： Mark Steven Honkomp , Mehmet Suleyman Ciray , Mark Lawrence Hunt
Abstract: A turbine blade tip cooling system includes a turbine blade having a tip cavity, a tip rail surrounding at least a portion of the tip cavity and at least one internal cooling cavity. The tip rail has an inner rail surface, an outer rail surface, an end surface and at least one tip rail pocket open at the end surface and fluidly connected to the at least one internal cooling cavity that carries a coolant. A tip rail cooling insert attaches to the at least one tip rail pocket, and has insert cooling channel(s) and a coolant collection plenum for directing coolant from the at least one internal cooling cavity to the insert cooling channel(s).
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公开(公告)号：US20210017864A1
公开(公告)日：2021-01-21
申请号：US16876615
申请日：2020-05-18
Applicant: General Electric Company
Inventor： Mark Steven Honkomp , Mark Lawrence Hunt , Frederick Whitfield Dantzler , Yan Cui , Ethan Conrad Schaeffer
IPC: F01D5/18
Abstract: A tip rail cooling insert for attaching into a tip rail pocket in a tip rail of a turbine blade is disclosed. The insert includes a first inner layer defining at least one first insert cooling channel therein, the first inner layer including a pair of spaced legs defining a first coolant collection plenum with at least the tip rail pocket for directing coolant from at least one internal cooling cavity in the turbine blade to the at least one first insert cooling channel. Each of the pair of spaced legs has an angled outer end configured to accommodate rounded inner corners of the tip rail pocket. A first outer layer is on a first side of the first inner layer, and a second outer layer is on a second side of the first inner layer.
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公开(公告)号：US20200173288A1
公开(公告)日：2020-06-04
申请号：US16208001
申请日：2018-12-03
Applicant: General Electric Company
Inventor： Mark Steven Honkomp , Mehmet Suleyman Ciray , Mark Lawrence Hunt
IPC: F01D5/18
Abstract: A turbine blade tip cooling system includes a turbine blade having a tip cavity, a tip rail surrounding at least a portion of the tip cavity and at least one internal cooling cavity. The tip rail has an inner rail surface, an outer rail surface, an end surface and at least one tip rail pocket open at the end surface and fluidly connected to the at least one internal cooling cavity that carries a coolant. A tip rail cooling insert attaches to the at least one tip rail pocket, and has insert cooling channel(s) and a coolant collection plenum for directing coolant from the at least one internal cooling cavity to the insert cooling channel(s).
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公开(公告)号：US20170226864A1
公开(公告)日：2017-08-10
申请号：US15019516
申请日：2016-02-09
Applicant: General Electric Company
Inventor： Mark Steven Honkomp , Xiaoyong Fu , Paul Kendall Smith , Jalindar Appa Walunj
IPC: F01D5/14
CPC classification number: F01D5/141 , F01D5/143 , F01D5/147 , F05D2220/30 , F05D2250/74 , Y02T50/673
Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric contour proximate a junction between the base and the airfoil.
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公开(公告)号：US11208902B2
公开(公告)日：2021-12-28
申请号：US16876615
申请日：2020-05-18
Applicant: General Electric Company
Inventor： Mark Steven Honkomp , Mark Lawrence Hunt , Frederick Whitfield Dantzler , Yan Cui , Ethan Conrad Schaeffer
Abstract: A tip rail cooling insert for attaching into a tip rail pocket in a tip rail of a turbine blade is disclosed. The insert includes a first inner layer defining at least one first insert cooling channel therein, the first inner layer including a pair of spaced legs defining a first coolant collection plenum with at least the tip rail pocket for directing coolant from at least one internal cooling cavity in the turbine blade to the at least one first insert cooling channel. Each of the pair of spaced legs has an angled outer end configured to accommodate rounded inner corners of the tip rail pocket. A first outer layer is on a first side of the first inner layer, and a second outer layer is on a second side of the first inner layer.
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