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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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公开(公告)号：US10247006B2
公开(公告)日：2019-04-02
申请号：US15207750
申请日：2016-07-12
Applicant: General Electric Company
Inventor： Dennis Scott Holloway , Adebukola Oluwaseun Benson , Melbourne James Myers , Peter Paul Pirolla , William Scott Zemitis
Abstract: Various embodiments of the invention include turbine blades and systems employing such blades. Various particular embodiments include a turbine blade 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, wherein the trailing edge defines a radial throat distribution between the airfoil and an adjacent airfoil; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge.
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公开(公告)号：US09759070B2
公开(公告)日：2017-09-12
申请号：US14011784
申请日：2013-08-28
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D5/186 , F01D5/225 , F05D2240/307 , F05D2240/81 , F05D2260/20 , F05D2260/201 , F05D2260/202
Abstract: The present application provides a turbine bucket. The turbine bucket may include an airfoil and a tip shroud attached to the airfoil. The tip shroud may include a cooling core and an enhanced cooling surface.
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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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Patent Agency Ranking
公开(公告)号：US10247009B2
公开(公告)日：2019-04-02
申请号：US15163061
申请日：2016-05-24
Applicant: General Electric Company
Inventor： Melbourne James Myers , Xiuzhang James Zhang , Stuart Samuel Collins , Camilo Andres Sampayo , Joseph Block
Abstract: The present disclosure is directed to a rotor blade for a gas turbine system. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A shank portion extends radially inwardly from the radially inner surface of the platform. The shank portion and the platform collectively define a shank pocket. An airfoil extends radially outwardly from the radially outer surface of the platform. The shank portion, the platform, and the airfoil collectively define a cooling passage extending from a cooling passage inlet defined by the shank portion or the platform and directly coupled to the shank pocket through the platform to a cooling passage outlet defined by the airfoil.
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公开(公告)号：US10066488B2
公开(公告)日：2018-09-04
申请号：US14955563
申请日：2015-12-01
Applicant: General Electric Company
Inventor： Melbourne James Myers , Camilo Andres Sampayo , Xiuzhang James Zhang
Abstract: A turbomachine blade is disclosed including an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil. A platform may couple the airfoil to a shank, the platform including a trailing edge extending downstream relative to the shank. At least one cooling conduit delivers a cooling fluid radially inward from at least one of the cooling fluid plenum and the trailing edge cooling opening to a wheel space that is adjacent the shank and radially inward from the trailing edge of the platform. A related turbomachine is also disclosed.
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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：US20170342841A1
公开(公告)日：2017-11-30
申请号：US15163061
申请日：2016-05-24
Applicant: General Electric Company
Inventor： Melbourne James Myers , Xiuzhang James Zhang , Stuart Samuel Collins , Camilo Andres Sampayo , Joseph Block
IPC: F01D5/18
CPC classification number: F01D5/18 , F01D5/143 , F01D5/186 , F05D2220/32 , F05D2240/304 , F05D2240/306 , F05D2240/81 , F05D2260/20
Abstract: The present disclosure is directed to a rotor blade for a gas turbine system. The rotor blade includes a platform having a radially inner surface and a radially outer surface. A shank portion extends radially inwardly from the radially inner surface of the platform. The shank portion and the platform collectively define a shank pocket. An airfoil extends radially outwardly from the radially outer surface of the platform. The shank portion, the platform, and the airfoil collectively define a cooling passage extending from a cooling passage inlet defined by the shank portion or the platform and directly coupled to the shank pocket through the platform to a cooling passage outlet defined by the airfoil.
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公开(公告)号：US20170152752A1
公开(公告)日：2017-06-01
申请号：US14955563
申请日：2015-12-01
Applicant: General Electric Company
Inventor： Melbourne James Myers , Camilo Andres Sampayo , Xiuzhang James Zhang
CPC classification number: F01D5/187 , F01D5/082 , F01D5/147 , F05D2240/304 , F05D2240/80 , F05D2260/20 , Y02T50/676
Abstract: A turbomachine blade is disclosed including an airfoil including a cooling fluid plenum extending therein and a trailing edge cooling opening extending from the cooling fluid plenum through a trailing edge of the airfoil. A platform may couple the airfoil to a shank, the platform including a trailing edge root extending downstream relative to the shank. At least one cooling conduit delivers a cooling fluid radially inward from at least one of the cooling fluid plenum and the trailing edge cooling opening to a wheel space that is adjacent the shank and radially inward from the trailing edge root. A related turbomachine is also disclosed.
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