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公开(公告)号：US20210189887A1
公开(公告)日：2021-06-24
申请号：US16722020
申请日：2019-12-20
Applicant: General Electric Company
Inventor： Martin James Jasper , Claire Katherine Naioti , Melbourne James Myers , William Scott Zemitis , Stephen Douglas Shearer
Abstract: A rotor blade is provided. The rotor blade includes a main body having a shank, an airfoil extends radially outwardly from the shank, and a platform. The main body includes a pressure side slash face and a suction side slash face. A slot is defined within each of the pressure side slash face and the suction side slash face. The slot of the pressure side slash face and the slot of the suction side slash face each include an upstream end portion that defines an end and a main body portion extending from the upstream end portion. The upstream end portion tapers from the end to the main body portion. The main body portion further includes a retention wall that covers a portion of the end and that defines an opening. The retention wall further includes an inner retention surface. The retention wall defines an offset from the opening.
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公开(公告)号：US20200277864A1
公开(公告)日：2020-09-03
申请号：US16725654
申请日：2019-12-23
Applicant: General Electric Company
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：US10519785B2
公开(公告)日：2019-12-31
申请号：US15431950
申请日：2017-02-14
Applicant: General Electric Company
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：US20190292914A1
公开(公告)日：2019-09-26
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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Patent Agency Ranking
公开(公告)号：US20180230821A1
公开(公告)日：2018-08-16
申请号：US15431981
申请日：2017-02-14
Applicant: General Electric Company
Inventor： William Scott Zemitis , Mahesh Pasupuleti , Bryan David Lewis , Melbourne James Myers
CPC classification number: F01D5/225 , F01D5/147 , F01D5/20 , F05D2220/32 , F05D2240/307
Abstract: A turbine blade includes an airfoil that extends from a root end to a tip end. A tip shroud extends from the tip end. The turbine blade further includes a pressure side fillet. The pressure side fillet couples the tip end to the tip shroud. The pressure side fillet includes a first protrusion located adjacent to the tip end and a second protrusion located radially inward from the first protrusion.
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公开(公告)号：US20180230816A1
公开(公告)日：2018-08-16
申请号：US15431939
申请日：2017-02-14
Applicant: General Electric Company
Inventor： William Scott Zemitis , Richard Ryan Pilson , Melbourne James Myers
CPC classification number: F01D5/20 , F01D5/225 , F01D11/08 , F01D25/24 , F05B2240/11 , F05D2240/81 , F05D2260/20 , F05D2260/30
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：US20180016902A1
公开(公告)日：2018-01-18
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
CPC classification number: F01D5/141 , F01D5/145 , F05D2250/74 , Y02E20/16 , Y02T50/673
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：US20150064010A1
公开(公告)日：2015-03-05
申请号：US14011784
申请日：2013-08-28
Applicant: General Electric Company
IPC: F01D5/18
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.
Abstract translation: 本申请提供了一种涡轮机桶。 涡轮机桶可以包括附接到翼型件的翼型件和顶端罩。 尖端护罩可以包括冷却芯和增强的冷却表面。
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公开(公告)号：US20150040582A1
公开(公告)日：2015-02-12
申请号：US13961194
申请日：2013-08-07
Applicant: General Electric Company
Inventor： Zhirui Dong , Xiuhang James Zhang , Melbourne James Myers , Camilo Andres Sampayo
IPC: F01D5/18
Abstract: A cooling circuit for a turbine bucket having an airfoil portion includes a trailing edge cooling circuit portion provided with a first radially outwardly directed inlet passage intermediate leading and trailing edges of the airfoil portion of the bucket, extending from a platform portion of the bucket to a location adjacent a radially outer tip of the bucket, and connecting to a second radially inwardly directed passage extending from a location adjacent the radially outer tip to a location adjacent the platform portion. The second radially inwardly directed passage connects to a third trailing edge region passage, and a plurality of crossover passages connect a radially outer half of the second radially inwardly directed passage to a radially outer half of the third trailing edge region passage.
Abstract translation: 具有翼型部分的涡轮机叶片的冷却回路包括后缘冷却回路部分，该后缘冷却回路部分设置有从铲斗的平台部分延伸到铲斗的翼型部分的前缘和后缘之间的第一径向向外的入口通道 位于邻近所述铲斗的径向外部末端并且连接到从邻近所述径向外部末端的位置延伸到邻近所述平台部分的位置的第二径向向内指向的通道。 第二径向向内定向的通道连接到第三后缘区域通道，并且多个交叉通道将第二径向向内定向通道的径向外半部连接到第三后缘区域通道的径向外半部。
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