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公开(公告)号：US10738651B2
公开(公告)日：2020-08-11
申请号：US15995085
申请日：2018-05-31
Applicant: General Electric Company
Inventor： Brad Wilson VanTassel , Joseph Anthony Weber , Bryan David Lewis , Travis J Packer
Abstract: A turbine that includes an inner shroud segment having a cooling configuration in which interior channels are configured to receive and direct a coolant. The cooling configuration may include a pair of counterflowing crossflow channels in which a first crossflow channel extends side-by-side with a neighboring second crossflow channel; and a feed and outlet channel configuration comprising neighboring feed and outlet channels. The feed channel may connect at a first connection to an upstream end of the first crossflow channel and the outlet channel may connect at a second connection to a downstream end of the second crossflow channel. The feed channel may extend in an inner radial direction from an inlet to the first connection. The outlet channel may extend in an outer radial direction from the second connection to an outlet. The feed channel may include a section that undercuts the outlet channel.
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公开(公告)号：US10526899B2
公开(公告)日：2020-01-07
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
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：US20190368378A1
公开(公告)日：2019-12-05
申请号：US15995085
申请日：2018-05-31
Applicant: General Electric Company
Inventor： Brad Wilson VanTassel , Joseph Anthony Weber , Bryan David Lewis , Travis J Packer
Abstract: A turbine that includes an inner shroud segment having a cooling configuration in which interior channels are configured to receive and direct a coolant. The cooling configuration may include a pair of counterflowing crossflow channels in which a first crossflow channel extends side-by-side with a neighboring second crossflow channel; and a feed and outlet channel configuration comprising neighboring feed and outlet channels. The feed channel may connect at a first connection to an upstream end of the first crossflow channel and the outlet channel may connect at a second connection to a downstream end of the second crossflow channel. The feed channel may extend in an inner radial direction from an inlet to the first connection. The outlet channel may extend in an outer radial direction from the second connection to an outlet. The feed channel may include a section that undercuts the outlet channel.
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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：US20210388729A1
公开(公告)日：2021-12-16
申请号：US16985369
申请日：2020-08-05
Applicant: General Electric Company
Inventor： Stephen Walter Newman , Bryan David Lewis , Debdulal Das
Abstract: A cast turbine nozzle includes an airfoil having a body including a suction side, a pressure side opposing the suction side, a leading edge spanning between the pressure side and the suction side, a trailing edge opposing the leading edge and spanning between the pressure side and the suction side, and a cooling cavity defined by an inner surface of the body. The nozzle also includes at least one endwall connected with the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, and a plurality of heat transfer protrusions extending inwardly from the inner surface within the body, the plurality of heat transfer protrusions extending from the leading edge along the suction side and along the pressure side in a radially staggered columnar pattern. The inner surface includes a planar surface extending between adjacent heat transfer protrusions.
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Patent Agency Ranking
公开(公告)号：US10989070B2
公开(公告)日：2021-04-27
申请号：US15995072
申请日：2018-05-31
Applicant: General Electric Company
Inventor： Brad Wilson VanTassel , Evan Andrew Sewall , Joseph Anthony Weber , Travis J Packer , Joseph Daniel Franzen, Jr. , Bryan David Lewis
Abstract: A turbine having a stationary shroud ring formed about rotor blades. The stationary shroud ring may include an inner shroud segment. The inner shroud segment may include a cooling configuration that includes a crossflow channel. The crossflow channel may extend lengthwise between an upstream end and a downstream end, and, therebetween, include a junction point that divides the crossflow channel lengthwise into upstream and downstream sections, with the upstream section extending between the upstream end and the junction point, and the downstream section extending between the junction point and the downstream end. The crossflow channel may have a cross-sectional flow area that varies lengthwise such that a cross-sectional flow area of the upstream section decreases between the upstream end and the junction point, and a cross-sectional flow area of the downstream section increases between the junction point and the downstream end.
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公开(公告)号：US10689993B2
公开(公告)日：2020-06-23
申请号：US16191614
申请日：2018-11-15
Applicant: General Electric Company
Inventor： Sylvain Pierre , Bryan David Lewis , Debdulal Das , Stephen Walter Newman
Abstract: A turbine nozzle having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.
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公开(公告)号：US10001013B2
公开(公告)日：2018-06-19
申请号：US14198659
申请日：2014-03-06
Applicant: General Electric Company
Inventor： Brad Wilson VanTassel , James Ryan Connor , Bryan David Lewis , Adebukola Oluwaseun Benson
CPC classification number: F01D5/082 , B23P15/02 , F01D5/187 , F01D11/24 , F05D2240/11 , F05D2240/81 , F05D2260/201 , Y02T50/676 , Y10T29/49341
Abstract: Platform cooling arrangements in a turbine rotor blade include a feedhole that extends from the suction side slash face to the interior cooling passage, and, one or more branch holes that each extends from the feedhole to the suction side slash face such that coolant flows from the interior cooling passage, through the feedhole to the one or more branch holes and exits the platform along the suction side slash face.
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公开(公告)号：US09909436B2
公开(公告)日：2018-03-06
申请号：US14801187
申请日：2015-07-16
Applicant: General Electric Company
Inventor： Christopher Lee Golden , Dustin Michael Earnhardt , Michelle Jessica Iduate , Bryan David Lewis , Christopher Donald Porter , David Wayne Weber
IPC: F01D9/06
CPC classification number: F01D9/065 , F05D2240/81 , Y02T50/676
Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade, which can include: an endwall coupled to a radial end of an airfoil, relative to a rotor axis of a turbomachine; and a substantially crescent-shaped chamber positioned within the endwall and radially displaced from a trailing edge of the airfoil, the substantially crescent-shaped chamber receiving a cooling fluid from a cooling circuit, wherein the substantially crescent-shaped chamber extends from a fore section positioned proximal to one of a pressure side surface and a suction side surface of the airfoil to an aft section positioned proximal to the trailing edge of the airfoil and the other of the pressure side surface and the suction side surface of the airfoil, wherein the aft section of the substantially crescent-shaped chamber is in fluid communication with the fore section of the substantially crescent-shaped chamber.
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公开(公告)号：US20170016348A1
公开(公告)日：2017-01-19
申请号：US14801187
申请日：2015-07-16
Applicant: General Electric Company
Inventor： Christopher Lee Golden , Dustin Michael Earnhardt , Michelle Jessica Iduate , Bryan David Lewis , Christopher Donald Porter , David Wayne Weber
CPC classification number: F01D9/065 , F05D2240/81 , Y02T50/676
Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade, which can include: an endwall coupled to a radial end of an airfoil, relative to a rotor axis of a turbomachine; and a substantially crescent-shaped chamber positioned within the endwall and radially displaced from a trailing edge of the airfoil, the substantially crescent-shaped chamber receiving a cooling fluid from a cooling circuit, wherein the substantially crescent-shaped chamber extends from a fore section positioned proximal to one of a pressure side surface and a suction side surface of the airfoil to an aft section positioned proximal to the trailing edge of the airfoil and the other of the pressure side surface and the suction side surface of the airfoil, wherein the aft section of the substantially crescent-shaped chamber is in fluid communication with the fore section of the substantially crescent-shaped chamber.
Abstract translation: 本公开的实施例提供了一种用于固定叶片的冷却结构，其可以包括：相对于涡轮机的转子轴线耦合到翼型件的径向端部的端壁; 以及基本上月牙形的腔室，其定位在端壁内并且从翼型件的后缘径向偏移，基本上月牙形的腔室从冷却回路接收冷却流体，其中基本上月牙形的腔室从位于 靠近所述翼型件的压力侧表面和吸力侧表面之一到位于所述翼型件的后缘附近并且所述翼型件的所述压力侧表面和所述吸力侧表面中的另一个的后部，其中所述后部 基本上月牙形的腔室与基本上新月形的腔室的前部部分流体连通。
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