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公开(公告)号：US09938836B2
公开(公告)日：2018-04-10
申请号：US14978224
申请日：2015-12-22
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , F01D9/041 , F05D2220/32 , F05D2240/304 , F05D2260/20 , F05D2260/2212 , Y02T50/676
Abstract: One aspect of the disclosure provides for a turbine airfoil. The turbine airfoil may include a trailing edge having: a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel; a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; and a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section.
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公开(公告)号：US20170175547A1
公开(公告)日：2017-06-22
申请号：US14977247
申请日：2015-12-21
Applicant: General Electric Company
CPC classification number: F01D5/187 , F01D5/186 , F02C3/04 , F05D2220/32 , F05D2240/305 , F05D2240/307 , F05D2250/185 , F05D2260/205
Abstract: A cooling system according to an embodiment includes: a serpentine cooling circuit, the serpentine cooling circuit including a first leg extending in a first direction, a second leg extending in a second direction, and a turn fluidly coupling the first leg and the second leg; and an air feed cavity for supplying cooling air to the serpentine cooling circuit; wherein the first leg of the serpentine cooling circuit extends radially outward from and at least partially covers at least one central plenum of a multi-wall blade, and wherein the second leg of the serpentine cooling circuit extends radially outward from and at least partially covers a first set of near wall cooling channels of the multi-wall blade.
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公开(公告)号：US09669458B2
公开(公告)日：2017-06-06
申请号：US14173949
申请日：2014-02-06
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Benjamin Paul Lacy , Aaron Ezekiel Smith , Dustin Michael Earnhardt
CPC classification number: B22C7/02 , B22C9/04 , B22C9/10 , B22C9/103 , B22C9/108 , B22C9/24 , F01D5/186 , F05D2230/211 , F05D2240/81 , F05D2260/204
Abstract: A core for forming micro channels within a turbine component is provided. The core includes a base comprising a first side and a second side; and a core assembly coupled to the second side. The core assembly further includes a plurality of channel members, wherein each channel member has a first end, a second end, and a channel body coupled to and extending between said first end and said second end. The channel body includes a channel shape configured to form the micro channels within the turbine component.
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公开(公告)号：US20170130592A1
公开(公告)日：2017-05-11
申请号：US14938261
申请日：2015-11-11
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Metodi Blagoev Zlatinov , Thomas Earl Dyson
IPC: F01D5/18
CPC classification number: F01D5/186 , F05D2260/202 , Y02T50/672 , Y02T50/676
Abstract: A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.
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公开(公告)号：US20150184522A1
公开(公告)日：2015-07-02
申请号：US14143587
申请日：2013-12-30
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Stanley Frank Simpson , Lisa Anne Wichmann
CPC classification number: F01D5/187 , B23P15/04 , F01D5/147 , F01D5/188 , F01D5/284 , F05D2240/305 , F05D2240/306 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/22141 , F05D2260/941 , F05D2300/17 , F05D2300/20 , Y02T50/672 , Y02T50/676 , Y10T29/49337 , Y10T29/49341
Abstract: A turbine blade that includes an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may further include a rib configuration that partitions the chamber into radially extending flow passages, and a blade outer shell that defines an outer surface of the airfoil. The rib configuration is a non-integral component to the blade outer shell.
Abstract translation: 一种涡轮机叶片，其包括由凹形压力侧外壁和凸形吸入侧外壁限定的翼型件，所述翼型件沿着前缘和后缘连接，并且在其间形成用于接收冷却剂流的径向延伸的室。 涡轮叶片还可以包括将腔室分隔成径向延伸的流动通道的肋构造，以及限定翼型件的外表面的叶片外壳。 肋构造是叶片外壳的非整体部件。
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Patent Agency Ranking
公开(公告)号：US20150184519A1
公开(公告)日：2015-07-02
申请号：US14143443
申请日：2013-12-30
Applicant: General Electric Company
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/188 , F05D2240/305 , F05D2240/306 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/22141 , Y02T50/676
Abstract: A turbine blade having an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may further include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include a camber line rib having a wavy profile. The wavy profile may include at least one back-and-forth “S” shape.
Abstract translation: 一种具有由凹形压力侧外壁和凸形吸入侧外壁限定的翼型件的涡轮机叶片，其沿着前缘和后缘连接，并且在它们之间形成用于接收冷却剂流动的径向延伸室。 涡轮叶片还可以包括将腔室分隔成径向延伸的流动通道的肋构型。 肋构造可以包括具有波浪形轮廓的弧形线肋。 波浪形轮廓可以包括至少一个前后“S”形。
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公开(公告)号：US20150184517A1
公开(公告)日：2015-07-02
申请号：US14038076
申请日：2013-09-26
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , John Wesley Harris, JR.
CPC classification number: F01D5/186 , B23H9/14 , B23K26/389 , B26F1/26 , F01D5/141 , F01D5/187 , F05D2230/10 , F05D2230/12 , Y02T50/676
Abstract: A method for fabricating an airfoil includes forming a diffuser section in an exterior surface of the airfoil. The diffuser section is defined by at least an outer surface and an inner surface that converge at a stop surface. The method also includes positioning a drilling element of a drilling device on the stop surface. The method further includes orienting the drilling element at a first angle relative to the exterior surface. The method also includes forming, using the drilling element, a cooling channel extending through the airfoil from the stop surface to an interior surface, thereby forming the cooling channel at substantially the first angle.
Abstract translation: 一种用于制造翼型的方法包括在翼型件的外表面中形成扩散器部分。 扩散器部分由至少外表面和在止动表面处会聚的内表面限定。 该方法还包括将钻井装置的钻孔元件定位在止动表面上。 该方法还包括相对于外表面以第一角度定向钻孔元件。 该方法还包括使用钻孔元件形成从止动表面延伸穿过翼型件到内表面的冷却通道，从而以大致第一角度形成冷却通道。
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58.发明申请公开(公告)号：US20150118022A1
公开(公告)日：2015-04-30
申请号：US14064918
申请日：2013-10-28
Applicant: General Electric Company
Inventor： David Wayne WEBER , Gregory Thomas Foster , Aaron Ezekiel Smith
CPC classification number: F01D11/24 , F01D9/04 , F01D11/005 , F05D2240/11 , F05D2240/81 , F05D2260/205
Abstract: In one example, an arcuate segment for a ring-shaped, rotary machine component such as a stator nozzle or bucket shroud, includes a segment body having an end face formed with a circumferentially-facing seal slot adapted to receive a seal extending between the segment body and a corresponding seal slot in an adjacent segment body to seal a radially-extending gap between the adjacent segment bodies. A cooling channel is provided in the segment body in proximity to the seal slot, and is adapted to be supplied with cooling air. A passage extends from the cooling channel into the seal slot, at a location where the cooling air can be supplied to the higher pressure area on the radially-outer side of the seal.
Abstract translation: 在一个示例中，用于环形旋转机器部件（例如定子喷嘴或铲斗护罩）的弧形段包括段体，其具有形成有面向周向的密封槽的端面，其适于接收在段 主体和相邻的分段体中相应的密封槽，以密封相邻分段体之间的径向延伸的间隙。 冷却通道设置在分段主体中，靠近密封槽，并且适于供应冷却空气。 通道从冷却通道延伸到密封槽中，在冷却空气可被供应到密封件的径向外侧上的较高压力区域的位置处。
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公开(公告)号：US12215602B2
公开(公告)日：2025-02-04
申请号：US18599486
申请日：2024-03-08
Applicant: General Electric Company
Abstract: A component for a turbine engine comprises a wall having a first wall surface and a second wall surface; and a cooling hole comprising a connecting passage extending between an inlet at the first wall surface and an outlet located at the second wall surface. The connecting passage includes: a metering section extending from the inlet toward the outlet and defining a centerline, and a diffusing section at the outlet defining first and second side walls, a first junction between the first side wall and the metering section and a second junction between the second side wall the metering section, the first side wall extending between the first junction and the outlet, and the second side wall extending between the second junction and the outlet. A metering section distance is measured between the centerline and a metering section wall of the metering section.
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公开(公告)号：US20210215065A1
公开(公告)日：2021-07-15
申请号：US17218678
申请日：2021-03-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jonathan Russell Ratzlaff , Aaron Ezekiel Smith
Abstract: A hanger for a turbine engine can include a first surface confronting a cooling airflow, a second surface facing a heated airflow, and a third surface radially outward of the first surface. The hanger can also include a cyclonic separator with a dirty air inlet and a clean air outlet, as well as a cooling air circuit extending through the cyclonic separator.
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