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公开(公告)号：US20240011399A1
公开(公告)日：2024-01-11
申请号：US18142577
申请日：2023-05-02
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Nicholas William Rathay , Brendon James Leary , Gregory Terrence Garay , Gustavo Adolfo Ledezma , David Wayne Weber , Aaron Ezekiel Smith
CPC classification number: F01D5/187 , F01D5/20 , F01D5/141 , F05D2260/201 , F05D2260/205 , F01D5/3007
Abstract: An airfoil includes a body, a cooling passage, a first cooling cavity, a second cooling cavity, a cooling conduit, and a connecting conduit. The body defines an interior and includes a tip rail with an exterior surface extending between a first surface, a second surface, and a third surface. The cooling passage is formed within the interior. The first cooling cavity and the second cooling cavity are spaced from each other within the tip rail. The cooling conduit fluidly couples the cooling passage with the first cooling cavity. The connecting conduit fluidly couples the first cooling cavity to the second cooling cavity.
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公开(公告)号：US10605091B2
公开(公告)日：2020-03-31
申请号：US15194855
申请日：2016-06-28
Applicant: General Electric Company
Abstract: An apparatus and method for forming a film hole in an outer wall of an airfoil. The film hole includes a blind opening adjacent the interior of the airfoil and a hole adjacent the exterior of the airfoil. The blind opening fluidly couples to the hole to form the film hole for providing a volume of fluid as a surface cooling film along the exterior of the outer wall.
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公开(公告)号：US10370978B2
公开(公告)日：2019-08-06
申请号：US14884114
申请日：2015-10-15
Applicant: General Electric Company
Inventor： Matthew Lee Krumanaker , Steven Robert Brassfield , Robert Frederick Bergholz , Aaron Ezekiel Smith , Weston Nolan Dooley
Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can further comprise a leading edge cooling circuit defined by a supply passage, a pin bank passage divided into one or more sub-circuits by pin banks disposed within the pin bank passage, and at least first and second cooling passages. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.
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公开(公告)号：US20190017391A1
公开(公告)日：2019-01-17
申请号：US15648541
申请日：2017-07-13
Applicant: General Electric Company
Inventor： Thomas Earl Dyson , Nicholas William Rathay , Brendon James Leary , Gregory Terrence Garay , Gustavo Adolfo Ledezma , David Wayne Weber , Aaron Ezekiel Smith
Abstract: An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.
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公开(公告)号：US20180363468A1
公开(公告)日：2018-12-20
申请号：US15622266
申请日：2017-06-14
Applicant: General Electric Company
Inventor： Matthew Thomas Beyer , Gregory Terrence Garay , Tingfan Pang , Aaron Ezekiel Smith
Abstract: An apparatus and method for cooling an airfoil or engine component can include an outer wall defining an interior. A cooling circuit can be provided in the interior for directing flow of fluid and defining a flow direction. A plurality of cooling conduits can be arranged in the cooling circuit and organized into two or more sets of rows.
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Patent Agency Ranking
公开(公告)号：US20180291743A1
公开(公告)日：2018-10-11
申请号：US15481659
申请日：2017-04-07
Applicant: General Electric Company
Inventor： James Michael Hoffman , Weston Nolan Dooley , Matthew Lee Krumanaker , Aaron Ezekiel Smith , Steven Robert Brassfield
Abstract: A turbine engine can include an airfoil comprising an outer wall bounding an interior, as well as an airfoil cooling circuit located within the interior and including a feed tube separating into at least first and second branches. A flow divider can be included in the airfoil and positioned to confront the feed tube.
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公开(公告)号：US20180163544A1
公开(公告)日：2018-06-14
申请号：US15883498
申请日：2018-01-30
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , David Wayne Weber
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2240/304 , F05D2260/201 , F05D2260/203 , F05D2260/22141 , 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; 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; and a pressure side panel having a third pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel.
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公开(公告)号：US20170175550A1
公开(公告)日：2017-06-22
申请号：US14978235
申请日：2015-12-22
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , Gregory Thomas Foster , Michelle Jessica Iduate , Brendon James Leary , David Wayne Weber
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2240/304 , F05D2260/201 , F05D2260/203 , F05D2260/22141 , 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; 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; and a pressure side panel having a third pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel.
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公开(公告)号：US20170175544A1
公开(公告)日：2017-06-22
申请号：US14977175
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Aaron Ezekiel Smith , David Wayne Weber
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/188 , F05D2220/30 , F05D2240/305 , F05D2240/306 , F05D2260/201 , F05D2260/202 , F05D2260/22141
Abstract: A cooling system for a multi-wall blade according to an embodiment includes: a primary cooling air feed for providing cooling air; and a feed splitter coupled to the primary cooling air feed for splitting the cooling air provided by the primary cooling air feed between a pressure side cooling circuit and a suction side cooling circuit.
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公开(公告)号：US09528381B2
公开(公告)日：2016-12-27
申请号：US14143599
申请日：2013-12-30
Applicant: General Electric Company
Inventor： Stephen Paul Wassynger , Aaron Ezekiel Smith
IPC: F01D5/18
CPC classification number: F01D5/187 , F01D5/188 , F05D2240/305 , F05D2240/306 , F05D2250/71 , F05D2250/711 , F05D2250/712 , F05D2250/713 , F05D2250/75 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , 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 include a rib configuration that partitions the chamber and defines a flow passage having a first and a second side. The flow passage may include a port formed through the first side. A projection of a center axis of the port through the flow passage may define a strike point on the second side of the flow passage, and a backstrike recess may be positioned on the second side of the flow passage so to contain the strike point.
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。 涡轮机叶片可以包括肋构造，其分隔室并限定具有第一侧和第二侧的流动通道。 流路可以包括通过第一侧形成的端口。 通过流动通道的端口的中心轴线的突起可以限定流动通道的第二侧上的撞击点，并且反冲击凹口可以定位在流动通道的第二侧上以便容纳撞击点。
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