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公开(公告)号：US20200063574A1
公开(公告)日：2020-02-27
申请号：US16669756
申请日：2019-10-31
Applicant: General Electric Company
Abstract: A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.
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公开(公告)号：US10208607B2
公开(公告)日：2019-02-19
申请号：US15239940
申请日：2016-08-18
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Lana Maria Osusky
Abstract: A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the leading edge cavity with a second leading edge cavity.
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公开(公告)号：US20180363471A1
公开(公告)日：2018-12-20
申请号：US15624269
申请日：2017-06-15
Applicant: General Electric Company
Inventor： Zachary John Snider , Allison Christine Gose , Daniel Burnos , Gregory Thomas Foster
Abstract: A turbine airfoil includes a turbine component that includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a near wall source cavity disposed within the turbine component, and the near wall source cavity receives cooling air, and a second near wall cooling cavity disposed within the turbine component. The turbine airfoil further includes a first circuit completion plate disposed on a first end of the turbine component, and the first circuit completion plate fluidly couples the near wall source cavity to the second near wall cooling cavity.
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公开(公告)号：US10094569B2
公开(公告)日：2018-10-09
申请号：US14567761
申请日：2014-12-11
Applicant: General Electric Company
Inventor： Lewis Berkley Davis, Jr. , Gregory Thomas Foster , Kaitlin Marie Graham , Krishnakumar Venkataraman , Stanley Kevin Widener
Abstract: Embodiments of the present disclosure provide an apparatus comprising: a reaction chamber positioned between a first turbine stage of a power generation system and a turbine stage of the power generation system, wherein the turbine stage comprises a turbine nozzle and a turbine blade row; a plurality of injectors positioned on a wall of the reaction chamber; and a conduit in fluid communication with the plurality of injectors, wherein the conduit delivers at least one of fuel from a fuel supply line to the reaction chamber through the plurality of injectors.
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公开(公告)号：US10030526B2
公开(公告)日：2018-07-24
申请号：US14977200
申请日：2015-12-21
Applicant: General Electric Company
Inventor： Gregory Thomas Foster , Elisabeth Kraus Black , Michelle Jessica Iduate , Brendon James Leary , Jacob Charles Perry, II , David Wayne Weber
Abstract: A cooling system for a turbine bucket including a multi-wall blade and a platform. A cooling circuit for the multi-wall blade includes: an outer cavity circuit and a central cavity for collecting cooling air from the outer cavity circuit; a platform core air feed for receiving the cooling air from the central cavity; and an air passage for fluidly connecting the platform core air feed to a platform core of the platform.
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Patent Agency Ranking
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：US20180051574A1
公开(公告)日：2018-02-22
申请号：US15239940
申请日：2016-08-18
Applicant: General Electric Company
Inventor： David Wayne Weber , Gregory Thomas Foster , Lana Maria Osusky
CPC classification number: F01D5/187 , F01D5/147 , F01D9/02 , F01D25/12 , F02C3/04 , F05D2220/32 , F05D2240/303 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/205
Abstract: A cooling circuit according to an embodiment includes: a cooling circuit for a multi-wall blade, the cooling circuit including: a pressure side cavity with a surface adjacent a pressure side of the multi-wall blade; a suction side cavity with a surface adjacent a suction side of the multi-wall blade; a central cavity disposed between the pressure side and suction side cavities, the central cavity including no surfaces adjacent the pressure and suction sides of the multi-wall blade; a first leading edge cavity with surfaces adjacent the pressure and suction sides of the multi-wall blade; and at least one impingement opening for fluidly coupling the leading edge cavity with a second leading edge cavity.
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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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9.发明授权公开(公告)号：US09518475B2
公开(公告)日：2016-12-13
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：US20150098808A1
公开(公告)日：2015-04-09
申请号：US14049020
申请日：2013-10-08
Applicant: General Electric Company
Inventor： Victor John Morgan , Gregory Thomas Foster , Neelesh Nandkumar Sarawate , David Wayne Weber
IPC: F01D11/08
CPC classification number: F01D11/08 , F01D9/041 , F01D11/003 , F05D2230/60 , F05D2260/38 , Y10T29/4932
Abstract: A method and system for sealing between components within a gas turbine is provided. A first recess defined in a first component receives a seal member. A second recess defined in a second component adjacent the first component also receives the seal member. The first and second recesses are located proximate a hot gas path defined through the gas turbine, and define circumferential paths about the turbine axis. The seal member includes a sealing face that extends in a direction substantially parallel to the turbine axis. The seal member also includes a plurality of seal layers, wherein at least one of the seal layers includes at least one stress relief region for facilitating flexing of the first seal member.
Abstract translation: 提供了一种在燃气轮机内的部件之间进行密封的方法和系统。 限定在第一部件中的第一凹部接收密封构件。 限定在与第一部件相邻的第二部件中的第二凹部也接收密封部件。 第一和第二凹槽位于通过燃气涡轮机限定的热气路径附近，并限定围绕涡轮机轴线的圆周路径。 密封构件包括沿基本上平行于涡轮机轴线的方向延伸的密封面。 密封构件还包括多个密封层，其中至少一个密封层包括用于促进第一密封构件弯曲的至少一个应力释放区域。
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