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公开(公告)号：US20210140328A1
公开(公告)日：2021-05-13
申请号：US17151799
申请日：2021-01-19
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Thomas Raymond Farrell , Markus Feigl
Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.
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2.发明申请公开(公告)号：US20200256204A1
公开(公告)日：2020-08-13
申请号：US16270071
申请日：2019-02-07
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Thomas Raymond Farrell , Markus Feigl
IPC: F01D5/30
Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.
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公开(公告)号：US11480061B2
公开(公告)日：2022-10-25
申请号：US17151799
申请日：2021-01-19
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Thomas Raymond Farrell , Markus Feigl
Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.
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公开(公告)号：US10738622B2
公开(公告)日：2020-08-11
申请号：US15232527
申请日：2016-08-09
Applicant: General Electric Company
Inventor： James Albert Tallman , Thomas Raymond Farrell
Abstract: A component configured for impingement cooling includes an inner wall defining a plurality of apertures extending therethrough. Each aperture of the plurality of apertures is configured to emit a cooling fluid therethrough. The component also includes an outer wall that includes an exterior surface, an opposite interior surface, and a thickness defined therebetween. The component further includes a plurality of recesses defined in the outer wall. Each recess of the plurality of recesses extends from a recess first end to an opposite recess second end. The second recess end is defined at the interior surface, and the recess first end is positioned within the outer wall at a depth less than the thickness. Each recess is aligned with a corresponding aperture of the plurality of apertures to receive the cooling fluid therefrom.
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Patent Agency Ranking
公开(公告)号：US20140260263A1
公开(公告)日：2014-09-18
申请号：US13845334
申请日：2013-03-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Thomas Raymond Farrell
IPC: F02C7/22
Abstract: One embodiment of the present invention is a turbine nozzle segment for a turbine section of a gas turbine. The turbine nozzle segment includes an inner platform, an outer platform and an airfoil that extends therebetween. The airfoil includes a forward portion and an aft portion that is disposed downstream from the forward portion. The turbine nozzle segment further includes a fuel injection insert that extends between the inner platform and the outer platform downstream from the aft portion of the airfoil. The fuel injection insert includes a fuel circuit that extends within the fuel injection insert, and a plurality of fuel injection ports disposed within the fuel injection insert. The plurality of fuel injection ports provide for fluid communication with the fuel circuit.
Abstract translation: 本发明的一个实施例是用于燃气轮机的涡轮部分的涡轮喷嘴段。 涡轮喷嘴段包括在其间延伸的内平台，外平台和翼型件。 翼型件包括设置在前部的下游的前部和后部。 涡轮喷嘴段还包括燃料喷射插入件，该燃料喷射插入件在翼型件的后部下游延伸在内平台和外平台之间。 燃料喷射插入件包括在燃料喷射插入件内延伸的燃料回路和设置在燃料喷射插入件内的多个燃料喷射口。 多个燃料喷射口提供与燃料回路的流体连通。
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公开(公告)号：US10907484B2
公开(公告)日：2021-02-02
申请号：US16270071
申请日：2019-02-07
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Thomas Raymond Farrell , Markus Feigl
Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.
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公开(公告)号：US20180045057A1
公开(公告)日：2018-02-15
申请号：US15232527
申请日：2016-08-09
Applicant: General Electric Company
Inventor： James Albert Tallman , Thomas Raymond Farrell
Abstract: A component configured for impingement cooling includes an inner wall defining a plurality of apertures extending therethrough. Each aperture of the plurality of apertures is configured to emit a cooling fluid therethrough. The component also includes an outer wall that includes an exterior surface, an opposite interior surface, and a thickness defined therebetween. The component further includes a plurality of recesses defined in the outer wall. Each recess of the plurality of recesses extends from a recess first end to an opposite recess second end. The second recess end is defined at the interior surface, and the recess first end is positioned within the outer wall at a depth less than the thickness. Each recess is aligned with a corresponding aperture of the plurality of apertures to receive the cooling fluid therefrom.
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公开(公告)号：US09458767B2
公开(公告)日：2016-10-04
申请号：US13845334
申请日：2013-03-18
Applicant: General Electric Company
Inventor： Thomas Raymond Farrell
Abstract: One embodiment of the present invention is a turbine nozzle segment for a turbine section of a gas turbine. The turbine nozzle segment includes an inner platform, an outer platform and an airfoil that extends therebetween. The airfoil includes a forward portion and an aft portion that is disposed downstream from the forward portion. The turbine nozzle segment further includes a fuel injection insert that extends between the inner platform and the outer platform downstream from the aft portion of the airfoil. The fuel injection insert includes a fuel circuit that extends within the fuel injection insert, and a plurality of fuel injection ports disposed within the fuel injection insert. The plurality of fuel injection ports provide for fluid communication with the fuel circuit.
Abstract translation: 本发明的一个实施例是用于燃气轮机的涡轮部分的涡轮喷嘴段。 涡轮喷嘴段包括在其间延伸的内平台，外平台和翼型件。 翼型件包括设置在前部的下游的前部和后部。 涡轮喷嘴段还包括燃料喷射插入件，该燃料喷射插入件在翼型件的后部下游延伸在内平台和外平台之间。 燃料喷射插入件包括在燃料喷射插入件内延伸的燃料回路和设置在燃料喷射插入件内的多个燃料喷射口。 多个燃料喷射口提供与燃料回路的流体连通。
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9.发明申请TRANSITION DUCT HAVING AIRFOIL AND HOT GAS PATH ASSEMBLY FOR TURBOMACHINE 审中-公开具有飞行器的过渡管和用于涡轮机的热气路径组件公开(公告)号：US20140127008A1
公开(公告)日：2014-05-08
申请号：US13671839
申请日：2012-11-08
Applicant: GENERAL ELECTRIC COMPANY
IPC: F02C7/00
Abstract: Transition ducts, hot gas path assemblies, and turbomachines are provided. A hot gas path assembly includes an outer support ring, an inner support ring, and a transition duct coupled to the outer support ring and the inner support ring. The transition duct includes a conduit defining a passage extending between an inlet and an outlet. The inlet and the outlet are generally aligned along a longitudinal axis. The transition duct further includes an airfoil disposed within the conduit and configured to alter a hot gas flow direction.
Abstract translation: 提供过渡管，热气路组件和涡轮机。 热气体路径组件包括外支撑环，内支撑环和耦合到外支撑环和内支撑环的过渡管。 过渡管道包括限定在入口和出口之间延伸的通道的导管。 入口和出口通常沿着纵向轴线对准。 过渡管道还包括设置在管道内的翼型件，并且构造成改变热气流动方向。
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