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公开(公告)号：US20210348514A1
公开(公告)日：2021-11-11
申请号：US16868165
申请日：2020-05-06
Applicant: General Electric Company
Inventor： Zachary John Snider , Matthew Troy Hafner , Jeffrey Clarence Jones
Abstract: Aspects of the embodiments set forth a sacrificial plug system including a component having a surface and at least one cooling hole in the surface; a sacrificial plug integrally formed with the component and integrally formed in the at least one cooling hole, where the sacrificial plug includes a top portion; a cover portion; and a bottom portion, the bottom portion integrally formed, engaged to, and connected to at least one cooling hole. The sacrificial plug system also includes at least one connective member integrally formed with the bottom portion of the sacrificial plug and integral with an inner wall of each respective at least one cooling hole; each at least one connective member being severable from the respective inner wall when a force is applied to the top portion, thus permitting the sacrificial plug to be removed from the at least one respective cooling hole.
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公开(公告)号：US10815786B2
公开(公告)日：2020-10-27
申请号：US16235079
申请日：2018-12-28
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , James Zhang , Jeffrey Clarence Jones , Peter de Diego
Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil is defined between a pressure face and a laterally opposed suction face, the pressure face and the suction face extending axially between opposite leading and trailing edges and radially between an outboard tip and a connection with a root of the rotor blade. The airfoil may include non-integral portions in which: a base portion of the airfoil is made from a first material; and a top portion of the airfoil is made from a second material. The airfoil may include a dovetail joint connecting the top portion to the base portion. The dovetail joint may include a dovetail extending from the top portion being received within a complementary dovetail groove formed in the base portion.
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公开(公告)号：US10794197B2
公开(公告)日：2020-10-06
申请号：US15623842
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Joshua Lee Margolies , Victor John Morgan , Matthew Troy Hafner
Abstract: A method for forming a coated turbine component and a coated turbine component is provided. The method includes a step of providing a component having a substrate including a trailing edge face. The method further includes a step of applying a thermal barrier coating or environmental barrier coating selectively to the substrate to form a discontinuous transition from a hot gas path surface at the trailing edge face to discourage hot gas flow along the trailing edge face.
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公开(公告)号：US20200208528A1
公开(公告)日：2020-07-02
申请号：US16235114
申请日：2018-12-28
Applicant: General Electric Company
Inventor： John McConnell Delvaux , Markus Feigl , Matthew Troy Hafner , Michael Anthony Wondrasek , James Zhang , Peter de Diego
Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral base and top portions. The airfoil may include a pin connector connecting the top portion to the base portion. The pin connector may include: a tab extending from the top portion; a complimentary slot for receiving the tab formed in the base portion; an elongated pin cavity formed through an interior region of the airfoil, where the pin cavity intersects the slot to divide the pin cavity into first and second pin cavity segments; a tab aperture formed through the tab, where the tab aperture is positioned so align with the pin cavity upon the tab being received within the slot; and a locking pin that extends continuously through the first segment of the pin cavity, the tab aperture, and the second segment of the pin cavity.
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公开(公告)号：US20200208527A1
公开(公告)日：2020-07-02
申请号：US16235095
申请日：2018-12-28
Applicant: General Electric Company
Inventor： Stanley Kevin Widener , John McConnell Delvaux , Matthew Troy Hafner , James Zhang , Peter de Diego
Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral portions in which: a base portion is made from a first material; and a top portion is made from a second material. The airfoil may include a connector securing the base portion to the top portion of the airfoil, wherein the connector comprises a wire-lock connector that includes: a tab extending from one of the base portion and the top portion; a complimentary slot for receiving the tab formed in the other one of the base portion and the top portion; a first groove formed in a side of the tab; a second groove formed in a side of the slot; a retaining aperture formed cooperatively via an alignment of the first and second grooves upon the tab being received into the slot; and a retaining wire housed within the retaining aperture.
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Patent Agency Ranking
公开(公告)号：US20200208526A1
公开(公告)日：2020-07-02
申请号：US16235079
申请日：2018-12-28
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , James Zhang , Jeffrey Clarence Jones , Peter de Diego
IPC: F01D5/14
Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil is defined between a pressure face and a laterally opposed suction face, the pressure face and the suction face extending axially between opposite leading and trailing edges and radially between an outboard tip and a connection with a root of the rotor blade. The airfoil may include non-integral portions in which: a base portion of the airfoil is made from a first material; and a top portion of the airfoil is made from a second material. The airfoil may include a dovetail joint connecting the top portion to the base portion. The dovetail joint may include a dovetail extending from the top portion being received within a complementary dovetail groove formed in the base portion.
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公开(公告)号：US10697326B2
公开(公告)日：2020-06-30
申请号：US15624142
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Glenn Curtis Taxacher , John McConnell Delvaux , Matthew Troy Hafner
Abstract: A turbine component assembly is disclosed, including a first component, a second component, and a cantilever spring. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The cantilever spring is attached directly to the second component as a compliant contact interface between the first component and the second component. The cantilever spring provides a radial spring compliance between the first component and the second component. During operation, the cantilever spring directly contacts and supports the first component.
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公开(公告)号：US10605459B2
公开(公告)日：2020-03-31
申请号：US15464419
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Stanley Kevin Widener , Michael John Hughes , Matthew Troy Hafner , Joseph Vincent Citeno
Abstract: The present disclosure is directed to an integrated combustor nozzle for a segmented annular combustion system. The integrated combustor nozzle includes an outer liner segment, an inner liner segment, and a fuel injection panel extending radially between the outer liner segment and the inner liner segment. The fuel injection panel includes a first side wall, a second side wall, and a plurality of premixing channels between the first and second side walls, each of the premixing channels having an outlet on one of the first and second side walls. The aft end of the fuel injection panel defines a turbine nozzle.
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公开(公告)号：US10526921B2
公开(公告)日：2020-01-07
申请号：US15623938
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Glenn Curtis Taxacher , John McConnell Delvaux , Matthew Troy Hafner
Abstract: An anti-rotation shroud dampening pin is disclosed including a shaft, an anti-rotation dampening tip at a first end of the shaft, and a cap at a second end of the shaft. The anti-rotation dampening tip includes a pin non-circular cross-section. A turbine shroud assembly is disclosed, including an inner shroud, an outer shroud, the anti-rotation shroud dampening pin, and a biasing apparatus. The inner shroud includes an anti-rotation depression having a depression non-circular cross-section. The outer shroud includes a channel extending from an aperture adjacent to the inner shroud. The anti-rotation shroud dampening pin is disposed within the channel and in contact with the inner shroud, and extends through the aperture into the anti-rotation depression. The biasing apparatus contacts the cap and provides a biasing force to the inner shroud through the anti-rotation dampening tip. The pin non-circular cross-section mates non-rotatably into the depression non-circular cross-section.
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公开(公告)号：USD871468S1
公开(公告)日：2019-12-31
申请号：US29598691
申请日：2017-03-28
Applicant: General Electric Company
Designer： John McConnell Delvaux , Matthew Troy Hafner , Glenn Curtis Taxacher
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