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11.发明申请SENSOR SIMULATOR AND SYSTEM FOR TESTING ROTATABLE SENSOR SIGNAL TRANSMITTERS 审中-公开用于测试可变传感器信号发射器的传感器模拟器和系统公开(公告)号：US20160209237A1
公开(公告)日：2016-07-21
申请号：US14599590
申请日：2015-01-19
Applicant: General Electric Company
Inventor： Kurt Kramer Schleif , Donald W. Shaw , Zachary John Snider , Mario Joseph Arceneaux
IPC: G01D3/02
CPC classification number: G01D3/02 , G01R31/2829 , H01R24/86 , H01R39/08 , H01R2201/20
Abstract: A sensor simulator and a system for testing rotatable sensor signal transmitters using the sensor simulator is disclosed herein. The sensor simulator includes a first and a second pin. The first pin includes a first end portion and a second end portion where the first end portion is configured to electronically couple to a positive terminal of a sensor circuit of the sensor signal transmitter. The second pin includes a first end portion and a second end portion where the first end portion is configured to electronically couple to a negative terminal of the same sensor circuit. The sensor simulator further includes an electronic component having a first wire lead electronically coupled to the second end portion of the first pin and a second wire lead electronically coupled the second end portion of the second pin.
Abstract translation: 本文公开了传感器模拟器和用于使用传感器模拟器测试可旋转传感器信号发射器的系统。 传感器模拟器包括第一和第二引脚。 第一引脚包括第一端部部分和第二端部部分，其中第一端部部分被配置为电连接到传感器信号发射器的传感器电路的正极端子。 第二引脚包括第一端部和第二端部，其中第一端部被配置为电连接到同一传感器电路的负极端子。 传感器模拟器还包括电子部件，其具有电子耦合到第一引脚的第二端部的第一引线引线和与第二引脚的第二端部电子耦合的第二引线。
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12.发明申请公开(公告)号：US20160061638A1
公开(公告)日：2016-03-03
申请号：US14474884
申请日：2014-09-02
Applicant: General Electric Company
Inventor： Kurt Kramer Schleif , Zachary John Snider
CPC classification number: G01D11/30 , F01D21/003 , G01D11/245 , G01M15/14 , G01N1/2247 , G01N33/0009 , G01N2001/2285 , G01N2201/021 , G01N2201/0227
Abstract: A fitting for positioning a probe in a hot gas path within a casing of a gas turbine engine is disclosed herein. The fitting may include a main body attachable to the casing opposite the hot gas path. The main body may include an internal bore and one or more cooling holes in communication with the internal bore. A compliant seal may be positionable within the internal bore. In addition, a follower may be positionable within the internal bore adjacent to the compliant seal. Moreover, the fitting may include a fastener configured to mate with the main body. In this manner, the follower may deform the compliant seal about the probe within the main body to secure and seal the probe within the main body.
Abstract translation: 本文公开了一种用于将探头定位在燃气涡轮发动机的壳体内的热气路径中的配件。 配件可以包括可附接到与热气体路径相对的壳体的主体。 主体可以包括内孔和与内孔连通的一个或多个冷却孔。 柔性密封件可以定位在内孔内。 此外，从动件可以位于邻近柔性密封件的内部孔内。 此外，配件可以包括被配置成与主体配合的紧固件。 以这种方式，随动件可以使主体内的探针周围的柔顺密封变形，以将探针固定并密封在主体内。
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公开(公告)号：US20240026795A1
公开(公告)日：2024-01-25
申请号：US17868911
申请日：2022-07-20
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John M. Matthews , Zachary John Snider
CPC classification number: F01D5/188 , F01D9/041 , F01D9/044 , F05D2230/237 , F05D2240/81 , F05D2260/201 , F05D2260/2214
Abstract: A stator vane includes a platform that defines an opening. The stator vane further includes an airfoil that has a leading edge, a trailing edge, a suction side wall, and a pressure side wall. The airfoil extends radially between a base and a tip. At least one of the base or the tip includes a protrusion. The protrusion extends into the opening of the platform such that the platform surrounds the protrusion of the airfoil. The stator vane further includes a braze joint disposed between and fixedly coupling the platform and the protrusion of the airfoil. The stator vane further includes a cooling circuit defined in at least one of the protrusion or the platform to cool the braze joint.
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14.发明授权公开(公告)号：US11572791B1
公开(公告)日：2023-02-07
申请号：US17574084
申请日：2022-01-12
Applicant: General Electric Company
Inventor： Zachary John Snider , John McConnell Delvaux
Abstract: A vibration damping system for a turbine nozzle or blade includes a vibration damping element including a plurality of contacting members including a plurality of damper pins. Each damper pin includes a body. A wire mesh member surrounds the body of at least one of the plurality of damper pins. The wire mesh member has a first outer dimension sized for frictionally engaging within a body opening in the turbine nozzle or blade to damp vibration. Spacer members devoid of a wire mesh member may also be used. The damper pins can have different sizes to accommodate contiguous body openings of different sizes in the nozzle or blade. The body opening can be angled relative to a radial extent of the nozzle or blade.
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公开(公告)号：US11519281B2
公开(公告)日：2022-12-06
申请号：US17118792
申请日：2020-12-11
Applicant: General Electric Company
Inventor： Sandip Dutta , Benjamin Paul Lacy , Gary Michael Itzel , Zachary John Snider
Abstract: The present disclosure is directed to a turbomachine that includes a hot gas path component having an inner surface and defining a hot gas path component cavity. An impingement insert is positioned within the hot gas path component cavity. The impingement insert includes an inner surface and an outer surface and defines an impingement insert cavity and a plurality of impingement apertures fluidly coupling the impingement insert cavity and the hot gas path component cavity. A plurality of pins extends from the outer surface of the impingement insert to the inner surface of the hot gas path component.
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Patent Agency Ranking
16.发明授权公开(公告)号：US11492908B2
公开(公告)日：2022-11-08
申请号：US16749178
申请日：2020-01-22
Applicant: General Electric Company
Inventor： Zachary John Snider
Abstract: A turbine rotor blade root is additively manufactured and includes a shank having a radially extending chamber defined therein. A blade mount is at a radial inner end of the shank. The blade mount has a hollow interior defined therein with the hollow interior in fluid communication with the radially extending chamber. A lattice support structure is disposed within the hollow interior of the blade mount.
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公开(公告)号：US11466581B1
公开(公告)日：2022-10-11
申请号：US17323354
申请日：2021-05-18
Applicant: General Electric Company
Inventor： Zachary John Snider , Adam John Fredmonski , Matthew Troy Hafner
Abstract: A turbine nozzle assembly system includes a plurality of nozzle sets, where each nozzle set forms an annulus. The nozzles in each set include an inner endwall and an outer endwall that include joint openings to receive the respective endwall mount ends of an airfoil. The airfoils across the plurality of nozzle sets have an inner endwall mount end and an outer endwall mount end that are identical amongst the plurality of nozzle sets. A wing portion of the airfoil has a selected wing shape that is identical within the respective nozzle set but different amongst the plurality of nozzle sets. In this manner, the endwalls can be removed from an airfoil and replaced with an airfoil having a different wing shape that provides a different pairwise throat area. The system allows changing of a pairwise throat area for a nozzle set without replacing the entirety of each nozzle.
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公开(公告)号：US11434767B2
公开(公告)日：2022-09-06
申请号：US16663941
申请日：2019-10-25
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Lyndsay Marie Kibler , Brad Wilson VanTassel , Benjamin Paul Lacy , Zachary John Snider , Christopher Donald Porter , Srikanth Chandrudu Kottilingam
Abstract: An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: at least one coolant feed channel fluidly coupled to a supply of cooling fluid; and an interconnected circuit of cooling channels, including: an interconnected circuit of cooling channels embedded within an exterior wall of the component; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling a supply of cooling fluid to the interconnected circuit of cooling channels; wherein the cooling fluid flows through the plurality of feed tubes into the interconnected circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels.
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公开(公告)号：US11242760B2
公开(公告)日：2022-02-08
申请号：US16749143
申请日：2020-01-22
Applicant: General Electric Company
Inventor： Zachary John Snider , Brad Wilson VanTassel , Jeffrey Clarence Jones
IPC: F01D5/18
Abstract: A turbine rotor blade is additively manufactured and includes an airfoil body with a radially extending chamber for receiving a coolant flow, a tip end at a radial outer end of the airfoil body, and a shank at a radial inner end of the airfoil body. The radially extending chamber extends at least partially into the shank to define a shank inner surface. An integral impingement cooling structure is within the radially extending chamber. The integral impingement cooling structure allows an exterior surface of a hollow body thereof to be uniformly spaced from the airfoil inner surface despite the curvature of the chamber. The turbine rotor blade has impingement cooling throughout the blade.
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公开(公告)号：US11192207B2
公开(公告)日：2021-12-07
申请号：US16172091
申请日：2018-10-26
Applicant: General Electric Company
Inventor： Jeffrey Clarence Jones , Zachary John Snider
IPC: B23K26/342 , B33Y10/00 , B33Y80/00 , B33Y30/00 , B23K26/082
Abstract: A passage incorporated into an additively manufactured object, the object and a related method are disclosed. The object has an additive manufacture build direction. The passage includes: a first portion aligned along an axis oriented less than approximately 45° from the build direction; and a second portion aligned along an axis oriented greater than approximately 45° from the build direction, the second portion including at least one self-supporting top surface portion including at least one edge aligned no greater than approximately 45° from the build direction. The passage having varying cross-sectional shape along a non-linear length accommodates additive manufacture regardless of build direction.
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