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公开(公告)号：US11384646B2
公开(公告)日：2022-07-12
申请号：US16405014
申请日：2019-05-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jacob John Kittleson , James Murray
Abstract: A hollow CMC article, a mandrel for forming the article and a method for forming the article are disclosed. The article includes a ply-wrap layer defining a cavity. The ply-wrap layer includes a first face, a second face, a root portion bridging the faces, and a plurality of CMC wrap plies. The root portion defines a terminus of the ply-wrap layer including a cross-sectional conformation consisting of a curve having a single turning point. Each of the plurality of CMC wrap plies are disposed along the first face, wrap over the root portion, and extend along the second face. The hollow article further includes a plurality of CMC lateral plies disposed along the faces.
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公开(公告)号：US10563524B2
公开(公告)日：2020-02-18
申请号：US15622295
申请日：2017-06-14
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jacob John Kittleson , Peter De Diego
Abstract: A ceramic matrix composite (CMC) turbine blade includes a root region, a narrowed neck region extending from the root region, and a hub region extending from the narrowed neck region. At least one central CMC ply extending from the root region is interwoven with at least one insert extending toward the narrowed neck region from the hub region. A method of forming a CMC turbine blade includes interweaving at least one central CMC ply extending from the root region with at least one insert extending toward the narrowed neck region from the hub region. The CMC turbine blade includes a root region, a narrowed neck region extending from the root region, and a hub region extending from the narrowed neck region.
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公开(公告)号：US09719420B2
公开(公告)日：2017-08-01
申请号：US14292969
申请日：2014-06-02
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Paul Stephen DiMascio , Victor John Morgan , Jason Robert Parolini , Glenn Curtis Taxacher , Frederic Woodrow Roberts, Jr. , Jacob John Kittleson , John McConnell Delvaux
IPC: F02C7/00 , B23K1/00 , B23P6/00 , B24B33/00 , C04B41/00 , C04B41/45 , C04B41/50 , C04B41/53 , C04B41/85 , C04B41/91 , C04B41/87 , C04B41/88 , C04B41/51 , C23C16/24
CPC classification number: F02C7/00 , B23K1/0018 , B23P6/002 , B23P6/007 , B24B33/00 , C04B41/009 , C04B41/4531 , C04B41/5025 , C04B41/5096 , C04B41/5144 , C04B41/53 , C04B41/85 , C04B41/87 , C04B41/88 , C04B41/91 , C23C16/24 , F05D2230/30 , F05D2230/90 , F05D2300/6033 , Y10T156/10 , Y10T428/24355 , C04B35/00 , C04B35/80 , C04B41/4529 , C04B41/4539 , C04B41/5133 , C04B41/0072
Abstract: A process of producing a ceramic matrix composite gas turbine component and a ceramic matrix composite gas turbine component are provided. The process includes modifying a surface of the ceramic matrix composite gas turbine component to produce a modified surface with a surface roughness of less than 6 micrometers. The modifying is selected from the group of techniques consisting of applying unreinforced matrix plies to the surface, vapor depositing silicon on the surface, honing the surface, applying braze paste to the surface, and combinations thereof. The component includes a modified surface including a surface roughness of less than 6 micrometers. The modified surface being selected from the group consisting of unreinforced matrix plies applied to a surface of the ceramic matrix composite gas turbine component, silicon vapor deposited on the surface, a honed surface, a braze paste applied to the surface, and combinations thereof.
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公开(公告)号：US10605100B2
公开(公告)日：2020-03-31
申请号：US15604074
申请日：2017-05-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jacob John Kittleson , John McConnell Delvaux
Abstract: A ceramic matrix composite (CMC) turbine blade assembly includes a rotor, a CMC turbine blade, and at least one dovetail sleeve. The rotor has a blade slot with at least one slot surface. The slot surface is at a slot angle. The CMC turbine blade is received in the blade slot. The CMC turbine blade includes a dovetail root having at least one root surface. The root surface is at a root angle. The root angle is at least 5 degrees greater than the slot angle. The dovetail sleeve is received in the blade slot of the rotor. The dovetail sleeve has at least one inner surface contacting at least one root surface and at least one outer surface contacting at least one slot surface to radially retain the CMC turbine blade in the blade slot. A dovetail sleeve and a method of mounting a CMC turbine blade are also disclosed.
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公开(公告)号：US10584600B2
公开(公告)日：2020-03-10
申请号：US15622330
申请日：2017-06-14
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jacob John Kittleson
Abstract: A ceramic matrix composite (CMC) turbine blade includes an airfoil, a hub extending from the airfoil, and a shank extending from the hub. The airfoil includes a leading edge, a trailing edge, a pressure side, and a suction side. The shank includes a dovetail root having a dovetail path curved in a radial plane. In some embodiments, a leading shank length of the shank at the leading edge and a trailing shank length of the shank at the trailing edge are greater than an intermediate shank length at an intermediate location between the leading edge and the trailing edge. At least one of the airfoil, the hub, and the shank is formed from a CMC. A method of forming the CMC turbine blade includes forming the dovetail root to have a dovetail path curved in a radial plane.
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Patent Agency Ranking
公开(公告)号：US10329927B2
公开(公告)日：2019-06-25
申请号：US15237204
申请日：2016-08-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jacob John Kittleson , James Murray
Abstract: A hollow CMC article, a mandrel for forming the article and a method for forming the article are disclosed. The article includes a ply-wrap layer defining a cavity. The ply-wrap layer includes a first face, a second face, a root portion bridging the faces, and a plurality of CMC wrap plies. The root portion defines a terminus of the ply-wrap layer including a cross-sectional conformation consisting of a curve having a single turning point. Each of the plurality of CMC wrap plies are disposed along the first face, wrap over the root portion, and extend along the second face. The hollow article further includes a plurality of CMC lateral plies disposed along the faces.
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7.发明授权公开(公告)号：US10273813B2
公开(公告)日：2019-04-30
申请号：US14926803
申请日：2015-10-29
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jacob John Kittleson , James Joseph Murray, III
Abstract: A process of producing a ceramic matrix composite component. The process includes positioning core plies on a mandrel. At least partially rigidizing the core plies to form a preform ceramic matrix composite arrangement defining a tip cavity and a hollow region. Ceramic matrix composite tip plies are positioned on the preform ceramic matrix composite arrangement and within the tip cavity. The ceramic matrix composite tip plies are densified to form a tip region of the composite component.
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公开(公告)号：US20140123782A1
公开(公告)日：2014-05-08
申请号：US14146553
申请日：2014-01-02
Applicant: General Electric Company
Inventor： Jacob John Kittleson , Shankar Chandrasekaran , Munish Vishwas Inamdar
IPC: G01D11/30
CPC classification number: G01D11/30 , G01D11/245
Abstract: A method for assembling a sensor assembly includes providing a sensing device configured to measure at least one variable. The method also includes at least partially enclosing a magnetic material within an enclosure. At least a portion of the enclosure is manufactured from a material having a permeability that facilitates forming a magnetic field therein. The method also includes coupling the sensing device to a first portion of the enclosure. The enclosure includes at least one second portion that is movable with respect to the first portion of the enclosure such that a magnetic coupling force is induced external to the enclosure to facilitate coupling the sensor assembly to a magnetic surface.
Abstract translation: 一种用于组装传感器组件的方法包括提供被配置为测量至少一个变量的感测装置。 该方法还包括在外壳内至少部分地包围磁性材料。 外壳的至少一部分由具有促进其中形成磁场的渗透性的材料制成。 该方法还包括将感测装置耦合到外壳的第一部分。 所述外壳包括至少一个第二部分，所述至少一个第二部分可相对于所述外壳的所述第一部分移动，使得在所述外壳外部引入磁耦合力以便于将所述传感器组件耦合到磁性表面。
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9.发明授权公开(公告)号：US11359502B2
公开(公告)日：2022-06-14
申请号：US16793269
申请日：2020-02-18
Applicant: General Electric Company
Inventor： Jacob John Kittleson
Abstract: A nozzle for a turbine system includes an airfoil, an inner sidewall, and an outer sidewall. Each of the inner sidewall and outer sidewall each includes a peripheral edge defining a pressure side slash face, a suction side slash face, a leading edge face, and a trailing edge face. At least one of the inner sidewall pressure side slash face, the inner sidewall suction side slash face, the outer sidewall pressure side slash face, or the outer sidewall suction side slash face includes a first swept surface extending at a first angle relative to a nominal slash face angle and a second swept surface extending at a second angle relative to the nominal slash face angle. The first and second swept surfaces meet at a joining line that is circumferentially aligned with a stiffening member extending circumferentially on a respective sidewall.
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公开(公告)号：US11236622B2
公开(公告)日：2022-02-01
申请号：US16812506
申请日：2020-03-09
Applicant: General Electric Company
Inventor： Alexander Stein , Jacob John Kittleson , Daniel Robert Burnos
IPC: F01D9/02
Abstract: A turbine nozzle for a gas turbine includes: an airfoil having an airfoil shape having a nominal profile substantially in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in TABLE I. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying the values by a height of the airfoil expressed in units of distance. The X and Y values are connected by smooth continuing arcs that define airfoil profile sections at each distance Z along at least a portion of the airfoil, and the airfoil profile sections at the Z distances are joined smoothly with one another to form the nominal profile. A trailing edge profile for a turbine nozzle is also disclosed.
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