公开(公告)号：US20220341339A1

公开(公告)日：2022-10-27

申请号：US17685523

申请日：2022-03-03

Applicant: General Electric Company

Inventor： David Alan Frey ,  Jeffrey Douglas Rambo ,  Alexander Martin Sener ,  Kirk Douglas Gallier

IPC: F01D9/04 ,  F01D25/24 ,  F02C7/28 ,  F01D5/18

Abstract: A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.

公开(公告)号：US20210285332A1

公开(公告)日：2021-09-16

申请号：US16817742

申请日：2020-03-13

Applicant: General Electric Company

Inventor： David Alan Frey ,  Jeffrey Douglas Rambo ,  Alexander Martin Sener ,  Kirk Douglas Gallier

IPC: F01D9/04 ,  F01D25/24 ,  F02C7/28 ,  F01D5/18

Abstract: A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.

公开(公告)号：US11085315B2

公开(公告)日：2021-08-10

申请号：US16505888

申请日：2019-07-09

Applicant: General Electric Company

Inventor： Kirk Douglas Gallier ,  David Alan Frey

IPC: F01D11/00 ,  F16J15/16

Abstract: An apparatus and method of sealing for an engine component between two surfaces arranged in spaced relationship to define a gap. A groove located is located in one of the two surface for receiving a seal having a body with a multi-faceted cross-sectional shape defining multiple seal facets. At least one of the multiple seal facets contacts one or both of the two surfaces.

公开(公告)号：US20210040861A1

公开(公告)日：2021-02-11

申请号：US17079577

申请日：2020-10-26

Applicant: General Electric Company

Inventor： Alexander Martin Sener ,  Brian David Keith ,  David Alan Frey ,  Jamil Darnell Grant

IPC: F01D11/00 ,  F01D17/16 ,  F01D9/04

Abstract: A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.

公开(公告)号：US20180328189A1

公开(公告)日：2018-11-15

申请号：US15592516

申请日：2017-05-11

Applicant: General Electric Company

Inventor： David Alan Frey ,  Kirk Douglas Gallier ,  Herbert Chidsey Roberts

IPC: F01D5/18 ,  F01D9/02 ,  F01D25/12 ,  F04D29/32 ,  F04D29/38 ,  F04D29/54 ,  F04D29/58 ,  B23P15/02

CPC classification number: F01D5/147 ,  B23P15/02 ,  F01D5/14 ,  F01D5/18 ,  F01D5/28 ,  F01D5/284 ,  F01D9/02 ,  F01D25/12 ,  F04D29/32 ,  F04D29/38 ,  F04D29/54 ,  F04D29/58 ,  F05D2260/204 ,  F05D2300/6033 ,  F05D2300/608

Abstract: CMC components having microchannels and methods for forming microchannels in CMC components are provided. For example, a method for forming microchannels in a CMC component comprises laying up a plurality of body plies for forming a body of the CMC component; laying up a microchannel ply on the plurality of body plies that has at least one void therein for forming at least one microchannel; laying up a cover ply on the microchannel ply to define an outer layer of the CMC component; and processing the laid up body plies, microchannel ply, and cover ply to form the CMC component. In another embodiment, the method comprises applying an additive matrix to the body plies to define at least one microchannel. In still other embodiments, the method comprises machining at least one microchannel in the plurality of body plies.

公开(公告)号：US20170122109A1

公开(公告)日：2017-05-04

申请号：US14926294

申请日：2015-10-29

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Kirk D. Gallier ,  David Alan Frey

IPC: F01D5/18 ,  F01D9/04 ,  F04D29/54 ,  F01D5/28 ,  F04D29/38 ,  F01D5/14 ,  F01D25/12

CPC classification number: F01D5/18 ,  F01D5/147 ,  F01D5/282 ,  F01D5/284 ,  F01D9/023 ,  F01D9/041 ,  F01D25/12 ,  F01D25/14 ,  F04D29/384 ,  F04D29/544 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2260/20 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: A component for a gas turbine engine includes a first surface and a second surface. The component additionally includes one or more layers of ceramic matrix composite material extending between the first and second surfaces. A thermal void extends between a first end and a second end. The second end of the thermal void is a terminal end embedded in the component between the first and second surfaces.

公开(公告)号：US11952900B2

公开(公告)日：2024-04-09

申请号：US17949601

申请日：2022-09-21

Applicant: General Electric Company

Inventor： Alexander Martin Sener ,  Brian David Keith ,  David Alan Frey ,  Jamil Darnell Grant

IPC: F01D11/00 ,  F01D9/04 ,  F01D17/16 ,  F02C3/04 ,  F02C9/22

CPC classification number: F01D11/005 ,  F01D9/042 ,  F01D11/003 ,  F01D17/162 ,  F02C3/04 ,  F02C9/22 ,  F05D2220/32 ,  F05D2220/3213 ,  F05D2240/35

Abstract: A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.

公开(公告)号：US20230304408A1

公开(公告)日：2023-09-28

申请号：US18093044

申请日：2023-01-04

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Kirk D. Gallier ,  David Alan Frey

IPC: F01D5/18 ,  F01D5/28 ,  F01D9/02 ,  F01D25/14 ,  F01D5/14 ,  F01D9/04 ,  F01D25/12 ,  F04D29/38 ,  F04D29/54

CPC classification number: F01D5/18 ,  F01D5/284 ,  F01D9/023 ,  F01D25/14 ,  F01D5/147 ,  F01D5/282 ,  F01D9/041 ,  F01D25/12 ,  F04D29/384 ,  F04D29/544 ,  Y02T50/60 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2260/20 ,  F05D2300/6033

Abstract: A component for a gas turbine engine includes a first surface and a second surface. The component additionally includes one or more layers of ceramic matrix composite material extending between the first and second surfaces. A thermal void extends between a first end and a second end. The second end of the thermal void is a terminal end embedded in the component between the first and second surfaces.

公开(公告)号：US20230014436A1

公开(公告)日：2023-01-19

申请号：US17949601

申请日：2022-09-21

Applicant: General Electric Company

Inventor： Alexander Martin Sener ,  Brian David Keith ,  David Alan Frey ,  Jamil Darnell Grant

IPC: F01D11/00 ,  F01D17/16 ,  F01D9/04 ,  F02C3/04 ,  F02C9/22

Abstract: A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.

公开(公告)号：US11441436B2

公开(公告)日：2022-09-13

申请号：US16994751

申请日：2020-08-17

Applicant: General Electric Company

Inventor： David Alan Frey ,  Kirk Douglas Gallier ,  Daniel Patrick Kerns ,  Brandon ALlanson Reynolds

IPC: F01D9/04 ,  F01D11/00 ,  F01D25/00 ,  F01D25/24 ,  C04B35/573 ,  C04B37/00 ,  C04B35/571 ,  C04B35/515 ,  C04B35/80

Abstract: Flow path assemblies and methods for forming such flow path assemblies for gas turbine engines are provided. For example, a flow path assembly for a gas turbine engine has a boundary structure, an airfoil, and a locking feature. The boundary structure and the airfoil are formed from a composite material. The boundary structure defines an opening and a cutout proximate the opening, and the airfoil is sized to fit within the opening of the boundary structure. The locking feature is received within the cutout defined by the boundary structure to interlock the airfoil with the boundary structure.