公开(公告)号：US11905881B2

公开(公告)日：2024-02-20

申请号：US17410491

申请日：2021-08-24

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Daniel Endecott Osgood ,  Jonathan Russell Ratzlaff ,  Kirk D. Gallier

IPC: F02C7/052 ,  F01D25/32 ,  F02C7/18 ,  F01D9/04 ,  B01D45/16 ,  F01D25/12

CPC classification number: F02C7/052 ,  B01D45/16 ,  F01D9/041 ,  F01D25/12 ,  F01D25/32 ,  F02C7/18 ,  F05D2260/607

Abstract: A component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet.

公开(公告)号：US10563867B2

公开(公告)日：2020-02-18

申请号：US14870829

申请日：2015-09-30

Applicant: General Electric Company

Inventor： Ronald Scott Bunker ,  Kevin Robert Feldmann ,  Douglas Ray Smith ,  Kirk D. Gallier ,  Daniel Scott Martyn ,  Rachel Anne Vukoja

IPC: F23R3/00 ,  F02C7/12 ,  F01D5/18 ,  F01D5/28

Abstract: An engine component for a gas turbine engine generating hot combustion gas flow is provided. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The engine component also includes a flow conditioning structure provided upstream of the outlet on the hot surface. The flow conditioning structure can include a ridge extending from the hot surface.

公开(公告)号：US10408073B2

公开(公告)日：2019-09-10

申请号：US15001572

申请日：2016-01-20

Applicant: General Electric Company

Inventor： Robert Charles Groves, II ,  Kirk D. Gallier

IPC: F01D9/06

Abstract: A stator component of a turbine engine having an airfoil defining a radial cooling channel, the airfoil having an airfoil outer surface and an airfoil inner surface. The airfoil outer surface defines a leading edge portion, a trailing edge portion, a pressure side wall, and a suction side wall. The airfoil inner surface defines a series of alternating peaks and valleys in the leading edge portion such that the airfoil has a varying cross-sectional thickness defined between the airfoil inner surface and the airfoil outer surface in the leading edge portion. A strut is disposed within the radial cooling channel and defines an inner radial cooling passage. The strut has an outer surface that defines a plurality of apertures that provide for fluid communication from the inner radial cooling passage to a radial cooling gap defined between the airfoil inner surface and the outer surface of the strut.

公开(公告)号：US20190071977A1

公开(公告)日：2019-03-07

申请号：US15697916

申请日：2017-09-07

Applicant: General Electric Company

Inventor： Zachary Daniel Webster ,  Aaron Ezekiel Smith ,  Gregory Terrence Garay ,  Kirk D. Gallier

IPC: F01D5/18 ,  F01D9/06

Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.

公开(公告)号：US20180370158A1

公开(公告)日：2018-12-27

申请号：US15632739

申请日：2017-06-26

Applicant: General Electric Company

Inventor： Kirk D. Gallier ,  Nathan Carl Sizemore

IPC: B29C70/30 ,  B29C70/54 ,  B29D99/00 ,  F01D5/18 ,  F01D5/28 ,  B32B5/02 ,  B32B18/00

Abstract: Ply layups and methods for forming composite components are provided. For example, a method for forming a composite component comprises laying up a plurality of composite plies to form a composite ply layup; partially processing the composite ply layup to form a green state layup; machining the green state layup; assembling the green state layup with one or more sub-assemblies; and processing the green state layup and the one or more sub-assemblies to form the composite component. In an exemplary embodiment, the composite component is a turbine nozzle airfoil. Another exemplary method comprises laying up a plurality of composite plies to form a composite ply layup; compacting the composite ply layup to form a green state layup; machining the green state layup; assembling the green state layup with one or more sub-assemblies; and processing the green state layup and the one or more sub-assemblies to form the composite component.

公开(公告)号：US20180230839A1

公开(公告)日：2018-08-16

申请号：US15432269

申请日：2017-02-14

Applicant: General Electric Company

Inventor： Kirk D. Gallier ,  Edward Charles Vickers

IPC: F01D11/02 ,  F02K3/06

CPC classification number: F01D11/02 ,  F01D11/003 ,  F01D11/005 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/11 ,  F05D2240/56 ,  Y02T50/672

Abstract: A shroud assembly for a turbine engine comprises a plurality of circumferentially arranged shroud segments, each terminating in circumferentially spaced first and second shiplap elements, where the first shiplap element of one shroud segment can overlap the second shiplap element of an adjacent shroud segment.

公开(公告)号：US20170204734A1

公开(公告)日：2017-07-20

申请号：US15001572

申请日：2016-01-20

Applicant: General Electric Company

Inventor： Robert Charles Groves, II ,  Kirk D. Gallier

IPC: F01D9/06

CPC classification number: F01D9/065 ,  F05D2250/182 ,  F05D2250/184 ,  F05D2250/294 ,  F05D2260/201 ,  F05D2260/22141 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/676

Abstract: A stator component of a turbine engine having an airfoil defining a radial cooling channel, the airfoil having an airfoil outer surface and an airfoil inner surface. The airfoil outer surface defines a leading edge portion, a trailing edge portion, a pressure side wall, and a suction side wall. The airfoil inner surface defines a series of alternating peaks and valleys in the leading edge portion such that the airfoil has a varying cross-sectional thickness defined between the airfoil inner surface and the airfoil outer surface in the leading edge portion. A strut is disposed within the radial cooling channel and defines an inner radial cooling passage. The strut has an outer surface that defines a plurality of apertures that provide for fluid communication from the inner radial cooling passage to a radial cooling gap defined between the airfoil inner surface and the outer surface of the strut.

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：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：US20220145764A1

公开(公告)日：2022-05-12

申请号：US17582305

申请日：2022-01-24

Applicant: General Electric Company

Inventor： Zachary Daniel Webster ,  Aaron Ezekiel Smith ,  Gregory Terrence Garay ,  Kirk D. Gallier

IPC: F01D5/18 ,  F01D9/06 ,  F01D9/02

Abstract: An apparatus and method relating to a cooling hole of a component of a turbine engine. The cooling hole can extend from an inlet to an outlet to define a connecting passage. The cooling hole can contain a diffusing section. The diffusing section can be defined by an interior surface having variable geometries.