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公开(公告)号：US20200157947A1
公开(公告)日：2020-05-21
申请号：US16195048
申请日：2018-11-19
Applicant: General Electric Company
Inventor： Daniel Endecott Osgood , Tingfan Pang , Gregory Terrence Garay , Zachary Daniel Webster , Ryan Christopher Jones
Abstract: A cast component having reduced cross flow linking cavities and method of casting may include a body. The body may define a plurality of internal flow channels. The plurality of internal flow channels may include a first internal flow channel and a second internal flow channel. The cast component may also include a plurality of linking cavities obstructing unintended fluid communication between the first internal flow channel and the second internal flow channel through the plurality of linking cavities.
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公开(公告)号：US20200040743A1
公开(公告)日：2020-02-06
申请号：US16055292
申请日：2018-08-06
Applicant: General Electric Company
Inventor： Daniel Endecott Osgood , Zachary Daniel Webster , Gregory Terrence Garay , Kevin Robert Feldmann
Abstract: A component for a gas turbine engine. The component includes a body. The body has an exterior surface abutting a flowpath for the flow of a hot combustion gas through the gas turbine engine. Further, the body defines a cooling passageway within the body to supply cool air to the component. The component includes a leading face and a trailing face defining a trench therebetween on the exterior surface. The body defines a plurality of cooling holes extending between the cooling passageway and a plurality of outlets defined in the trench such that the trench is fluidly coupled to the cooling passageway. Additionally, the leading face and trailing face are each tangent to at least one of the plurality of outlets. The trench directs the cool air along a contour of the component.
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公开(公告)号：US20190316473A1
公开(公告)日：2019-10-17
申请号：US16423313
申请日：2019-05-28
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Zachary Daniel Webster
Abstract: A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.
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公开(公告)号：US20190071976A1
公开(公告)日：2019-03-07
申请号：US15697886
申请日：2017-09-07
Applicant: General Electric Company
Inventor： Zachary Daniel Webster , Aaron Ezekiel Smith , Kirk D. Gallier
CPC classification number: F01D5/186 , F01D9/023 , F01D9/041 , F01D9/065 , F01D25/12 , F02K1/822 , F05D2220/323 , F05D2230/50 , F05D2240/11 , F05D2240/124 , F05D2240/306 , F05D2240/81 , F05D2250/73 , F05D2260/202 , F23R3/002 , F23R2900/03042
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.
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公开(公告)号：US20170298743A1
公开(公告)日：2017-10-19
申请号：US15098733
申请日：2016-04-14
Applicant: General Electric Company
Inventor： Zachary Daniel Webster , Kevin Robert Feldmann
CPC classification number: F01D5/186 , F01D9/023 , F01D9/041 , F01D9/065 , F01D25/08 , F02K1/822 , F05D2220/32 , F05D2240/11 , F05D2240/35 , F05D2240/81 , F05D2250/11 , F05D2250/14 , F05D2250/314 , F05D2250/322 , F05D2260/202 , F23R3/002 , F23R3/04 , F23R2900/03042 , Y02T50/672 , Y02T50/676
Abstract: An apparatus and method relating to a film-hole of a component of a turbine engine comprising including forming the hole in the component and applying a coating to the component such that the coating fills in portions of the film-hole.
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Patent Agency Ranking
公开(公告)号：US20240301798A1
公开(公告)日：2024-09-12
申请号：US18668840
申请日：2024-05-20
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Zachary Daniel Webster , Daniel Endecott Osgood , Kirk Douglas Gallier
CPC classification number: F01D5/187 , F01D5/087 , F05D2240/307 , F05D2260/20 , F05D2260/201 , F05D2260/232
Abstract: An apparatus and method for an engine component for a turbine engine. The engine component having an outer wall defining an interior and extending between a root and a tip to define a radial direction, a tip wall spanning the first side and second sides to close the interior at the tip. A tip rail extending from the tip wall and having an inner tip rail surface, an outer tip rail surface extending from at least one of the first or the second side, and radially terminating in an upper tip rail surface connecting the inner tip rail surface and the outer tip rail surface. A tip rim formed in at least one of the outer surface or the inner tip rail surface and spaced from the upper tip rail surface in the radial direction, and multiple cooling passages formed in the outer wall and fluidly coupling the at least one cooling conduit to the tip rim at corresponding passage outlets.
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公开(公告)号：US20240247590A1
公开(公告)日：2024-07-25
申请号：US18599486
申请日：2024-03-08
Applicant: General Electric Company
CPC classification number: F01D5/186 , F01D5/187 , F01D9/02 , F01D9/065 , F05D2230/10 , F05D2260/202
Abstract: A component for a turbine engine comprises a wall having a first wall surface and a second wall surface; and a cooling hole comprising a connecting passage extending between an inlet at the first wall surface and an outlet located at the second wall surface. The connecting passage includes: a metering section extending from the inlet toward the outlet and defining a centerline, and a diffusing section at the outlet defining first and second side walls, a first junction between the first side wall and the metering section and a second junction between the second side wall the metering section, the first side wall extending between the first junction and the outlet, and the second side wall extending between the second junction and the outlet. A metering section distance is measured between the centerline and a metering section wall of the metering section.
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公开(公告)号：US20240209738A1
公开(公告)日：2024-06-27
申请号：US18418909
申请日：2024-01-22
Applicant: General Electric Company
Inventor： Daniel Endecott Osgood , Zachary Daniel Webster , Gregory Terrence Garay , Kevin Robert Feldmann
CPC classification number: F01D5/186 , F01D1/12 , F01D5/147 , F01D5/284 , F01D11/12 , F01D11/122 , F01D11/14 , F05D2220/32 , F05D2230/31 , F05D2230/311 , F05D2240/303 , F05D2240/304 , F05D2260/201 , F05D2260/202 , F05D2300/514
Abstract: A component for a turbine engine includes a body with an exterior surface abutting a combustion flowpath for a combustion gas flow through the turbine engine, a cooling passage defined within the body, and a trench on the exterior surface. The trench includes a plurality of outlets, and a plurality of cooling holes extending from the cooling passage to the corresponding plurality of outlets.
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公开(公告)号：US11998974B2
公开(公告)日：2024-06-04
申请号：US17898751
申请日：2022-08-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Daniel Endecott Osgood , Zachary Daniel Webster , Craig Alan Gonyou , Daniel Lee Durstock , Kevin R. Feldmann , Kirk Douglas Gallier , William C. Herman , Nicholas Charles Gentilli
IPC: B22C9/10
CPC classification number: B22C9/10
Abstract: A casting core used in the manufacture of a cast engine component for a turbine engine, the cast engine component having a first area, a second area, a fluid passage wall separating the first area and the second area, and a connecting fluid passage extending through the fluid passage wall and interconnecting the first area and the second area. The connecting fluid passage having a turn with a radius (R). The casting core having a first core and a second core. The first core and the second core being defined by a set of geometric characteristics having a first minimum equivalent diameter (D1eqmin) of the first core and a second minimum equivalent diameter (D2eqmin) of the second core. A first flexible geometry factor (FGF1) being equal to:
(
D
1
eq
min
D
2
eq
min
)
(
R
D
2
eq
min
)
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公开(公告)号：US11927111B2
公开(公告)日：2024-03-12
申请号：US17836023
申请日：2022-06-09
Applicant: General Electric Company
Inventor： Jonathan Michael Rausch , Zachary Daniel Webster , Kevin Robert Feldmann , Andrew David Perry , Kirk Douglas Gallier , Daniel Endecott Osgood
CPC classification number: F01D5/186 , F01D25/12 , F05D2220/32 , F05D2240/30 , F05D2260/202
Abstract: A blade for a turbine engine with a wall separating a cooling fluid flow and a hot gas fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. A plurality of cooling holes each having a passage extending between an inlet at the cooled surface and an outlet at the heated surface. The outlet extending between an upstream end and a downstream end with respect to the hot gas fluid flow to define a distance, the passage defining a centerline forming a first angle (θ) with the heated surface.
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