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公开(公告)号：US20170107837A1
公开(公告)日：2017-04-20
申请号：US14887537
申请日：2015-10-20
Applicant: General Electric Company
Inventor： Benjamin Scott Huizenga , Kevin Robert Feldmann , Robert Alan Frederick , Robert Charles Groves, II , Kirk Douglas Gallier , Timothy Francis Andrews , Darrell Senile
CPC classification number: F01D11/005 , F01D5/284 , F01D9/023 , F01D9/041 , F01D9/047 , F01D25/12 , F05D2220/32 , F05D2240/57 , F05D2250/71 , F05D2300/6033 , F16J15/061 , F16J15/0887 , Y02T50/672
Abstract: A gas turbine engine arcuate leaf seal assembly includes arcuate leaf seal extending radially and circumferentially between adjacent first and second turbine components. Upper and lower leaf seal portions of leaf seal are in radially spaced apart arcuate upper and lower grooves in the first and second turbine components respectfully. The seal includes an arcuate body and a circumferential retention tab extending radially away from body and disposed in a notch in a wall of grooves. Seal may have a thickness between 3 mils and 35 mils and/or torsional stiffness between 0.015 and 0.15 lb/in. Turbine components may be radially adjacent turbine nozzle upper and lower components. The upper or lower component may be made of a ceramic matrix composite material. Annular cooling air plenum including flow cavities in inner support ring segments may be in lower component and in flow communication with hollow fairing airfoils.
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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：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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公开(公告)号：US20230399954A1
公开(公告)日：2023-12-14
申请号：US17836049
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
IPC: F01D5/18
CPC classification number: F01D5/187 , F05D2260/202 , F05D2240/30
Abstract: A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A temperature sensor is provided within the engine and configured to detect a gas temperature within the engine core. A set of blades is circumferentially arranged in the turbine section. A blade in the set of blades includes an outer wall bounding an interior, a cooling conduit within the interior, and a plurality of film holes fluidly coupled to the cooling conduit.
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公开(公告)号：US11788470B2
公开(公告)日：2023-10-17
申请号：US17188668
申请日：2021-03-01
Applicant: General Electric Company
Inventor： Jeffrey Douglas Rambo , Brandon Wayne Miller , Kevin Robert Feldmann , Patrick Michael Marrinan , Robert Jon McQuiston
CPC classification number: F02C7/185 , F01D25/12 , F02C7/14 , F05D2220/323 , F05D2260/20 , F05D2270/112 , F05D2270/301 , F05D2270/3032
Abstract: A method is provided of controlling a cooled cooling air system for an aeronautical gas turbine engine. The method includes: receiving data indicative of an ambient condition of the aeronautical gas turbine engine, data indicative of a deterioration parameter of the aeronautical gas turbine engine, data indicative of an operating condition of the aeronautical gas turbine engine, or a combination thereof; and modifying a cooling capacity of the cooled cooling air system in response to the received data indicative of the ambient condition of the aeronautical gas turbine engine, data indicative of the deterioration parameter of the aeronautical gas turbine engine, data indicative of an operating condition of the aeronautical gas turbine engine, or the combination thereof.
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Patent Agency Ranking
公开(公告)号：US20220349310A1
公开(公告)日：2022-11-03
申请号：US17852875
申请日：2022-06-29
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：US20190257205A1
公开(公告)日：2019-08-22
申请号：US15898716
申请日：2018-02-19
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Zachary Daniel Webster , Gregory Terrence Garay , Kevin Robert Feldmann , Steven Robert Brassfield
Abstract: An apparatus and method an engine component for a turbine engine comprising an outer wall bounding an interior and defining a pressure side and an opposing suction side, with both sides extending between a leading edge and a trailing edge to define a chord-wise direction, and extending between a root and a tip to define a span-wise direction, at least one cooling passage located within the interior, at least one cooling hole having an inlet fluidly coupled to the cooling passage and an outlet located along the outer wall.
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公开(公告)号：US20170191417A1
公开(公告)日：2017-07-06
申请号：US14989290
申请日：2016-01-06
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Robert Frederick Bergholz , Jason Randolph Allen , Robert David Briggs , Byron Andrew Pritchard, JR. , Kevin Robert Feldmann , Curtis Walton Stover , Zachary Daniel Webster , Fernando Reiter , Michael Alan Meade
CPC classification number: F01D5/187 , F01D9/065 , F01D25/12 , F05D2240/11 , F05D2250/21 , F05D2250/22 , F05D2250/23 , F05D2250/232 , F05D2250/241 , F05D2250/27 , F05D2260/201 , F05D2260/2214 , F23R3/005 , F23R2900/03044 , F23R2900/03045 , Y02T50/672 , Y02T50/676
Abstract: An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, and a second engine component having a first surface in fluid communication with a cooling fluid flow and a second surface spaced from the cooling surface to define a space. A cooling aperture extends through the second engine component. A cooling feature extends from the cooling surface of the first engine component, and is oriented relative to the cooling aperture such that the cooling fluid flow is orthogonal and non-orthogonal to different portions of the cooling feature.
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公开(公告)号：US20170089579A1
公开(公告)日：2017-03-30
申请号：US14870866
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
CPC classification number: F23R3/007 , F01D5/186 , F01D5/284 , F02C7/12 , F05D2250/611 , F05D2250/711 , F05D2250/712 , F05D2260/202 , F05D2300/6033 , F23R3/002 , F23R2900/03042 , Y02T50/672 , Y02T50/676
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 hot combustion gas flow defines an upstream direction and a downstream direction relative to the hot surface. The substrate also 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 passage comprises a metering section; and a diffusing section, with the diffusing section including a shelf, a first outer lobe and a second outer lobe.
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公开(公告)号：US20170089578A1
公开(公告)日：2017-03-30
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
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.
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