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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：US10386069B2
公开(公告)日：2019-08-20
申请号：US14407076
申请日：2013-06-13
Applicant: General Electric Company
Inventor： Shawn Michael Pearson , Robert Frederick Bergholz , Douglas Ray Smith , Frederick Alan Buck , Stephen Mark Molter , Kevin Robert Feldmann
Abstract: A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge laterally from an outlet end of the inclined inlet bore. The pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape.
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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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公开(公告)号：US09581085B2
公开(公告)日：2017-02-28
申请号：US13836426
申请日：2013-03-15
Applicant: General Electric Company
Inventor： Robert Joseph Bartz , Joseph Steven Bubnick , Scott Matthew Bush , Kevin Robert Feldmann , Robert Alan Frederick , Craig William Higgins
Abstract: Embodiments of hot streak alignment for gas turbine durability include structures and methods to align hot streaks with the leading edges of aligned first stage nozzle vanes in order to improve mixing of the hot streaks with cooling air at a stator nozzle of a first stage turbine and reduce usage of cooling air at first stage non-aligned stator nozzle vanes disposed adjacent to the aligned stator vanes.
Abstract translation: 用于燃气轮机耐久性的热条纹对准的实施例包括将热条纹与对准的第一级喷嘴叶片的前缘对准的结构和方法，以便改善热条纹与第一级涡轮机的定子喷嘴处的冷却空气的混合，并且减少 在与定位的定子叶片相邻设置的第一级不对准的定子喷嘴叶片上使用冷却空气。
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公开(公告)号：US11879356B2
公开(公告)日：2024-01-23
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
CPC classification number: F01D5/186 , F01D1/12 , F01D5/147 , F01D5/284 , 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 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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Patent Agency Ranking
公开(公告)号：US20230399953A1
公开(公告)日：2023-12-14
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：US20220307419A1
公开(公告)日：2022-09-29
申请号：US17215130
申请日：2021-03-29
Applicant: General Electric Company
Inventor： Christopher Edward Wolfe , Hendrik Pieter Jacobus de Bock , William Dwight Gerstler , Brian Gene Brzek , Brandon Wayne Miller , Daniel Alan Niergarth , Kevin Robert Feldmann , Kevin Edward Hinderliter
Abstract: A thermal management system for transferring heat between fluids includes a thermal transport bus through which a heat exchange fluid flows. Additionally, the system includes a heat source heat exchanger arranged along the bus such that heat is added to the fluid flowing through the heat source heat exchanger. Moreover, the system includes a plurality of heat sink heat exchangers arranged along the bus such that heat is removed from the fluid flowing through the plurality of heat sink heat exchangers. Furthermore, the system includes a bypass conduit fluidly coupled to the bus such that the bypass conduit allows the fluid to bypass one of the heat source heat exchanger or one of the heat sink heat exchangers. In addition, the system includes a valve configured to control a flow of the fluid through the bypass conduit based on a pressure of the fluid within the bus.
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公开(公告)号：US20220275757A1
公开(公告)日：2022-09-01
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
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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公开(公告)号：US11313235B2
公开(公告)日：2022-04-26
申请号：US14659640
申请日：2015-03-17
Applicant: General Electric Company
Inventor： Ronald Scott Bunker , Frederick Alan Buck , Robert David Briggs , Gulcharan Singh Brainch , Kevin Robert Feldmann
Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a metering section defining a metering diameter and a diffusing section that defines a hooded length.
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公开(公告)号：US10472972B2
公开(公告)日：2019-11-12
申请号：US14955261
申请日：2015-12-01
Applicant: General Electric Company
Abstract: Engine components are provided for a gas turbine engines that generate a hot combustion gas flow. 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 generally 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 can also include a coating on at least a portion of the hot surface and on at least a portion of an inner surface defined within the passage.
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