Patents by Inventor Robert Feldmann
Robert Feldmann has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11927111Abstract: 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 (?) with the heated surface.Type: GrantFiled: June 9, 2022Date of Patent: March 12, 2024Assignee: General Electric CompanyInventors: Jonathan Michael Rausch, Zachary Daniel Webster, Kevin Robert Feldmann, Andrew David Perry, Kirk Douglas Gallier, Daniel Endecott Osgood
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Patent number: 11898460Abstract: 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.Type: GrantFiled: June 9, 2022Date of Patent: February 13, 2024Assignee: General Electric CompanyInventors: Jonathan Michael Rausch, Zachary Daniel Webster, Kevin Robert Feldmann, Andrew David Perry, Kirk Douglas Gallier, Daniel Endecott Osgood
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Patent number: 11879356Abstract: 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.Type: GrantFiled: June 29, 2022Date of Patent: January 23, 2024Assignee: General Electric CompanyInventors: Daniel Endecott Osgood, Zachary Daniel Webster, Gregory Terrence Garay, Kevin Robert Feldmann
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Publication number: 20230399954Abstract: 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.Type: ApplicationFiled: June 9, 2022Publication date: December 14, 2023Inventors: Jonathan Michael Rausch, Zachary Daniel Webster, Kevin Robert Feldmann, Andrew David Perry, Kirk Douglas Gallier, Daniel Endecott Osgood
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Publication number: 20230399955Abstract: 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. One or more blades in the compressor or turbine sections has an internal cooling conduit with at least one of a bend or a terminal end. A plurality of cooling holes are provided in the blade, with each hole having an inlet fluidly coupled to the cooling conduit and an outlet opening onto an exterior of the blade.Type: ApplicationFiled: July 19, 2023Publication date: December 14, 2023Inventors: Jonathan Michael Rausch, Zachary Daniel Webster, Kevin Robert Feldmann, Andrew David Perry, Kirk Douglas Gallier, Daniel Endecott Osgood
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Publication number: 20230399953Abstract: 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 (?) with the heated surface.Type: ApplicationFiled: June 9, 2022Publication date: December 14, 2023Inventors: Jonathan Michael Rausch, Zachary Daniel Webster, Kevin Robert Feldmann, Andrew David Perry, Kirk Douglas Gallier, Daniel Endecott Osgood
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Patent number: 11788470Abstract: 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.Type: GrantFiled: March 1, 2021Date of Patent: October 17, 2023Assignee: General Electric CompanyInventors: Jeffrey Douglas Rambo, Brandon Wayne Miller, Kevin Robert Feldmann, Patrick Michael Marrinan, Robert Jon McQuiston
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Patent number: 11591965Abstract: 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.Type: GrantFiled: March 29, 2021Date of Patent: February 28, 2023Assignee: General Electric CompanyInventors: 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
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Publication number: 20220349310Abstract: 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.Type: ApplicationFiled: June 29, 2022Publication date: November 3, 2022Inventors: Daniel Endecott Osgood, Zachary Daniel Webster, Gregory Terrence Garay, Kevin Robert Feldmann
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Publication number: 20220307419Abstract: 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.Type: ApplicationFiled: March 29, 2021Publication date: September 29, 2022Inventors: 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
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Publication number: 20220275757Abstract: 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.Type: ApplicationFiled: March 1, 2021Publication date: September 1, 2022Inventors: Jeffrey Douglas Rambo, Brandon Wayne Miller, Kevin Robert Feldmann, Patrick Michael Marrinan, Robert Jon McQuiston
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Patent number: 11401818Abstract: 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.Type: GrantFiled: August 6, 2018Date of Patent: August 2, 2022Assignee: General Electric CompanyInventors: Daniel Endecott Osgood, Zachary Daniel Webster, Gregory Terrence Garay, Kevin Robert Feldmann
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Publication number: 20220170383Abstract: An engine component assembly with a first substrate having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, with the cooling surface being different than the hot surface, a second substrate having a first surface in fluid communication with a cooling fluid supply and a second surface, different from the first surface, facing and spaced from the cooling surface to define at least one interior cavity. At least one cavity is provided within the first substrate defining a cavity surface where at least a portion of the cavity surface is directly opposite the second surface. At least one cooling aperture extending through the second substrate from the first surface to the second surface, and defining a streamline along which a cooling fluid passes from the cooling fluid supply to the at least one interior cavity.Type: ApplicationFiled: February 16, 2022Publication date: June 2, 2022Inventors: Robert Frederick Bergholz, Jason Randolph Allen, Robert David Briggs, Kevin Robert Feldmann, Curtis Walton Stover, Zachary Daniel Webster, Fernando Reiter
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Patent number: 11313235Abstract: 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.Type: GrantFiled: March 17, 2015Date of Patent: April 26, 2022Inventors: Ronald Scott Bunker, Frederick Alan Buck, Robert David Briggs, Gulcharan Singh Brainch, Kevin Robert Feldmann
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Patent number: 11280215Abstract: 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 with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.Type: GrantFiled: October 28, 2015Date of Patent: March 22, 2022Assignee: General Electric CompanyInventors: Robert Frederick Bergholz, Jason Randolph Allen, Robert David Briggs, Kevin Robert Feldmann, Curtis Walton Stover, Zachary Daniel Webster, Fernando Reiter
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Patent number: 11187094Abstract: An assembly for a turbine engine comprising a plurality of circumferentially arranged segments having first and second confronting end faces. The first and second confronting end faces include a multi-channel spline seal assembly. The multi-channel spline seal assembly includes at least a first and second channel wherein confronting first or second channels can receive at least one spline seal.Type: GrantFiled: August 26, 2019Date of Patent: November 30, 2021Assignee: General Electric CompanyInventors: Kevin Robert Feldmann, Robert Proctor, David Scott Stapleton, Robert Charles Groves, II
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Patent number: 11021961Abstract: An aspect of the present disclosure is directed to a rotor assembly for a turbine engine. The rotor assembly includes an airfoil assembly and a hub to which the airfoil assembly is attached. A wall assembly defines a first cavity and a second cavity between the airfoil assembly and the hub. The first cavity and the second cavity are at least partially fluidly separated by the wall assembly. The first cavity is in fluid communication with a flow of first cooling fluid and the second cavity is in fluid communication with a flow of second cooling fluid different from the first cooling fluid.Type: GrantFiled: December 5, 2018Date of Patent: June 1, 2021Assignee: General Electric CompanyInventors: Jeffrey Douglas Rambo, Kirk Douglas Gallier, Brandon Wayne Miller, Craig Alan Gonyou, Kevin Robert Feldmann, Justin Paul Smith
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Publication number: 20210062666Abstract: An assembly for a turbine engine comprising a plurality of circumferentially arranged segments having first and second confronting end faces. The first and second confronting end faces include a multi-channel spline seal assembly. The multi-channel spline seal assembly includes at least a first and second channel wherein confronting first or second channels can receive at least one spline seal.Type: ApplicationFiled: August 26, 2019Publication date: March 4, 2021Inventors: Kevin Robert Feldmann, Robert Proctor, David Scott Stapleton, Robert Charles Groves, II
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Publication number: 20200182059Abstract: An aspect of the present disclosure is directed to a rotor assembly for a turbine engine. The rotor assembly includes an airfoil assembly and a hub to which the airfoil assembly is attached. A wall assembly defines a first cavity and a second cavity between the airfoil assembly and the hub. The first cavity and the second cavity are at least partially fluidly separated by the wall assembly. The first cavity is in fluid communication with a flow of first cooling fluid and the second cavity is in fluid communication with a flow of second cooling fluid different from the first cooling fluid.Type: ApplicationFiled: December 5, 2018Publication date: June 11, 2020Inventors: Jeffrey Douglas Rambo, Kirk Douglas Gallier, Brandon Wayne Miller, Craig Alan Gonyou, Kevin Robert Feldmann, Justin Paul Smith
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Patent number: 10563867Abstract: 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.Type: GrantFiled: September 30, 2015Date of Patent: February 18, 2020Assignee: General Electric CompanyInventors: Ronald Scott Bunker, Kevin Robert Feldmann, Douglas Ray Smith, Kirk D. Gallier, Daniel Scott Martyn, Rachel Anne Vukoja