Patents by Inventor Winton Davies
Winton Davies 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: 12253006Abstract: A composite blade assembly for a turbine engine. The composite blade assembly having a core, a first skin and a second skin. The core having a composite structure. The first skin having at least one composite ply. The second skin having at least one composite ply. The first skin having a first radius. The second skin having a second radius.Type: GrantFiled: December 27, 2022Date of Patent: March 18, 2025Assignee: General Electric CompanyInventors: Nicholas Joseph Kray, Elzbieta Kryj-Kos, Tod Winton Davis, Gary Willard Bryant, Jr.
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Publication number: 20240417063Abstract: A composite airfoil assembly for a gas turbine engine. The composite airfoil assembly includes a composite airfoil defined by a core and a skin. The composite airfoil assembly further includes cladding. The core defines a core exterior, where the skin is applied to at least a portion of the core exterior. The cladding is prepared before being coupled or adhered to the composite airfoil.Type: ApplicationFiled: June 13, 2023Publication date: December 19, 2024Inventors: Elzbieta Kryj-Kos, Nicholas Joseph Kray, Tod Winton Davis, Gary Willard Bryant, JR.
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Publication number: 20240401486Abstract: A composite airfoil assembly for a gas turbine engine, the composite airfoil assembly comprising a composite airfoil, a first cladding, and a second cladding. The composite airfoil having a core comprising a composite structure having a core bulk modulus and a laminate skin applied to at least a portion of an exterior of the core. The first cladding and the second cladding are coupled to an outer surface of the composite airfoil.Type: ApplicationFiled: June 5, 2023Publication date: December 5, 2024Inventors: Nicholas Joseph Kray, Tod Winton Davis, Elzbieta Kryj-Kos, Michael John Franks
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Publication number: 20240352863Abstract: An airfoil assembly for a turbine engine. The airfoil assembly has an airfoil, and a spa. The airfoil has a wall bounding an interior and defining an exterior surface. The wall extends between a leading edge and a trailing edge to define a chordwise direction, and between a root and a tip to define a spanwise direction. The spar includes a centerline axis. the spar extends into the interior of the airfoil.Type: ApplicationFiled: November 15, 2023Publication date: October 24, 2024Inventors: Ming Xie, Mitchell Harold Boyer, Tod Winton Davis
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Publication number: 20240352862Abstract: An airfoil assembly having a trunnion and a spar. The trunnion having an interior surface defining a flared socket with an open top. The spar extending from the flared socket and through the open top.Type: ApplicationFiled: April 21, 2023Publication date: October 24, 2024Inventors: Nicholas Joseph Kray, Tod Winton Davis, Nicholas Mark Daggett, Arthur William Sibbach, Elzbieta Kryj-Kos
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Patent number: 12078080Abstract: An airfoil assembly and a method of forming the airfoil assembly, the airfoil assembly having a trunnion, a spar, a skin, and an insert. The trunnion having a flared socket with an open top. The spar extending from the flared socket and through the open top. The spar having a first end located within the flared socket. The skin having a braided or woven fiber.Type: GrantFiled: April 21, 2023Date of Patent: September 3, 2024Assignee: General Electric CompanyInventors: Ming Xie, Tod Winton Davis
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Publication number: 20240209741Abstract: A composite blade assembly for a turbine engine. The composite blade assembly having a core, a first skin and a second skin. The core having a composite structure. The first skin having at least one composite ply. The second skin having at least one composite ply. The first skin having a first radius. The second skin having a second radius.Type: ApplicationFiled: December 27, 2022Publication date: June 27, 2024Inventors: Nicholas Joseph Kray, Elzbieta Kryj-Kos, Tod Winton Davis, Gary Willard Bryant, JR.
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Patent number: 11846192Abstract: An airfoil assembly and a method of forming the airfoil assembly, the airfoil assembly having a trunnion, a spar, and a set of inserts. The trunnion having a flared socket with an open top. The spar extending from the flared socket and through the open top. The spar having a first end located within the flared socket.Type: GrantFiled: April 21, 2023Date of Patent: December 19, 2023Assignee: General Electric CompanyInventors: Ming Xie, Mitchell Harold Boyer, Tod Winton Davis
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Patent number: 11047058Abstract: A method for making a metallic leading edge guard of the type having a nose with first and second wings extending therefrom is disclosed. The method includes machining from a metallic blank a first half comprising a first portion of the nose and one of the wings, wherein the first portion of the nose includes an interface surface; and electroforming a second half comprising a second portion of the nose and the second wing, wherein the second half is joined to the first half at the interface surface.Type: GrantFiled: April 2, 2015Date of Patent: June 29, 2021Assignee: GENERAL ELECTRIC COMPANYInventors: Qiang Li, Nicholas Joseph Kray, Michael W. Peretti, Tod Winton Davis
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Patent number: 10774679Abstract: An airfoil assembly for a turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, the airfoil extending axially between a leading edge and a trailing edge to define a chord-wise direction and also extending radially between a root and a tip to define a span-wise direction. An aperture and at least one slot can define at least a portion of a release plane extending through the outer wall.Type: GrantFiled: February 9, 2018Date of Patent: September 15, 2020Assignee: General Electric CompanyInventors: Stephanie Glynn Cotten, James Francis Brown, Theodore Robert Ingling, Tod Winton Davis, Gary Willard Bryant, Jr., Max Robert Farson
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Patent number: 10738630Abstract: A platform apparatus for a propulsion rotor having an annular array of airfoils carried by a rotor disk. The apparatus includes: at least one forward segment comprising an arcuate forward body having a plurality of spaced-apart axially-extending forward fingers, each of the forward fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by an aft edge, wherein the forward segment defines a flow path surface and an opposed back surface; at least one aft segment comprising an arcuate aft body having a plurality of spaced-apart actually-extending aft fingers, each of the aft fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by a forward edge, wherein the aft segment defines a flow path surface and an opposed back surface, and wherein the aft edges have a shape complementary to a shape of the forward edges.Type: GrantFiled: February 19, 2018Date of Patent: August 11, 2020Assignee: General Electric CompanyInventors: Qiang Li, Nicholas Joseph Kray, Gerald Alexander Pauley, Ming Xie, Jorge Orlando Lamboy, Tod Winton Davis
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Publication number: 20200123910Abstract: An airfoil assembly for a turbine engine includes an airfoil with an outer wall having a pressure side and a suction side, the airfoil extending axially between a leading edge and a trailing edge to define a chord-wise direction and also extending radially between a root and a tip to define a span-wise direction. An aperture and at least one slot can define at least a portion of a release plane extending through the outer wall.Type: ApplicationFiled: February 9, 2018Publication date: April 23, 2020Inventors: Stephanie Glynn Cotten, James Francis Brown, Theodore Robert Ingling, Tod Winton Davis, Gary Willard Bryant, JR., Max Robert Farson
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Patent number: 10494933Abstract: An airfoil includes: an airfoil body having convex and concave sides extending between a leading edge and a trailing edge, the airfoil body including primary and secondary regions having differing physical properties; and at least one metallic cladding element attached to the airfoil body.Type: GrantFiled: March 18, 2016Date of Patent: December 3, 2019Assignee: General Electric CompanyInventors: Gary Willard Bryant, Jr., Tod Winton Davis, Wei Wu
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Publication number: 20190257210Abstract: A platform apparatus for a propulsion rotor having an annular array of airfoils carried by a rotor disk. The apparatus includes: at least one forward segment comprising an arcuate forward body having a plurality of spaced-apart axially-extending forward fingers, each of the forward fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by an aft edge, wherein the forward segment defines a flow path surface and an opposed back surface; at least one aft segment comprising an arcuate aft body having a plurality of spaced-apart actually-extending aft fingers, each of the aft fingers bounded by a curved first lateral edge interconnected to a straight second lateral edge by a forward edge, wherein the aft segment defines a flow path surface and an opposed back surface, and wherein the aft edges have a shape complementary to a shape of the forward edges.Type: ApplicationFiled: February 19, 2018Publication date: August 22, 2019Inventors: Qiang Li, Nicholas Joseph Kray, Gerald Alexander Pauley, Ming Xie, Jorge Orlando Lamboy, Tod Winton Davis
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Patent number: 9885244Abstract: A metallic leading edge protective strip adapted to provide impact protection for a leading edge of an airfoil of a turbomachine. The protective strip is formed of a stainless steel or a nickel-based alloy and is denser and provides increased strength and elasticity characteristics as compared to an identical protective strip formed of a titanium-based alloy. The protective strip is particularly suitable for use with composite blades and allows for thinner airfoils, thereby improving engine efficiency.Type: GrantFiled: June 28, 2013Date of Patent: February 6, 2018Assignee: General Electric CompanyInventors: Nicholas Joseph Kray, Dong-Jin Shim, Tod Winton Davis
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Publication number: 20170268349Abstract: An airfoil includes: an airfoil body having convex and concave sides extending between a leading edge and a trailing edge, the airfoil body including primary and secondary regions having differing physical properties; and at least one metallic cladding element attached to the airfoil body.Type: ApplicationFiled: March 18, 2016Publication date: September 21, 2017Inventors: Gary Willard Bryant, JR., Tod Winton Davis, Wei Wu
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Patent number: 9239062Abstract: A fan blade for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side.Type: GrantFiled: September 10, 2012Date of Patent: January 19, 2016Assignee: General Electric CompanyInventors: Jorge Orlando Lamboy, Nicholas Joseph Kray, Gerald Alexander Pauley, Qiang Li, Daniel Allen Wilkin, II, Tod Winton Davis
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Publication number: 20150184527Abstract: A metallic leading edge protective strip adapted to provide impact protection for a leading edge of an airfoil of a turbomachine. The protective strip is formed of a stainless steel or a nickel-based alloy and is denser and provides increased strength and elasticity characteristics as compared to an identical protective strip formed of a titanium-based alloy. The protective strip is particularly suitable for use with composite blades and allows for thinner airfoils, thereby improving engine efficiency.Type: ApplicationFiled: June 28, 2013Publication date: July 2, 2015Applicant: GENERAL ELECTRIC COMPANYInventors: Nicholas Joseph Kray, Dong-Jin Shim, Tod Winton Davis
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Publication number: 20140219805Abstract: A fan blade for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side.Type: ApplicationFiled: September 10, 2012Publication date: August 7, 2014Inventors: Jorge Orlando Lamboy, Nicholas Joseph Kray, Gerald Alexander Pauley, Qiang Li, Daniel Allen Wilkin, II, Tod Winton Davis
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Patent number: 8046437Abstract: An improved system and method for supporting web system services is provided for storing data and context of client applications on the web. A client application may include a web system services interface for invoking web system services to support web applications to operate over the web using different devices that may store data and context of web applications as a web application document onto a web server. A web application document may be represented by components that may include view information, content, and context information. The application may also include a web system services user interface for providing a graphical user interface for a user to invoke web system services that may include a new document system service, a store document system service, and a restore document system service. A schema for context scope may be implemented for collecting context information relevant to the web application document.Type: GrantFiled: March 16, 2007Date of Patent: October 25, 2011Assignee: Yahoo! Inc.Inventors: Ronald Martinez, Karon A. Weber, Samantha Tripodi, Winton Davies, Chris Kalaboukis, Oliver Raskin