Patents by Inventor David Alan Frey
David Alan Frey 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: 11846207Abstract: A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.Type: GrantFiled: March 3, 2022Date of Patent: December 19, 2023Assignee: General Electric CompanyInventors: David Alan Frey, Jeffrey Douglas Rambo, Alexander Martin Sener, Kirk Douglas Gallier
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Publication number: 20230304408Abstract: A component for a gas turbine engine includes a first surface and a second surface. The component additionally includes one or more layers of ceramic matrix composite material extending between the first and second surfaces. A thermal void extends between a first end and a second end. The second end of the thermal void is a terminal end embedded in the component between the first and second surfaces.Type: ApplicationFiled: January 4, 2023Publication date: September 28, 2023Inventors: Ronald Scott Bunker, Kirk D. Gallier, David Alan Frey
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Publication number: 20230014436Abstract: A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.Type: ApplicationFiled: September 21, 2022Publication date: January 19, 2023Inventors: Alexander Martin Sener, Brian David Keith, David Alan Frey, Jamil Darnell Grant
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Publication number: 20220341339Abstract: A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.Type: ApplicationFiled: March 3, 2022Publication date: October 27, 2022Inventors: David Alan Frey, Jeffrey Douglas Rambo, Alexander Martin Sener, Kirk Douglas Gallier
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Patent number: 11441436Abstract: Flow path assemblies and methods for forming such flow path assemblies for gas turbine engines are provided. For example, a flow path assembly for a gas turbine engine has a boundary structure, an airfoil, and a locking feature. The boundary structure and the airfoil are formed from a composite material. The boundary structure defines an opening and a cutout proximate the opening, and the airfoil is sized to fit within the opening of the boundary structure. The locking feature is received within the cutout defined by the boundary structure to interlock the airfoil with the boundary structure.Type: GrantFiled: August 17, 2020Date of Patent: September 13, 2022Assignee: General Electric CompanyInventors: David Alan Frey, Kirk Douglas Gallier, Daniel Patrick Kerns, Brandon ALlanson Reynolds
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Patent number: 11391161Abstract: An apparatus and method relating an airfoil for a turbine engine with an outer wall bounding an interior and defining a pressure side and a suction side 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. The airfoil includes a first cooling passage extending in the span-wise direction within the interior and a second cooling passage defining an impingement surface and located proximate the first cooling passage, an interior wall separating the first cooling passage from the second cooling passage, and at least one cooling hole passing through the interior wall.Type: GrantFiled: July 19, 2018Date of Patent: July 19, 2022Assignee: General Electric CompanyInventors: David Alan Frey, Kirk D. Gallier
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Patent number: 11268394Abstract: A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.Type: GrantFiled: March 13, 2020Date of Patent: March 8, 2022Assignee: General Electric CompanyInventors: David Alan Frey, Jeffrey Douglas Rambo, Alexander Martin Sener, Kirk Douglas Gallier
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Patent number: 11193392Abstract: An ingestion restricting device is provided, which is particularly useful in a turbine engine. The ingestion restricting device can include a first component defining a first edge and including a plurality of ceramic matrix composite (CMC) plies forming outer, inner, and intermediate layers. The ingestion restricting device can also include a second component adjacent to the first component and defining a second edge. The first edge of the first component is opposite the second edge of the second component and defines a gap therebetween. Also, at least one ply of the plurality of CMC plies in the outer layer of the first component comprises an integral protrusion extending from the first edge a distance sufficient to traverse the gap and to overlap the second edge of the second component.Type: GrantFiled: March 21, 2016Date of Patent: December 7, 2021Assignee: General Electric CompanyInventor: David Alan Frey
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Publication number: 20210285332Abstract: A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.Type: ApplicationFiled: March 13, 2020Publication date: September 16, 2021Inventors: David Alan Frey, Jeffrey Douglas Rambo, Alexander Martin Sener, Kirk Douglas Gallier
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Patent number: 11085315Abstract: An apparatus and method of sealing for an engine component between two surfaces arranged in spaced relationship to define a gap. A groove located is located in one of the two surface for receiving a seal having a body with a multi-faceted cross-sectional shape defining multiple seal facets. At least one of the multiple seal facets contacts one or both of the two surfaces.Type: GrantFiled: July 9, 2019Date of Patent: August 10, 2021Assignee: General Electric CompanyInventors: Kirk Douglas Gallier, David Alan Frey
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Patent number: 11053809Abstract: A component, such as for a turbine engine, can include an airfoil with an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side 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. The component can also include at least one cooling passage within the interior.Type: GrantFiled: July 16, 2019Date of Patent: July 6, 2021Assignee: General Electric CompanyInventors: Daniel Endecott Osgood, David Alan Frey, Kirk D. Gallier, Steven Robert Brassfield
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Patent number: 11047240Abstract: CMC components having microchannels and methods for forming microchannels in CMC components are provided. For example, a method for forming microchannels in a CMC component comprises laying up a plurality of body plies for forming a body of the CMC component; laying up a microchannel ply on the plurality of body plies that has at least one void therein for forming at least one microchannel; laying up a cover ply on the microchannel ply to define an outer layer of the CMC component; and processing the laid up body plies, microchannel ply, and cover ply to form the CMC component. In another embodiment, the method comprises applying an additive matrix to the body plies to define at least one microchannel. In still other embodiments, the method comprises machining at least one microchannel in the plurality of body plies.Type: GrantFiled: May 11, 2017Date of Patent: June 29, 2021Assignee: General Electric CompanyInventors: David Alan Frey, Kirk Douglas Gallier, Herbert Chidsey Roberts
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Patent number: 10975701Abstract: Ceramic matrix composite (CMC) airfoils and methods for forming CMC airfoils are provided. In one embodiment, an airfoil is provided that includes opposite pressure and suction sides extending radially along a span and opposite leading and trailing edges extending radially along the span. The leading edge defines a forward end of the airfoil, and the trailing edge defines an aft end of the airfoil. A trailing edge portion is defined adjacent the trailing edge at the aft end, and a pocket is defined in and extends within the trailing edge portion. A heat pipe is received in the pocket. A method for forming an airfoil is provided that includes laying up a CMC material to form an airfoil preform assembly; processing the airfoil preform assembly; defining a pocket in a trailing edge portion of the airfoil; and inserting a heat pipe into the pocket.Type: GrantFiled: April 17, 2019Date of Patent: April 13, 2021Assignee: General Electric CompanyInventors: David Alan Frey, Samir Armando Salamah, Charles William Craig, III
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Publication number: 20210047932Abstract: Airfoils, additively manufactured airfoils, and methods of manufacturing airfoils are provided. For example, an airfoil comprises opposite pressure and suction sides that extend axially from a leading edge to a trailing edge and radially spaced apart inner and outer ends. The airfoil also comprises an outer wall defining the pressure and suction sides and leading and trailing edges. A rib extends within the airfoil from the pressure side to the suction side of the outer wall and radially from the inner to the outer end. The airfoil further comprises a first pre-impingement chamber surrounded by a first post-impingement chamber and a first dividing wall segment separating the first pre-impingement and first post-impingement chambers and having a plurality of cooling holes defined therein. The outer wall, rib, and first dividing wall segment are integrally formed as a single monolithic component.Type: ApplicationFiled: October 30, 2020Publication date: February 18, 2021Inventors: Charles William Craig, III, David Alan Frey
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Publication number: 20210040861Abstract: A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.Type: ApplicationFiled: October 26, 2020Publication date: February 11, 2021Inventors: Alexander Martin Sener, Brian David Keith, David Alan Frey, Jamil Darnell Grant
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Publication number: 20210017869Abstract: A component, such as for a turbine engine, can include an airfoil with an outer wall defining an exterior surface bounding an interior and defining a pressure side and a suction side 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. The component can also include at least one cooling passage within the interior.Type: ApplicationFiled: July 16, 2019Publication date: January 21, 2021Inventors: Daniel Endecott Osgood, David Alan Frey, Kirk D. Gallier, Steven Robert Brassfield
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Publication number: 20210010380Abstract: An apparatus and method of sealing for an engine component between two surfaces arranged in spaced relationship to define a gap. A groove located is located in one of the two surface for receiving a seal having a body with a multi-faceted cross-sectional shape defining multiple seal facets. At least one of the multiple seal facets contacts one or both of the two surfaces.Type: ApplicationFiled: July 9, 2019Publication date: January 14, 2021Inventors: Kirk Douglas Gallier, David Alan Frey
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Publication number: 20200378268Abstract: Flow path assemblies and methods for forming such flow path assemblies for gas turbine engines are provided. For example, a flow path assembly for a gas turbine engine has a boundary structure, an airfoil, and a locking feature. The boundary structure and the airfoil are formed from a composite material. The boundary structure defines an opening and a cutout proximate the opening, and the airfoil is sized to fit within the opening of the boundary structure. The locking feature is received within the cutout defined by the boundary structure to interlock the airfoil with the boundary structure.Type: ApplicationFiled: August 17, 2020Publication date: December 3, 2020Inventors: David Alan Frey, Kirk Douglas Gallier, Daniel Patrick Kerns, Brandon ALlanson Reynolds
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Patent number: 10837293Abstract: Airfoils, additively manufactured airfoils, and methods of manufacturing airfoils are provided. For example, an airfoil comprises opposite pressure and suction sides that extend axially from a leading edge to a trailing edge and radially spaced apart inner and outer ends. The airfoil also comprises an outer wall defining the pressure and suction sides and leading and trailing edges. A rib extends within the airfoil from the pressure side to the suction side of the outer wall and radially from the inner to the outer end. The airfoil further comprises a first pre-impingement chamber surrounded by a first post-impingement chamber and a first dividing wall segment separating the first pre-impingement and first post-impingement chambers and having a plurality of cooling holes defined therein. The outer wall, rib, and first dividing wall segment are integrally formed as a single monolithic component.Type: GrantFiled: July 19, 2018Date of Patent: November 17, 2020Assignee: General Electric CompanyInventors: Charles William Craig, III, David Alan Frey
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Patent number: 10822981Abstract: A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.Type: GrantFiled: October 30, 2017Date of Patent: November 3, 2020Assignee: General Electric CompanyInventors: Alexander Martin Sener, Brian David Keith, David Alan Frey, Jamil Darnell Grant