Patents by Inventor Bruce E. Varney
Bruce E. Varney 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: 11725535Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends between the inner platform and the outer platform. A reinforcement spar extends between the inner platform and the outer platform through a hollow core of the ceramic-containing airfoil.Type: GrantFiled: August 21, 2018Date of Patent: August 15, 2023Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce CorporationInventors: Ted J. Freeman, Bruce E. Varney, David J. Thomas, Jeffrey A. Walston
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Patent number: 11619387Abstract: A liner for a combustor includes a support member, an intermediate member, and a liner member. The intermediate member is positioned intermediate the support member and the liner member and has a plurality of protrusions and a plurality of recesses. The support member is coupled to the intermediate member at a tangent of each protrusion. Additionally, the liner member is comprised of a ceramic matrix composite material. The liner member is coupled to the intermediate member at a tangent of each recess.Type: GrantFiled: July 27, 2016Date of Patent: April 4, 2023Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Ted Joseph Freeman, Bruce E. Varney, Adam L. Chamberlain
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Patent number: 11274567Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.Type: GrantFiled: April 16, 2019Date of Patent: March 15, 2022Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce CorporationInventors: Daniel K. Vetters, Aaron D. Sippel, David J. Thomas, Andrew J. Eifert, Paul A. Davis, Simon L. Jones, Peter Broadhead, Bruce E. Varney, Jeffrey A. Walston, Steven Hillier
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Patent number: 11268389Abstract: A turbine blade is secured with a turbine disk by a retention assembly. The turbine blade includes a blade stem and the disk includes at least one mount post for mounting of the turbine blade. The retention assembly is secured with the disk by forming a diffusion joint with the disk.Type: GrantFiled: May 14, 2018Date of Patent: March 8, 2022Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce CorporationInventors: Ted J. Freeman, Aaron D. Sippel, Bruce E. Varney
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Patent number: 11149590Abstract: An assembly for a gas turbine engine includes ceramic material containing (i.e. ceramic matrix composite) segments and joints that couple the segments together.Type: GrantFiled: May 30, 2018Date of Patent: October 19, 2021Assignees: Rolls-Royce Corporation, Rolls-Royce High Temperature Composites, Inc., Rolls-Roycfe North American Technologies Inc.Inventors: Aaron D. Sippel, Ted J. Freeman, Joseph P. Lamusga, Daniel K. Vetters, Sean E. Landwehr, Bruce E. Varney
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Patent number: 10954809Abstract: A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints.Type: GrantFiled: May 25, 2018Date of Patent: March 23, 2021Assignees: Rolls-Royce High Temperature Composites Inc., Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Aaron D. Sippel, Bruce E. Varney, Ted J. Freeman, Christopher Barrett
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Patent number: 10837314Abstract: A system for a hot section dual wall component in a gas turbine engine is used to avoid blockage by minimizing particulate deposits. The system includes impingement apertures formed in first wall of a cooling passageway of the dual wall component, and posts included on a second wall of the cooling passageway. The impingement apertures and the posts are respectively aligned opposite each other in the cooling passageway in operative cooperation so that working fluid exhausting into the cooling passageway from the impingement apertures in a first direction is directed to flow in a second direction along the cooling passageway to provide a laminar flow of the working fluid through the cooling passageway in order to minimize deposition of particles.Type: GrantFiled: July 6, 2018Date of Patent: November 17, 2020Assignee: Rolls-Royce CorporationInventors: Bruce E. Varney, Brett Barker
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Patent number: 10830058Abstract: An airfoil for use in a gas turbine engine is disclosed herein. The airfoil includes a pressure side wall, a suction side wall, and a cooling air distribution system. The suction side wall is arranged opposite the pressure side wall. The cooling air distribution system is formed internal to at least one of the pressure side wall and the suction side wall. The cooling air distribution system is configured to distribute cooling air through the airfoil to cool the airfoil.Type: GrantFiled: October 27, 2017Date of Patent: November 10, 2020Assignee: Rolls-Royce CorporationInventors: Brett J. Barker, Bruce E. Varney, Paul H. Davis, Kevin P. Holley
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Patent number: 10767863Abstract: An annular assembly for a gas turbine engine and a method of making the annular assembly. The annular assembly comprises a supporting member comprising metal and including a support hole therethrough, and a liner tile made of ceramic matrix composite material. A plurality of the liner tile form an annular liner to shield hot combustion gases produced by the gas turbine engine. The liner tile is disposed adjacent the supporting member. A connecting member comprising ceramic material has a base element and a stem. The base element is embedded in the liner tile during construction of the liner tile to form an integrated structure therewith. A distal end of the stem passes through the support hole and is mated with a retaining member to retain the liner tile adjacent the supporting member.Type: GrantFiled: July 22, 2016Date of Patent: September 8, 2020Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce CorporationInventors: Ted Joseph Freeman, Bruce E. Varney, Andrew Joseph Lazur
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Patent number: 10683770Abstract: A turbine shroud adapted for use in a gas turbine engine is disclosed in this paper. The turbine shroud includes a blade track segment comprising ceramic matrix composite materials and an attachment unit comprising metallic materials. The attachment unit is coupled to the blade track segment and is configured to interface with other metallic components in the gas turbine engine.Type: GrantFiled: April 18, 2018Date of Patent: June 16, 2020Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce CorporationInventors: Ted J. Freeman, Bruce E. Varney
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Patent number: 10648669Abstract: A combustor adapted for use in a gas turbine engine is disclosed. The combustor includes a metallic case forming a cavity and a ceramic liner arranged in the cavity of the metallic case. The ceramic liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine. The ceramic liner is located in the metallic case using a plurality of cross key connectors.Type: GrantFiled: July 20, 2016Date of Patent: May 12, 2020Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.Inventors: Bruce E. Varney, Ted J. Freeman, Adam L. Chamberlain
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Patent number: 10633996Abstract: A turbine assembly for a gas turbine engine is disclosed herein. The turbine assembly includes a turbine vane and an annular turbine shroud. The turbine vane has an airfoil extending through a primary gas path and is formed to include cooling passages sized to conduct cooling air from an inlet aperture to a discharge aperture. The turbine shroud is adapted to extend around a bladed turbine wheel to resist gasses from passing over turbine blades without interacting with the turbine blades. The turbine shroud includes a ceramic matrix composite blade track having a radially-inwardly facing inner surface arranged in confronting relation with the primary gas path.Type: GrantFiled: November 17, 2016Date of Patent: April 28, 2020Assignee: Rolls-Royce CorporationInventors: Brett J. Barker, Bruce E. Varney
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Patent number: 10563535Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.Type: GrantFiled: April 4, 2016Date of Patent: February 18, 2020Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce plcInventors: Daniel K. Vetters, Aaron D. Sippel, David J. Thomas, Andrew J. Eifert, Paul A. Davis, Simon L. Jones, Peter Broadhead, Bruce E. Varney, Jeffrey A. Walston, Steven Hillier
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Publication number: 20200011199Abstract: A system for a hot section dual wall component in a gas turbine engine is used to avoid blockage by minimizing particulate deposits. The system includes impingement apertures formed in first wall of a cooling passageway of the dual wall component, and posts included on a second wall of the cooling passageway. The impingement apertures and the posts are respectively aligned opposite each other in the cooling passageway in operative cooperation so that working fluid exhausting into the cooling passageway from the impingement apertures in a first direction is directed to flow in a second direction along the cooling passageway to provide a laminar flow of the working fluid through the cooling passageway in order to minimize deposition of particles.Type: ApplicationFiled: July 6, 2018Publication date: January 9, 2020Applicant: Rolls-Royce CorporationInventors: Bruce E. Varney, Brett Barker
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Patent number: 10480342Abstract: A gas turbine engine includes a turbine having a plurality of vanes, a plurality of blades, a turbine shroud arranged around the vanes and blades, and a turbine case arranged around the turbine shroud. The turbine shroud is sized to block combustion products from passing over the blades without pushing the blades to rotate. The turbine shroud includes a runner arranged around the blades and a carrier arranged around the runner.Type: GrantFiled: January 19, 2016Date of Patent: November 19, 2019Assignee: Rolls-Royce CorporationInventors: Bruce E. Varney, Jack D. Petty, Daniel K. Vetters, Eugene Clemens
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Publication number: 20190345831Abstract: A turbine blade is secured with a turbine disk by a retention assembly. The retention assembly is secured with the disk by forming a diffusion joint with the disk.Type: ApplicationFiled: May 14, 2018Publication date: November 14, 2019Inventors: Ted J. Freeman, Aaron D. Sippel, Bruce E. Varney
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Publication number: 20190242268Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.Type: ApplicationFiled: April 16, 2019Publication date: August 8, 2019Inventors: Daniel K. Vetters, Aaron D. Sippel, David J. Thomas, Andrew J. Eifert, Paul A. Davis, Simon L. Jones, Peter Broadhead, Bruce E. Varney, Jeffrey A. Walston, Steven Hillier
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Patent number: 10371008Abstract: A turbine shroud for a gas turbine engine includes an annular metallic carrier and a ceramic-containing blade track. A connection is formed between the annular metallic carrier and the ceramic-containing blade track by insert pins extending through metallic carrier into the ceramic-containing blade track.Type: GrantFiled: December 17, 2015Date of Patent: August 6, 2019Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce CorporationInventors: Aaron D. Sippel, Bruce E. Varney, Ted J. Freeman, Jeffrey A. Walston, Jun Shi
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Patent number: 10260362Abstract: A turbine vane for a gas turbine engine incorporating a ceramic matrix composite airfoil is disclosed in this paper. The turbine vane includes an attachment unit configured to mount the ceramic matrix composite airfoil to other metallic components of the turbine vane.Type: GrantFiled: May 30, 2017Date of Patent: April 16, 2019Assignee: Rolls-Royce CorporationInventor: Bruce E. Varney
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Patent number: 10247040Abstract: A gas turbine engine includes a turbine having a plurality of vanes, a plurality of blades, a turbine shroud arranged around the vanes and blades, and a turbine case arranged around the turbine shroud. The turbine shroud is sized to block combustion products from passing over the blades without pushing the blades to rotate. The turbine shroud includes a runner arranged around the blades and a carrier arranged around the runner.Type: GrantFiled: January 19, 2016Date of Patent: April 2, 2019Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce CorporationInventors: Bruce E. Varney, Jack D. Petty, Daniel K. Vetters, Eugene Clemens