Patents by Inventor Bruce Edward Varney
Bruce Edward 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: 11796174Abstract: A combustion assembly for a gas turbine engine may be provided. The combustion assembly may include a ceramic matrix composite combustor shell, which may include a chamber defined by a wall of the ceramic matrix composite combustor shell, and the ceramic matrix composite combustor shell may include a ceramic matrix composite chute integral with the ceramic matrix composite combustor shell. The ceramic matrix composite chute may extend towards a midline of the chamber. A method for fabricating a ceramic matrix composite chute may be provided. At least one chute may be woven in three dimensions into a ceramic preform. A layup tool may be inserted into the chute. The chute may be enlarged with the layup tool. The ceramic preform may be formed into a ceramic matrix composite body, which includes a combustor shell and the chute.Type: GrantFiled: July 22, 2019Date of Patent: October 24, 2023Assignee: ROLLS-ROYCE CORPORATIONInventor: Bruce Edward Varney
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Patent number: 11655543Abstract: A method includes predicting a composition of calcium-magnesium-aluminum-silicate (CMAS) to be encountered by a high temperature mechanical system during use of the high temperature mechanical system. The method further includes selecting a composition of a CMAS-resistant barrier coating layer based at least in part on the predicted composition of CMAS. The CMAS-resistant barrier coating layer includes a base composition and at least one secondary oxide selected based on the predicted composition of CMAS. The at least one secondary oxide includes at least one of an oxide of a divalent element, an oxide of a trivalent element, or an oxide of a tetravalent element. The CMAS-resistant barrier coating layer comprises greater than 0 mol. % and less than about 7 mol. % of the at least one secondary oxide.Type: GrantFiled: August 8, 2018Date of Patent: May 23, 2023Assignees: ROLLS-ROYCE CORPORATION, ROLLS-ROYCE PLC, ROLLS-ROYCE NORTH AMERICAN TECHNOLOGIES, INC.Inventors: Ngunjoh Lawrence Ndamka, Li Li, Ann Bolcavage, Bruce Edward Varney, Sean E. Landwehr
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Patent number: 11248491Abstract: An example gas turbine engine component includes a component configured to separate a cooling air plenum from a heated gas environment. The component includes a substrate defining a surface, and a unitary structure. The unitary structure includes a cooling region and a cover layer. The cover layer defines a hot wall surface configured to face the heated gas environment. The cooling region is disposed between the cover surface and the substrate and includes a plurality of support structures extending between the cover layer and the surface of the substrate. At least some of the support structures define a respective bond surface bonded to the substrate at the surface of the substrate. An example technique for fabricating the gas turbine engine component includes additively depositing the unitary structure on the surface of the substrate.Type: GrantFiled: December 27, 2019Date of Patent: February 15, 2022Assignee: ROLLS-ROYCE CORPORATIONInventor: Bruce Edward Varney
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Patent number: 11199097Abstract: A component for a gas turbine engine that separates a cooling air plenum from a heated gas environment. The component defines a hot section surface adjacent to the heated gas environment having a plurality of cooling apertures fluidically connecting the cooling air plenum to the heated gas environment to allow a cooling air to flow from the cooling air plenum to the heated gas environment through the plurality of cooling apertures. The plurality of cooling apertures each have an aperture diameter of less than about 3 millimeters (mm) and an average surface roughness of less than about 1 micrometer (1 ?m).Type: GrantFiled: January 27, 2020Date of Patent: December 14, 2021Assignee: ROLLS-ROYCE CORPORATIONInventor: Bruce Edward Varney
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Patent number: 10914177Abstract: Techniques for forming a dual-walled component for a gas turbine engine that include chemically etching at least one of a hot section part or a cold section part to form an etched part having plurality of support structures and bonding the etched part to a corresponding cold section part or a corresponding hot section part to form a dual-walled component, with the plurality of support structures defining at least one cooling channel between the at least one of the hot section part or the cold section part and the corresponding cold section part or the corresponding hot section part.Type: GrantFiled: December 30, 2019Date of Patent: February 9, 2021Assignee: Rolls-Royce CorporationInventor: Bruce Edward Varney
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Publication number: 20200165922Abstract: A component for a gas turbine engine that separates a cooling air plenum from a heated gas environment. The component defines a hot section surface adjacent to the heated gas environment having a plurality of cooling apertures fluidically connecting the cooling air plenum to the heated gas environment to allow a cooling air to flow from the cooling air plenum to the heated gas environment through the plurality of cooling apertures. The plurality of cooling apertures each have an aperture diameter of less than about 3 millimeters (mm) and an average surface roughness of less than about 1 micrometer (1 ?m).Type: ApplicationFiled: January 27, 2020Publication date: May 28, 2020Inventor: Bruce Edward Varney
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Publication number: 20200149408Abstract: Techniques for forming a dual-walled component for a gas turbine engine that include chemically etching at least one of a hot section part or a cold section part to form an etched part having plurality of support structures and bonding the etched part to a corresponding cold section part or a corresponding hot section part to form a dual-walled component, with the plurality of support structures defining at least one cooling channel between the at least one of the hot section part or the cold section part and the corresponding cold section part or the corresponding hot section part.Type: ApplicationFiled: December 30, 2019Publication date: May 14, 2020Inventor: Bruce Edward Varney
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Publication number: 20200131931Abstract: An example gas turbine engine component includes a component configured to separate a cooling air plenum from a heated gas environment. The component includes a substrate defining a surface, and a unitary structure. The unitary structure includes a cooling region and a cover layer. The cover layer defines a hot wall surface configured to face the heated gas environment. The cooling region is disposed between the cover surface and the substrate and includes a plurality of support structures extending between the cover layer and the surface of the substrate. At least some of the support structures define a respective bond surface bonded to the substrate at the surface of the substrate. An example technique for fabricating the gas turbine engine component includes additively depositing the unitary structure on the surface of the substrate.Type: ApplicationFiled: December 27, 2019Publication date: April 30, 2020Inventor: Bruce Edward Varney
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Publication number: 20200103112Abstract: A combustion assembly for a gas turbine engine may be provided. The combustion assembly may include a ceramic matrix composite combustor shell, which may include a chamber defined by a wall of the ceramic matrix composite combustor shell, and the ceramic matrix composite combustor shell may include a ceramic matrix composite chute integral with the ceramic matrix composite combustor shell. The ceramic matrix composite chute may extend towards a midline of the chamber. A method for fabricating a ceramic matrix composite chute may be provided. At least one chute may be woven in three dimensions into a ceramic preform. A layup tool may be inserted into the chute. The chute may be enlarged with the layup tool. The ceramic preform may be formed into a ceramic matrix composite body, which includes a combustor shell and the chute.Type: ApplicationFiled: July 22, 2019Publication date: April 2, 2020Applicant: Rolls-Royce CorporationInventor: BRUCE EDWARD VARNEY
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Patent number: 10544683Abstract: A component for a gas turbine engine that separates a cooling air plenum from a heated gas environment. The component defines a hot section surface adjacent to the heated gas environment having a plurality of cooling apertures fluidically connecting the cooling air plenum to the heated gas environment to allow a cooling air to flow from the cooling air plenum to the heated gas environment through the plurality of cooling apertures. The plurality of cooling apertures each have an aperture diameter of less than about 3 millimeters (mm) and an average surface roughness of less than about 1 micrometer (1 ?m).Type: GrantFiled: August 9, 2017Date of Patent: January 28, 2020Assignee: Rolls-Royce CorporationInventor: Bruce Edward Varney
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Publication number: 20190048475Abstract: A method includes predicting a composition of calcium-magnesium-aluminum-silicate (CMAS) to be encountered by a high temperature mechanical system during use of the high temperature mechanical system. The method further includes selecting a composition of a CMAS-resistant barrier coating layer based at least in part on the predicted composition of CMAS. The CMAS-resistant barrier coating layer includes a base composition and at least one secondary oxide selected based on the predicted composition of CMAS. The at least one secondary oxide includes at least one of an oxide of a divalent element, an oxide of a trivalent element, or an oxide of a tetravalent element. The CMAS-resistant barrier coating layer comprises greater than 0 mol. % and less than about 7 mol. % of the at least one secondary oxide.Type: ApplicationFiled: August 8, 2018Publication date: February 14, 2019Inventors: Ngunjoh Lawrence Ndamka, Li Li, Ann Bolcavage, Bruce Edward Varney, Sean E. Landwehr
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Patent number: 10024175Abstract: A method for forming a hole in a ceramic matrix composite (CMC) component may be provided. A sacrificial fiber having an environmental barrier coating on an outer surface thereof may be inserted into a porous ceramic preform that includes ceramic fibers. The ceramic preform may be formed into a ceramic matrix composite body. The sacrificial fiber may be removed from the ceramic matrix composite body, the environmental barrier coating of the sacrificial fiber defining an opening in the ceramic matrix composite body. A ceramic matrix composite component may be provided. The ceramic matrix composite component may include an environmental barrier coating of a sacrificial fiber, where the environmental barrier coating forms a lining of a hole passing partly or entirely through a thickness of the ceramic matrix composite body.Type: GrantFiled: May 26, 2015Date of Patent: July 17, 2018Assignee: Rolls-Royce CorporationInventor: Bruce Edward Varney
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Publication number: 20180058222Abstract: A component for a gas turbine engine that separates a cooling air plenum from a heated gas environment. The component defines a hot section surface adjacent to the heated gas environment having a plurality of cooling apertures fluidically connecting the cooling air plenum to the heated gas environment to allow a cooling air to flow from the cooling air plenum to the heated gas environment through the plurality of cooling apertures. The plurality of cooling apertures each have an aperture diameter of less than about 3 millimeters (mm) and an average surface roughness of less than about 1 micrometer (1 ?m).Type: ApplicationFiled: August 9, 2017Publication date: March 1, 2018Inventor: Bruce Edward Varney
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Patent number: 9797263Abstract: A method to form a hole in a ceramic matrix composite component may be provided. A monolithic rod may be inserted into a porous ceramic preform. The ceramic preform may be formed into a ceramic matrix composite body that includes the monolithic rod. A portion of the monolithic rod may be removed, leaving a remaining portion in the ceramic matrix composite body. The remaining portion may include walls that define the opening in the ceramic matrix composite body. Alternatively or in addition, a ceramic matrix composite component may be provided. The ceramic matrix composite component may comprise a ceramic matrix composite body that includes a portion of a monolithic rod. The portion of the monolithic rod forms a lining around a hole passing partly or entirely through a length of the monolithic rod.Type: GrantFiled: May 26, 2015Date of Patent: October 24, 2017Assignee: Rolls-Royce CorporationInventors: Bruce Edward Varney, Ted Joseph Freeman
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Publication number: 20170059159Abstract: A combustion assembly for a gas turbine engine may be provided. The combustion assembly may include a ceramic matrix composite combustor shell, which may include a chamber defined by a wall of the ceramic matrix composite combustor shell, and the ceramic matrix composite combustor shell may include a ceramic matrix composite chute integral with the ceramic matrix composite combustor shell. The ceramic matrix composite chute may extend towards a midline of the chamber. A method for fabricating a ceramic matrix composite chute may be provided. At least one chute may be woven in three dimensions into a ceramic preform. A layup tool may be inserted into the chute. The chute may be enlarged with the layup tool. The ceramic preform may be formed into a ceramic matrix composite body, which includes a combustor shell and the chute.Type: ApplicationFiled: August 25, 2015Publication date: March 2, 2017Inventor: BRUCE EDWARD VARNEY
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Publication number: 20160348511Abstract: A method for forming a hole in a ceramic matrix composite (CMC) component may be provided. A sacrificial fiber having an environmental barrier coating on an outer surface thereof may be inserted into a porous ceramic preform that includes ceramic fibers. The ceramic preform may be formed into a ceramic matrix composite body. The sacrificial fiber may be removed from the ceramic matrix composite body, the environmental barrier coating of the sacrificial fiber defining an opening in the ceramic matrix composite body. A ceramic matrix composite component may be provided. The ceramic matrix composite component may include an environmental barrier coating of a sacrificial fiber, where the environmental barrier coating forms a lining of a hole passing partly or entirely through a thickness of the ceramic matrix composite body.Type: ApplicationFiled: May 26, 2015Publication date: December 1, 2016Inventor: Bruce Edward Varney
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Publication number: 20160348515Abstract: A method to form a hole in a ceramic matrix composite component may be provided. A monolithic rod may be inserted into a porous ceramic preform. The ceramic preform may be formed into a ceramic matrix composite body that includes the monolithic rod. A portion of the monolithic rod may be removed, leaving a remaining portion in the ceramic matrix composite body. The remaining portion may include walls that define the opening in the ceramic matrix composite body. Alternatively or in addition, a ceramic matrix composite component may be provided. The ceramic matrix composite component may comprise a ceramic matrix composite body that includes a portion of a monolithic rod. The portion of the monolithic rod forms a lining around a hole passing partly or entirely through a length of the monolithic rod.Type: ApplicationFiled: May 26, 2015Publication date: December 1, 2016Inventors: Bruce Edward Varney, Ted Joseph Freeman
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Publication number: 20130139514Abstract: A method is disclosed herein for reducing binding between a combustor liner of a gas turbine engine and a free-standing ring disposed about the combustor liner. The method comprises the step of disposing a rolling assembly to roll between the combustor liner and the free-standing ring during relative radial displacement.Type: ApplicationFiled: March 7, 2011Publication date: June 6, 2013Inventors: Bruce Edward Varney, Vickie Rae Smiley, Todd S. Taylor, Jack Dwane Petty, SR.
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Publication number: 20120167572Abstract: One embodiment of the present invention is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and components thereof. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: ApplicationFiled: December 22, 2011Publication date: July 5, 2012Inventors: Edward Claude Rice, Jack Dwane Petty, Bruce Edward Varney, Mindi Danette Wigal
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Patent number: 7900461Abstract: The invention is a combination that includes a gas turbine engine extending along an axis. The gas turbine engine includes an annular combustor with a combustor liner. The combination of the invention also includes a plurality of projections extending from the combustor liner and spaced from one another circumferentially about the axis. The combination of the invention also includes a free-standing ring disposed about the combustor liner and positioned adjacent to the plurality of projections along the axis. The plurality of projections engage a corresponding circumferentially-facing portion of the free-standing ring and circumferentially support the combustor liner while allowing relative radial displacement between the combustor liner and the free-standing ring. The combination of the invention also includes a rolling assembly operably disposed between the free-standing ring and the plurality of projections to reduce binding during the relative radial displacement.Type: GrantFiled: May 31, 2007Date of Patent: March 8, 2011Assignee: Rolls-Royce CorporationInventors: Bruce Edward Varney, Vickie Rae Smiley, Todd S. Taylor, Jack Dwane Petty, Sr.