Patents by Inventor Paul Izon
Paul Izon 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: 10648352Abstract: A turbine blade sealing structure for a ceramic matrix composite component is provided. The turbine sealing structure includes at least one top ply abutting a top portion of a shank. The at least one top ply extends out over the top portion of the shank. The turbine sealing structure includes at least one side ply abutting a side portion of the shank. The at least one side ply extends along a side portion of the shank. The at least one top ply and at least one side ply form an angel wing and a skirt with on the shank of the ceramic matrix composite component.Type: GrantFiled: June 13, 2013Date of Patent: May 12, 2020Assignee: General Electric CompanyInventors: Anthony Reid Paige, Paul Izon, Michael Verrilli, Mark Willard Marusko, Mark Eugene Noe, Joshua Brian Jamison, Andrew John Breslin
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Patent number: 10457020Abstract: A method of forming a ceramic matrix composite turbine blade with squealer tip and with tip flare is provided. The tip flare may be located at either or both of the pressure side and the suction side. The method provides a mandrel which is placed in the pre-form tooling to create the cavity and aid in formation of the pressure side flare.Type: GrantFiled: January 7, 2015Date of Patent: October 29, 2019Assignee: General Electric CompanyInventors: Matthew Mark Weaver, Paul Izon, Kathleen Elizabeth Albers
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Patent number: 10287897Abstract: A rotor blade assembly for a rotor of a gas turbine engine having an axis of rotation includes a shank portion formed from a ceramic matrix composite (CMC) material. The rotor blade assembly also includes a platform portion formed from a substantially similar CMC material as that of the shank portion. The platform portion is coupled to the shank portion. The platform portion and the shank portion cooperate to at least partially define two opposing side portions of the rotor blade assembly. The opposing side portions are angularly separated with respect to the axis of rotation. The rotor blade assembly further includes a damper retention apparatus. The damper retention apparatus is coupled to the shank portion. The damper retention apparatus includes at least one angled bracket apparatus extending toward a circumferentially adjacent rotor blade assembly.Type: GrantFiled: September 8, 2011Date of Patent: May 14, 2019Assignee: General Electric CompanyInventors: Anthony Reid Paige, II, Michael James Verrilli, Joshua Brian Jamison, Mark Eugene Noe, Paul Izon, Mark Willard Marusko
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Patent number: 10018054Abstract: Methods for fabricating a component of a gas turbine engine are provided. In one embodiment, the method includes molding a CMC material to form a first portion of the gas turbine engine component, processing the first portion to form a first assembly, preparing the first assembly and a second portion of the gas turbine engine component for processing, and processing the first assembly and second portion to form a second assembly. In another embodiment, the method includes processing a first plurality of CMC plies to form a first assembly; positioning the first assembly and a second plurality of CMC plies on a tool for processing, the first assembly defining a first plane, the second plurality of plies defining a second plane, wherein the second plane is perpendicular to the first plane; and processing the first assembly and the second plurality of plies to form a second assembly.Type: GrantFiled: October 23, 2015Date of Patent: July 10, 2018Assignee: General Electric CompanyInventors: Michael J. Verrilli, Mark Eugene Noe, Mark Willard Marusko, Paul Izon, Robert Tyler, Christopher Hasse
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Publication number: 20170114649Abstract: Methods for fabricating a component of a gas turbine engine are provided. In one embodiment, the method includes molding a CMC material to form a first portion of the gas turbine engine component, processing the first portion to form a first assembly, preparing the first assembly and a second portion of the gas turbine engine component for processing, and processing the first assembly and second portion to form a second assembly. In another embodiment, the method includes processing a first plurality of CMC plies to form a first assembly; positioning the first assembly and a second plurality of CMC plies on a tool for processing, the first assembly defining a first plane, the second plurality of plies defining a second plane, wherein the second plane is perpendicular to the first plane; and processing the first assembly and the second plurality of plies to form a second assembly.Type: ApplicationFiled: October 23, 2015Publication date: April 27, 2017Inventors: Michael J. Verrilli, Mark Eugene Noe, Mark Willard Marusko, Paul Izon, Robert Tyler, Christopher Hasse
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Publication number: 20160333698Abstract: A method of forming a ceramic matrix composite turbine blade with squealer tip and with tip flare is provided. The tip flare may be located at either or both of the pressure side and the suction side. The method provides a mandrel which is placed in the pre-form tooling to create the cavity and aid in formation of the pressure side flare.Type: ApplicationFiled: January 7, 2015Publication date: November 17, 2016Inventors: Matthew Mark WEAVER, Paul IZON, Kathleen Elizabeth ALBERS
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Patent number: 9410437Abstract: A process for producing airfoil components containing ceramic-based materials and having a tip cap. The process entails forming an airfoil portion of the component from an airfoil portion material that contains a precursor of a ceramic-based material. The airfoil portion material defines concave and convex walls of the airfoil portion, and the concave and convex walls define a tip region of the airfoil portion and at least one cavity within the airfoil portion. At least a first ply is formed that contains a precursor of a ceramic-based material, and the first ply at least partially closes the cavity at the tip region of the airfoil portion. The airfoil portion material and the first ply are then cured so that the first ply forms a tip cap that closes the cavity and the precursors of the airfoil portion material and first ply are converted to the ceramic-based materials thereof.Type: GrantFiled: December 20, 2012Date of Patent: August 9, 2016Assignee: General Electric CompanyInventors: Anthony Reid Paige, Mark Eugene Noe, Michael James Verrilli, Mark Willard Marusko, Joshua Brian Jamison, Paul Izon
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Publication number: 20150192027Abstract: A turbine blade sealing structure for a ceramic matrix composite component is provided. The turbine sealing structure includes at least one top ply abutting a top portion of a shank. The at least one top ply extends out over the top portion of the shank. The turbine sealing structure includes at least one side ply abutting a side portion of the shank. The at least one side ply extends along a side portion of the shank.Type: ApplicationFiled: June 13, 2013Publication date: July 9, 2015Inventors: Anthony Reid Paige, Paul Izon, Michael Verrilli, Mark Willard Marusko, Mark Eugene Noe, Joshua Brian Jamison, Andrew John Breslin
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Patent number: 8714932Abstract: A method of making a ceramic matrix composite blade includes laying up at least one ply of the plurality of fibrous ceramic plies in a preselected arrangement to form an airfoil and dovetail preform, laying up at least one additional ply of the plurality of fibrous ceramic plies on the airfoil and dovetail preform in a second preselected arrangement to form an integral platform as part of the non-rigidized blade preform, rigidizing the blade preform to form a rigidized blade preform, and densifying the rigidized blade preform to form a ceramic matrix composite blade having an integral platform structure. A tool for making the ceramic matrix composite blade and a ceramic matrix composite blade are also disclosed.Type: GrantFiled: December 31, 2008Date of Patent: May 6, 2014Assignee: General Electric CompanyInventors: Mark E. Noe, Mark W. Marusko, Joshua B. Jamision, Suresh Subramanian, Michael J. Verrilli, Paul Izon
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Publication number: 20140050893Abstract: A process for producing airfoil components containing ceramic-based materials and having a tip cap. The process entails forming an airfoil portion of the component from an airfoil portion material that contains a precursor of a ceramic-based material. The airfoil portion material defines concave and convex walls of the airfoil portion, and the concave and convex walls define a tip region of the airfoil portion and at least one cavity within the airfoil portion. At least a first ply is formed that contains a precursor of a ceramic-based material, and the first ply at least partially closes the cavity at the tip region of the airfoil portion. The airfoil portion material and the first ply are then cured so that the first ply forms a tip cap that closes the cavity and the precursors of the airfoil portion material and first ply are converted to the ceramic-based materials thereof.Type: ApplicationFiled: December 20, 2012Publication date: February 20, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Anthony Reid Paige, Mark Eugene Noe, Michael James Verrilli, Mark Willard Marusko, Joshua Brian Jamison, Paul Izon
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Publication number: 20130064668Abstract: A rotor blade assembly for a rotor of a gas turbine engine having an axis of rotation includes a shank portion formed from a ceramic matrix composite (CMC) material. The rotor blade assembly also includes a platform portion formed from a substantially similar CMC material as that of the shank portion. The platform portion is coupled to the shank portion. The platform portion and the shank portion cooperate to at least partially define two opposing side portions of the rotor blade assembly. The opposing side portions are angularly separated with respect to the axis of rotation. The rotor blade assembly further includes a damper retention apparatus. The damper retention apparatus is coupled to the shank portion. The damper retention apparatus includes at least one angled bracket apparatus extending toward a circumferentially adjacent rotor blade assembly.Type: ApplicationFiled: September 8, 2011Publication date: March 14, 2013Inventors: Anthony Reid Paige, II, Michael James Verrilli, Joshua Brian Jamison, Mark Eugene Noe, Paul Izon, Mark Willard Marusko
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Publication number: 20110027098Abstract: A method of making a ceramic matrix composite blade includes laying up at least one ply of the plurality of fibrous ceramic plies in a preselected arrangement to form an airfoil and dovetail preform, laying up at least one additional ply of the plurality of fibrous ceramic plies on the airfoil and dovetail preform in a second preselected arrangement to form an integral platform as part of the non-rigidized blade preform, rigidizing the blade preform to form a rigidized blade preform, and densifying the rigidized blade preform to form a ceramic matrix composite blade having an integral platform structure. A tool for making the ceramic matrix composite blade and a ceramic matrix composite blade are also disclosed.Type: ApplicationFiled: December 31, 2008Publication date: February 3, 2011Applicant: General Electric CompanyInventors: Mark E. NOE, Mark W. MARUSKO, Joshua B. JAMISION, Suresh SUBRAMANIAN, Michael J. VERRILLI, Paul IZON
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Patent number: 6773234Abstract: A method enables a rotor assembly for a gas turbine engine to be fabricated. The method includes forming a blade including an airfoil extending from an integral dovetail used to mount the blade within the rotor assembly, and extending a projection from at least a portion of the blade, such that the stresses induced within at least a portion of the blade are facilitated to be maintained below a predetermined failure threshold for the blade to facilitate preventing failure of the blade.Type: GrantFiled: October 18, 2002Date of Patent: August 10, 2004Assignee: General Electric CompanyInventors: Sunil Kumar Sinha, Max Farson, Ming Cheng Li, Paul Izon, Nicholas Joseph Kray
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Publication number: 20040076523Abstract: A method enables a rotor assembly for a gas turbine engine to be fabricated. The method includes forming a blade including an airfoil extending from an integral dovetail used to mount the blade within the rotor assembly, and extending a projection from at least a portion of the blade, such that the stresses induced within at least a portion of the blade are facilitated to be maintained below a predetermined failure threshold for the blade to facilitate preventing failure of the blade.Type: ApplicationFiled: October 18, 2002Publication date: April 22, 2004Inventors: Sunil Kumar Sinha, Max Farson, Ming Cheng Li, Paul Izon, Nicholas Joseph Kray