Patents by Inventor Luis Tapia
Luis Tapia 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: 11220918Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.Type: GrantFiled: September 14, 2020Date of Patent: January 11, 2022Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Jeff Howe, Luis Tapia
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Patent number: 11208900Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.Type: GrantFiled: August 29, 2019Date of Patent: December 28, 2021Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Jeff Howe, Luis Tapia
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Publication number: 20210003019Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.Type: ApplicationFiled: September 14, 2020Publication date: January 7, 2021Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jeff Howe, Luis Tapia
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Patent number: 10830052Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.Type: GrantFiled: September 15, 2016Date of Patent: November 10, 2020Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Jeff Howe, Luis Tapia
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Patent number: 10669862Abstract: An airfoil includes a leading edge and an opposing trailing edge. The airfoil includes a pressure sidewall and an opposing suction sidewall. A leading edge cavity is defined between the pressure sidewall and the suction sidewall. The leading edge cavity has a first end opposite the leading edge and a second end defined at a rib. The airfoil includes at least one pin structure defined in the leading edge cavity between the first end and the second end. The at least one pin structure includes a main body and a first branch. The main body is coupled to the second end and extends toward the first end. The first branch extends from the main body toward the first end.Type: GrantFiled: July 13, 2018Date of Patent: June 2, 2020Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Luis Tapia, Jason Smoke
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Publication number: 20200018172Abstract: An airfoil includes a leading edge and an opposing trailing edge. The airfoil includes a pressure sidewall and an opposing suction sidewall. A leading edge cavity is defined between the pressure sidewall and the suction sidewall. The leading edge cavity has a first end opposite the leading edge and a second end defined at a rib. The airfoil includes at least one pin structure defined in the leading edge cavity between the first end and the second end. The at least one pin structure includes a main body and a first branch. The main body is coupled to the second end and extends toward the first end. The first branch extends from the main body toward the first end.Type: ApplicationFiled: July 13, 2018Publication date: January 16, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Luis Tapia, Jason Smoke
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Publication number: 20200011186Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.Type: ApplicationFiled: August 29, 2019Publication date: January 9, 2020Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jeff Howe, Luis Tapia
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Patent number: 10113433Abstract: An engine component includes a body having an internal surface and an external surface, the internal surface at least partially defining an internal cooling circuit. The engine component further includes a plurality of cooling holes formed in the body and extending between the internal cooling circuit and the external surface of the body. The plurality of cooling holes includes a first cooling hole with forward diffusion and lateral diffusion.Type: GrantFiled: October 4, 2012Date of Patent: October 30, 2018Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Mark C. Morris, David Waldman, Malak Fouad Malak, Luis Tapia
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Publication number: 20180073368Abstract: A method of manufacturing a cooled gas turbine component includes forming a core with an outer surface. The outer surface includes a core feature. The method also includes casting an outer wall of an airfoil about the core. The outer wall has an exterior surface and an interior surface. The interior surface includes a shaped inlet portion that corresponds to the core feature. Moreover, the method includes forming an outlet portion through the outer wall to fluidly connect the outlet portion to the shaped inlet portion. The shaped inlet portion and the outlet portion cooperatively define a cooling aperture through the outer wall.Type: ApplicationFiled: September 15, 2016Publication date: March 15, 2018Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Jeff Howe, Luis Tapia
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Patent number: 9777575Abstract: The turbine rotor blade includes a platform with a first side and a second side; an airfoil extending from the first side of the platform; and an attachment portion extending from the second side of the platform. The attachment portion includes first and second side surfaces and a base surface on an underside of the attachment portion between the first and second side surface. The base surface includes at least one curved segment or angled segment.Type: GrantFiled: January 20, 2014Date of Patent: October 3, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Luis Tapia, Steve Halfmann, Stuart Andrew Harman
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Patent number: 9650900Abstract: An engine component includes a body; and a plurality of cooling holes formed in the body, at least one of the cooling holes having a multi-lobed shape with at least a first lobe, a second lobe, and a third lobe.Type: GrantFiled: May 7, 2012Date of Patent: May 16, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Malak Fouad Malak, Rajiv Rana, Luis Tapia, David Chou, Jong Liu
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Patent number: 9562437Abstract: Turbine blade airfoils, film cooling systems thereof, and methods for forming improved film cooled components are provided. The turbine blade airfoil has an external wall surface and comprises leading and trailing edges, pressure and suction sidewalls both extending between the leading and the trailing edges, an internal cavity, one or more isolation trenches in the external wall surface, a plurality of film cooling holes arranged in cooling rows, and a plurality of span-wise surface connectors interconnecting the outlets of the film cooling holes in the same cooling row to form a plurality of rows of interconnected film cooling holes. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto the external wall surface. The span-wise surface connectors in at least one selected row of interconnected film cooling holes are disposed in the one or more isolation trenches.Type: GrantFiled: April 26, 2013Date of Patent: February 7, 2017Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Vighneswara Rao Kollati, Balamurugan Srinivasan, Jong Liu, Daniel C. Crites, Luis Tapia, Malak Fouad Malak, Rajiv Rana
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Patent number: 9228440Abstract: Turbine blade airfoils, showerhead film cooling systems thereof, and methods for cooling the turbine blade airfoils using the same are provided. The airfoil has a leading edge and a trailing edge, a pressure sidewall and a suction sidewall both extending between the leading and the trailing edges, and an internal cavity for supplying cooling air. A showerhead of film cooling holes is connected to the internal cavity. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto an external wall surface at the leading edge of the airfoil. A plurality of surface connectors is formed in the external wall surface. Each surface connector of the plurality of surface connectors interconnects the outlets of at least one selected pair of the film cooling holes.Type: GrantFiled: December 3, 2012Date of Patent: January 5, 2016Assignee: HONEYWELL INTERNATIONAL INC.Inventors: Vighneswara Rao Kollati, Balamurugan Srinivasan, Jong Liu, Daniel Cregg Crites, Luis Tapia, Malak Fouad Malak, Rajiv Rana
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Publication number: 20150204194Abstract: The turbine rotor blade includes a platform with a first side and a second side; an airfoil extending from the first side of the platform; and an attachment portion extending from the second side of the platform. The attachment portion includes first and second side surfaces and a base surface on an underside of the attachment portion between the first and second side surface. The base surface includes at least one curved segment or angled segment.Type: ApplicationFiled: January 20, 2014Publication date: July 23, 2015Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Luis Tapia, Steve Halfmann, Stuart Andrew Harman
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Publication number: 20140154096Abstract: Turbine blade airfoils, showerhead film cooling systems thereof, and methods for cooling the turbine blade airfoils using the same are provided. The airfoil has a leading edge and a trailing edge, a pressure sidewall and a suction sidewall both extending between the leading and the trailing edges, and an internal cavity for supplying cooling air. A showerhead of film cooling holes is connected to the internal cavity. Each film cooling hole has an inlet connected to the internal cavity and an outlet opening onto an external wall surface at the leading edge of the airfoil. A plurality of surface connectors is formed in the external wall surface. Each surface connector of the plurality of surface connectors interconnects the outlets of at least one selected pair of the film cooling holes.Type: ApplicationFiled: December 3, 2012Publication date: June 5, 2014Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Vighneswara Rao Kollati, Balamurugan Srinivasan, Jong Liu, Daniel Cregg Crites, Luis Tapia, Malak Fouad Malak, Rajiv Rana
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Patent number: 8628293Abstract: An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface to the exterior surface; and a concave trench extending from the cooling hole at the exterior surface of the body in a downstream direction.Type: GrantFiled: June 17, 2010Date of Patent: January 14, 2014Assignee: Honeywell International Inc.Inventors: Dhinagaran Ramachandran, Gopal Samy Muthiah, Jyothishkumar Venkataramanan, Balamurugan Srinivasan, Jong Liu, Luis Tapia, Daniel Cregg Crites, Malak Fouad Malak
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Publication number: 20130315710Abstract: An engine component includes a body having an interior surface and an exterior surface; a cooling hole formed in the body and extending from the interior surface; and a nonconcave trench extending from the cooling hole to the exterior surface of the body in a downstream direction such that cooling air flow from within the body flow through the cooling hole, through the trench, and onto the exterior surface.Type: ApplicationFiled: May 22, 2012Publication date: November 28, 2013Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Vighneswara Rao Kollati, Balamurugan Srinivasan, Jyothishkumar Venkataramanan, Sujatha Guntu, Jong Liu, Daniel Cregg Crites, Luis Tapia, Malak Fouad Malak
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Publication number: 20130294889Abstract: An engine component includes a body; and a plurality of cooling holes formed in the body, at least one of the cooling holes having a multi-lobed shape with at least a first lobe, a second lobe, and a third lobe.Type: ApplicationFiled: May 7, 2012Publication date: November 7, 2013Applicant: HONEYWELL INTERNATIONAL INC.Inventors: Malak Fouad Malak, Rajiv Rana, Luis Tapia, David Chou, Jong Liu
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Patent number: 8529193Abstract: An engine component includes a body; and a plurality of cooling holes formed in the body. At least one of the cooling holes has cross-sectional shape with a first concave portion and a first convex portion.Type: GrantFiled: November 25, 2009Date of Patent: September 10, 2013Assignee: Honeywell International Inc.Inventors: Jyothishkumar Venkataramanan, Gopal Samy Muthiah, Dhinagaran Ramachandran, Balamurugan Srinivasan, Malak Fouad Malak, Jong Liu, Luis Tapia, Daniel Crites
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Patent number: 8444387Abstract: A seal plate for directing an airflow includes a hub, main pumping vanes, and splitter vanes. The hub has a tubular section and an annular flange section flared outwardly relative to the tubular section to define a flow surface. The main pumping vanes are disposed circumferentially on the flow surface around the annular flange section and each has a canted section located radially inward relative to a straight section and aligned with a flow direction of the airflow. The straight section extends along a first plane including a centerline of the seal plate. The splitter vanes are disposed circumferentially on the flow surface around the annular flange section such that at least one splitter vane is disposed between the straight sections of two adjacent main pumping vanes. Each splitter vane has a length that is less than a length of each of the two adjacent main pumping vanes.Type: GrantFiled: November 20, 2009Date of Patent: May 21, 2013Assignee: Honeywell International Inc.Inventors: Mark C. Morris, Larry Barr, Paul Couey, Stuart Andrew Harman, Douglas L. Ramerth, Luis A. Tapia