Patents by Inventor Brandon S. Donnell
Brandon S. Donnell 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: 11085305Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.Type: GrantFiled: May 17, 2019Date of Patent: August 10, 2021Assignee: Raytheon Technologies CorporationInventors: Steven Taffet, Brandon S. Donnell, Daniel C. Nadeau, Russell Deibel, San Quach
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Publication number: 20200291790Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.Type: ApplicationFiled: May 17, 2019Publication date: September 17, 2020Inventors: Steven Taffet, Brandon S. Donnell, Daniel C. Nadeau, Russell Deibel, San Quach
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Patent number: 10626730Abstract: In a featured embodiment, a gas turbine engine component comprises an airfoil having a leading edge, a trailing edge, and pressure and suction side walls extending from the leading edge to the trailing edge. The airfoil extends from a base to a tip. A shelf is formed in the tip, and extends from the pressure side wall, around the leading edge, to the suction side wall.Type: GrantFiled: November 5, 2014Date of Patent: April 21, 2020Assignee: United Technologies CorporationInventors: James T. Auxier, Thomas N. Slavens, Brandon S. Donnell, Yafet Girma
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Patent number: 10370980Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.Type: GrantFiled: November 20, 2014Date of Patent: August 6, 2019Assignee: United Technologies CorporationInventors: Steven Taffet, Brandon S. Donnell, Daniel C. Nadeau, Russell Deibel, San Quach
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Publication number: 20190099810Abstract: A method includes (a) depositing a layer (224) of a powder material (216) on a work stage (226), the layer (224) having a thickness, (b) solidifying a portion of the layer (224) based upon data that defines an insert (228) with a body that is shaped to fit into a cavity in a gas turbine engine component, and (c) lowering the work stage (226) by the thickness. Steps (a)-(c) can then be repeated until the insert (228) is complete. The insert (228) can then be removed from the work stage (226). An insert (228) formed by the above process is also disclosed.Type: ApplicationFiled: December 3, 2018Publication date: April 4, 2019Inventors: Tracy A. Propheter-Hinckley, Brandon S. Donnell
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Patent number: 10173264Abstract: A method includes (a) depositing a layer of a powder material on a work stage, the layer having a thickness, (b) solidifying a portion of the layer based upon data that defines an insert with a body that is shaped to fit into a cavity in a gas turbine engine component, and (c) lowering the work stage by the thickness. Steps (a)-(c) can then be repeated until the insert is complete. The insert can then be removed from the work stage. An insert formed by the above process is also disclosed.Type: GrantFiled: March 11, 2014Date of Patent: January 8, 2019Assignee: United Technologies CorporationInventors: Tracy A. Propheter-Hinckley, Brandon S. Donnell
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Patent number: 10125614Abstract: A component for a gas turbine engine according to an exemplary aspect of this disclosure includes a surface having a plurality of cooling holes. The surface includes a first region and a second region each having a plurality of cooling holes. The cooling holes within the first region are arranged differently than the cooling holes in the second region.Type: GrantFiled: April 17, 2015Date of Patent: November 13, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Dominic J. Mongillo, San Quach, Steven Bruce Gautschi, Brandon S. Donnell, Anita L. Tracy, Yafet Girma
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Publication number: 20170022822Abstract: A lost core mold component comprises a first leg and a second leg with a plurality of crossover members connecting the first and second legs. The plurality of crossover members includes outermost crossover members spaced from each other. Adjacent ends of each of the first and second legs, and second crossover members are spaced closer to each other than are the outermost crossover members. Central crossover members extend between the first and second leg and between the second crossover members. The outermost crossover members extend for a first cross-sectional area. The second crossover members extend for a second cross-sectional area and the central crossover members extend for a third cross-sectional area. The first cross-sectional area is greater than the second cross-sectional area. The second cross-sectional area is greater than the third cross-sectional area. A gas turbine engine and component are also disclosed.Type: ApplicationFiled: November 20, 2014Publication date: January 26, 2017Inventors: Steven Taffet, Brandon S. Donnell, Daniel C. Nadeau, Russell Deibel, San Quach
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Publication number: 20160298463Abstract: In a featured embodiment, a gas turbine engine component comprises an airfoil having a leading edge, a trailing edge, and pressure and suction side walls extending from the leading edge to the trailing edge. The airfoil extends from a base to a tip. A shelf is formed in the tip, and extends from the pressure side wall, around the leading edge, to the suction side wall.Type: ApplicationFiled: November 5, 2014Publication date: October 13, 2016Applicant: United Technologies corporationInventors: James T. Auxier, Thomas N. Slavens, Brandon S. Donnell, Yafet Girma
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Publication number: 20160023275Abstract: A method includes (a) depositing a layer of a powder material on a work stage, the layer having a thickness, (b) solidifying a portion of the layer based upon data that defines an insert with a body that is shaped to fit into a cavity in a gas turbine engine component, and (c) lowering the work stage by the thickness. Steps (a)-(c) can then be repeated until the insert is complete. The insert can then be removed from the work stage. An insert formed by the above process is also disclosed.Type: ApplicationFiled: March 11, 2014Publication date: January 28, 2016Inventors: Tracy A. Propheter-Hinckley, Brandon S. Donnell
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Publication number: 20150300258Abstract: A component for a gas turbine engine according to an exemplary aspect of this disclosure includes a surface having a plurality of cooling holes. The surface includes a first region and a second region each having a plurality of cooling holes. The cooling holes within the first region are arranged differently than the cooling holes in the second region.Type: ApplicationFiled: April 17, 2015Publication date: October 22, 2015Inventors: Dominic J. Mongillo, San Quach, Steven Bruce Gautschi, Brandon S. Donnell, Anita L. Tracy, Yafet Girma
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Patent number: 9151165Abstract: A damper body extends between an axial first end, an opposing axial second end, a first lateral side, and an opposing second lateral side. A first pair of lugs are disposed at the first axial end and a second pair of lugs are disposed at the second axial end. In the first lug pair, a lug has an axially outermost foot which extends laterally beyond a lateral wall. The second lug pair has a lug with an axial outermost point with a foot extending laterally beyond a lateral wall. The foot on the first axial end and the foot on the second axial end are on opposed lateral sides.Type: GrantFiled: October 22, 2012Date of Patent: October 6, 2015Assignee: United Technologies CorporationInventors: Brandon S. Donnell, Yafet Girma, Gina C. O'Dell
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Patent number: 9045987Abstract: An assembly for a gas turbine engine includes a first platform and an airfoil extending from the first platform. The airfoil includes a first fillet, pressure side biased discharge openings, and a first center cooling discharge opening. A pressure side wall of the airfoil and the first platform form an acute angle at the trailing edge. The first fillet is formed around a perimeter of the airfoil where the airfoil extends from the first platform. The pressure side biased cooling discharge openings are along the trailing edge outside of the first fillet. Each pressure side biased cooling discharge opening extends from the trailing edge along the pressure side wall. The first center cooling discharge opening extends along the trailing edge into the first fillet and is centrally located between the pressure side wall and the suction side wall.Type: GrantFiled: June 15, 2012Date of Patent: June 2, 2015Assignee: United Technologies CorporationInventors: Jeffrey R. Levine, Dominic J. Mongillo, Brandon S. Donnell
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Publication number: 20130336767Abstract: An assembly for a gas turbine engine includes a first platform and an airfoil extending from the first platform. The airfoil includes a first fillet, pressure side biased discharge openings, and a first center cooling discharge opening. A pressure side wall of the airfoil and the first platform form an acute angle at the trailing edge. The first fillet is formed around a perimeter of the airfoil where the airfoil extends from the first platform. The pressure side biased cooling discharge openings are along the trailing edge outside of the first fillet. Each pressure side biased cooling discharge opening extends from the trailing edge along the pressure side wall. The first center cooling discharge opening extends along the trailing edge into the first fillet and is centrally located between the pressure side wall and the suction side wall.Type: ApplicationFiled: June 15, 2012Publication date: December 19, 2013Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jeffrey R. Levine, Dominic J. Mongillo, Brandon S. Donnell
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Publication number: 20120163993Abstract: A turbine engine component includes an airfoil portion having a leading edge, a platform, a leading edge airfoil to platform fillet, and a cooling tube located within said fillet. The cooling tube has a flared entrance end and a flared exit end.Type: ApplicationFiled: December 23, 2010Publication date: June 28, 2012Applicant: UNITED TECHNOLOGIES CORPORATIONInventors: Jeffrey R. Levine, Brandon S. Donnell