Patents by Inventor Daniel C. Nadeau
Daniel C. Nadeau 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: 10428666Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.Type: GrantFiled: December 12, 2016Date of Patent: October 1, 2019Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: John David Forbes, Gregory Anselmi, Christina E. Botnick, Eleanor D. Kaufman, Jeffrey Leon, Jeffrey R. Levine, Gerald M. Mace, Daniel C. Nadeau, Tania Bhatia Kashyap, Richard N. Allen
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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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Patent number: 10132168Abstract: An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.Type: GrantFiled: March 14, 2016Date of Patent: November 20, 2018Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Jeffrey Leon, Daniel C. Nadeau, Jeffrey R. Levine, Eleanor D. Kaufman, Richard N. Allen, Evan P. Molony, Gregory Anselmi
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Publication number: 20180163551Abstract: A turbine vane includes an inner platform and an outer platform joined together by an airfoil. The airfoil has a leading edge and a trailing edge joined together by a pressure side and a suction side disposed opposite the pressure side. The inner platform defines a plurality of first inner cooling holes and a plurality of second inner cooling holes that are fluidly connected to an inner cooling passage. The plurality of first inner cooling holes are disposed proximate the leading edge and extend towards the suction side and the plurality of second inner cooling holes are disposed proximate the trailing edge and the suction side and extend towards the leading edge.Type: ApplicationFiled: December 12, 2016Publication date: June 14, 2018Inventors: John David Forbes, Gregory Anselmi, Christina E. Botnick, Eleanor D. Kaufman, Jeffrey Leon, Jeffrey R. Levine, Gerald M. Mace, Daniel C. Nadeau, Tania Bhatia Kashyap, Richard N. Allen
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Publication number: 20170260864Abstract: An airfoil is disclosed, comprising an airfoil body and an internal cavity within the airfoil body. The internal cavity may comprise an outer edge comprising a first outer scallop and a second outer scallop, an inner edge opposite the outer edge, the inner edge comprising a first inner scallop and a second inner scallop, a leading edge spanning between the outer edge and the inner edge, and a trailing edge spanning between the outer edge and the inner edge and opposite the leading edge. Between the outer edge, the inner edge, the leading edge, and the trailing edge, the internal cavity may comprise eight columns of pedestals disposed axially relative to one another and axially between the leading edge and the trailing edge.Type: ApplicationFiled: March 14, 2016Publication date: September 14, 2017Applicant: United Technologies CorporationInventors: Jeffrey Leon, Daniel C. Nadeau, Jeffrey R. Levine, Eleanor D. Kaufman, Richard N. Allen, Evan P. Molony, Gregory Anselmi
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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: 20160333699Abstract: An airfoil for a gas turbine engine includes pressure and suction surfaces that are provided by pressure and suction walls extending in a radial direction and joined at a leading edge and a trailing edge. A cooling passage is arranged between the pressure and suction walls and extending to the trailing edge. The cooling passage terminates in a trailing edge exit that is arranged in the trailing edge. Multiple rows of pedestals include a first row of pedestals that join the pressure and suction walls. The first row of pedestals is arranged closest to the trailing edge but interiorly from the trailing edge thereby leaving the trailing edge exit unobstructed.Type: ApplicationFiled: December 26, 2014Publication date: November 17, 2016Inventors: James B. Downey, JR., Brenda Zhang, Steven G. Lemieux, Eleanor D. Kaufman, Takao Fukuda, Daniel C. Nadeau
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Patent number: 9157329Abstract: An airfoil for a gas turbine engine includes spaced apart pressure and suction walls joined at leading and trailing edges to provide an airfoil. Intermediate walls interconnect the pressure and suction walls to provide cooling passageways. The cooing passageways have interior pressure and suction surfaces that are respectively provided on the pressure and suction walls. Trip strips include a chevron-shaped trip strip that is provided on at least one of the interior pressure and suction surfaces.Type: GrantFiled: August 22, 2012Date of Patent: October 13, 2015Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Daniel C. Nadeau, Jeffrey R. Levine, Dominic J. Mongillo, Jr.
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Publication number: 20140056717Abstract: An airfoil for a gas turbine engine includes spaced apart pressure and suction walls joined at leading and trailing edges to provide an airfoil. Intermediate walls interconnect the pressure and suction walls to provide cooling passageways. The cooing passageways have interior pressure and suction surfaces that are respectively provided on the pressure and suction walls. Trip strips include a chevron-shaped trip strip that is provided on at least one of the interior pressure and suction surfaces.Type: ApplicationFiled: August 22, 2012Publication date: February 27, 2014Inventors: Daniel C. Nadeau, Jeffrey R. Levine, Dominic J. Mongillo, JR.