Patents by Inventor William Thomas Bennett
William Thomas Bennett 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: 10995954Abstract: A combustor for a gas turbine engine comprising a combustion liner defining a combustion chamber, wherein the combustion liner has at least one opening into which a combustor liner mount is received. The combustor liner mount can have at least one cooling passage defined therein having an inlet defining an inlet axis and an outlet defining an outlet axis, wherein the inlet axis is not collinear with the outlet axis for providing enhanced cooling to at least one of the combustor liner mount and an adjacent combustion component, such as an igniter or a borescope plug.Type: GrantFiled: October 25, 2018Date of Patent: May 4, 2021Assignee: General Electric CompanyInventors: Craig Alan Gonyou, William Thomas Bennett
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Patent number: 10738707Abstract: A gas turbine engine includes a combustion section space between a compressor section in a turbine section. The combustion section defines a combustion chamber and includes a combustor member defining an opening to the combustion chamber. A mounting assembly extends around or is positioned adjacent to the opening defined by the combustor member. In igniter extends through a ferrule of the mounting assembly and includes a distal end positioned proximate the opening in the combustor member. The igniter defines a plurality of channels each channel extending between a first end and a second end. The first end is positioned away from the distal end of the igniter relative to the second end, and the second end is a terminal end spaced from the distal end of the igniter.Type: GrantFiled: November 9, 2015Date of Patent: August 11, 2020Assignee: General Electric CompanyInventors: William Thomas Bennett, Kevin Samuel Klasing, Craig Alan Gonyou
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Patent number: 10724740Abstract: The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. At least one sidewall defines an impingement fluid outlet, and the aft body defines an impingement fluid cavity in fluid communication with the impingement fluid outlet.Type: GrantFiled: November 4, 2016Date of Patent: July 28, 2020Assignee: General Electric CompanyInventors: Gregory Allen Boardman, Marco Venturato, Douglas Downey Turner, Valeria Proano Cadena, William Thomas Bennett
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Patent number: 10634353Abstract: The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. The forward wall defines at least one channel inlet orifice. At least one sidewall defines at least one channel outlet orifice. At least one micro channel cooling circuit is defined between the one or more channel inlet orifices and the one or more channel outlet orifices.Type: GrantFiled: January 12, 2017Date of Patent: April 28, 2020Assignee: General Electric CompanyInventors: William Thomas Bennett, Jared Peter Buhler, Craig Alan Gonyou
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Publication number: 20190154260Abstract: A combustor for a gas turbine engine comprising a combustion liner defining a combustion chamber, wherein the combustion liner has at least one opening into which a combustor liner mount is received. The combustor liner mount can have at least one cooling passage defined therein having an inlet defining an inlet axis and an outlet defining an outlet axis, wherein the inlet axis is not collinear with the outlet axis for providing enhanced cooling to at least one of the combustor liner mount and an adjacent combustion component, such as an igniter or a borescope plug.Type: ApplicationFiled: October 25, 2018Publication date: May 23, 2019Inventors: Craig Alan Gonyou, William Thomas Bennett
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Patent number: 10145559Abstract: A combustor for a gas turbine engine comprising a combustion liner defining a combustion chamber, wherein the combustion liner has at least one opening into which a combustor liner mount is received. The combustor liner mount can have at least one cooling passage defined therein having an inlet defining an inlet axis and an outlet defining an outlet axis, wherein the inlet axis is not collinear with the outlet axis for providing enhanced cooling to at least one of the combustor liner mount and an adjacent combustion component, such as an igniter or a borescope plug.Type: GrantFiled: December 15, 2015Date of Patent: December 4, 2018Assignee: General Electric CompanyInventors: Craig Alan Gonyou, William Thomas Bennett
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Publication number: 20180195725Abstract: The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. The forward wall defines at least one channel inlet orifice. At least one sidewall defines at least one channel outlet orifice. At least one micro channel cooling circuit is defined between the one or more channel inlet orifices and the one or more channel outlet orifices.Type: ApplicationFiled: January 12, 2017Publication date: July 12, 2018Inventors: William Thomas Bennett, Jared Peter Buhler, Craig Alan Gonyou
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Publication number: 20180128488Abstract: The present disclosure is directed to a fuel nozzle for a gas turbine engine, the fuel nozzle defining a radial direction, a longitudinal direction, a circumferential direction, an upstream end, and a downstream end. The fuel nozzle includes an aft body coupled to at least one fuel injector. The aft body defines a forward wall and an aft wall each extended in the radial direction, and a plurality of sidewalls extended in the longitudinal direction. The plurality of sidewalls couples the forward wall and the aft wall. At least one sidewall defines an impingement fluid outlet, and the aft body defines an impingement fluid cavity in fluid communication with the impingement fluid outlet.Type: ApplicationFiled: November 4, 2016Publication date: May 10, 2018Inventors: Gregory Allen Boardman, Marco Venturato, Douglas Downey Turner, Valeria Proano Cadena, William Thomas Bennett
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Publication number: 20170261208Abstract: A substrate having one or more shaped effusion cooling holes formed therein. Each shaped cooling hole has a bore angled relative to an exit surface of the combustor liner. One end of the bore is an inlet formed in an inlet surface of the combustor liner. The other end of the bore is an outlet formed in the exit surface of the combustor liner. The outlet has a shaped portion that expands in only one dimension. Also methods for making the shaped cooling holes.Type: ApplicationFiled: May 26, 2017Publication date: September 14, 2017Inventors: John Howard Starkweather, William Thomas Bennett, John Franklin Gibbons, Anthony Stephen Urbanski
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Publication number: 20170191664Abstract: A combustor for a gas turbine engine comprises a liner having a forward opening and an aft opening. A deflector closes the forward opening and the aft opening is in fluid communication with a turbine section downstream of the combustor. A dome disposed in the deflector provides a fuel/air mixture to be ignited to drive the turbine section. A gap can be disposed between the deflector and the liner, having film holes disposed in the deflector for providing a flow of cool air to the gap for cooling the combustion liner downstream of the gap.Type: ApplicationFiled: January 5, 2016Publication date: July 6, 2017Inventor: William Thomas Bennett
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Publication number: 20170167728Abstract: A combustor for a gas turbine engine comprising a combustion liner defining a combustion chamber, wherein the combustion liner has at least one opening into which a combustor liner mount is received. The combustor liner mount can have at least one cooling passage defined therein having an inlet defining an inlet axis and an outlet defining an outlet axis, wherein the inlet axis is not collinear with the outlet axis for providing enhanced cooling to at least one of the combustor liner mount and an adjacent combustion component, such as an igniter or a borescope plug.Type: ApplicationFiled: December 15, 2015Publication date: June 15, 2017Inventors: Craig Alan Gonyou, William Thomas Bennett
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Publication number: 20170130653Abstract: A gas turbine engine includes a combustion section space between a compressor section in a turbine section. The combustion section defines a combustion chamber and includes a combustor member defining an opening to the combustion chamber. A mounting assembly extends around or is positioned adjacent to the opening defined by the combustor member. In igniter extends through a ferrule of the mounting assembly and includes a distal end positioned proximate the opening in the combustor member. The igniter defines a plurality of channels each channel extending between a first end and a second end. The first end is positioned away from the distal end of the igniter relative to the second end, and the second end is a terminal end spaced from the distal end of the igniter.Type: ApplicationFiled: November 9, 2015Publication date: May 11, 2017Inventors: William Thomas Bennett, Kevin Samuel Klasing, Craig Alan Gonyou
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Publication number: 20170101894Abstract: An engine component assembly is provided for impingement cooling including discrete cooling features. An insert is located opposite and adjacent to a cooled surface of the engine component and includes a plurality of angled impingement air holes. A cooling fluid flow path is flowing on one side the cooled surface of the engine component and adjacent to the insert and passes through the angled cooling holes of the insert in order to cool the cooled surface of the engine component. Additionally, a plurality of discrete cooling features may be located along the cooled surface of the engine component opposite the plurality of cooling holes in the insert.Type: ApplicationFiled: May 27, 2015Publication date: April 13, 2017Inventors: Phebe Helena PREETHI, William Thomas BENNETT, John Howard STARKWEATHER, Timothy Deryck STONE
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Patent number: 7287484Abstract: A method and a system are provided for the safe berthing of marine vessels in the high seas and other unprotected open waters. The invention allows a large vessel to be berthed alongside in close enough proximity to a marine structure so that conventional loading arm equipment may be used to load and unload the vessel under most environmental conditions. One or more floating dolphins moored to the bottom of the sea and provided with fendering means are used for berthing the vessel alongside to the marine structure. The preferred type of floating dolphin is a triangular semi-submersible moored buoyant structure comprising three buoyant column members, or “caissons”, arranged invertical fashion, three buoyant hull segments, or “pontoons”, that support and separate the column members and provide heave damping to the moored buoyant structure, and three horizontal bracing members that retain the tops of the column members in place.Type: GrantFiled: April 29, 2004Date of Patent: October 30, 2007Inventors: David Charles Landry, William Thomas Bennett, Jr.
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Publication number: 20040216485Abstract: A method and a system are provided for the safe berthing of marine vessels in the high seas and other unprotected open waters. The invention allows a large vessel to be berthed alongside in close enough proximity to a marine structure that conventional loading arm equipment may be used to load and unload the vessel under most environmental conditions. One or more floating dolphins moored to the bottom of the sea and provided with fendering means are used for berthing the vessel alongside to the marine structure. The preferred type of floating dolphin is a triangular semi-submersible moored buoyant structure comprising three buoyant column members, or “caissons”, arranged in vertical fashion, three buoyant hull segments, or “pontoons”, that support and separate the column members and provide heave damping to the moored buoyant structure, and three horizontal bracing members that retain the tops of the column members in place.Type: ApplicationFiled: April 29, 2004Publication date: November 4, 2004Inventors: David Charles Landry, William Thomas Bennett