Patents by Inventor Brandon Phillip Williams
Brandon Phillip Williams 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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Publication number: 20220195920Abstract: An embodiment of a torch ignitor system for combustor of a gas turbine engine includes a torch ignitor, the torch ignitor having a combustion chamber oriented about an axis, the combustion chamber having axially upstream and downstream ends defining a flow direction through the combustion chamber, along the axis. The torch ignitor system also includes a cap defining the axially upstream end of the combustion chamber and oriented about the axis, wherein the cap is configured to receive a fuel injector and at least one glow plug, a tip at a downstream end of the combustion chamber, and a passage for pressurized oxygen containing gas passing through the cap from an exterior of the combustion chamber and in fluid communication with the combustion chamber. An embodiment of a method for starting a gas turbine engine is also disclosed.Type: ApplicationFiled: December 23, 2020Publication date: June 23, 2022Applicant: Delavan Inc.Inventors: Jason Ryon, Brandon Phillip Williams
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Patent number: 11253823Abstract: A nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer air flow path, and a core conduit defined radially inward from the inner gas flow path. An injector assembly includes an outer housing, a nozzle within the outer housing, and an outer housing gas flow path defined radially outward from the nozzle between an inner surface of the outer housing and an outer surface of the nozzle. The nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer gas flow path and a core conduit defined radially inward from the inner gas flow path.Type: GrantFiled: March 29, 2019Date of Patent: February 22, 2022Assignee: Delavan Inc.Inventors: Jason Ryon, Philip E. O. Buelow, Lev Alexander Prociw, Brandon Phillip Williams
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Patent number: 11014054Abstract: A fluid-gas mixer including a housing, defining a primary axis, for mixing fluid and gas, a mixer nozzle circumscribing the primary axis, wherein an annular gap between an outer surface of the mixer nozzle and an inner surface of the housing defines at least one outer gas path, a swirling gas passage defining an inner gas path for mixing with the outer gas path.Type: GrantFiled: April 17, 2019Date of Patent: May 25, 2021Assignee: Delavan Inc.Inventors: Lev Alexander Prociw, Jason Ryon, Philip E. O. Buelow, Brandon Phillip Williams
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Publication number: 20200332998Abstract: A fluid-gas mixer including a housing, defining a primary axis, for mixing fluid and gas, a mixer nozzle circumscribing the primary axis, wherein an annular gap between an outer surface of the mixer nozzle and an inner surface of the housing defines at least one outer gas path, a swirling gas passage defining an inner gas path for mixing with the outer gas path.Type: ApplicationFiled: April 17, 2019Publication date: October 22, 2020Inventors: Lev Alexander Prociw, Jason Ryon, Philip E. O. Buelow, Brandon Phillip Williams
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Publication number: 20200306703Abstract: A nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer air flow path, and a core conduit defined radially inward from the inner gas flow path. An injector assembly includes an outer housing, a nozzle within the outer housing, and an outer housing gas flow path defined radially outward from the nozzle between an inner surface of the outer housing and an outer surface of the nozzle. The nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer gas flow path and a core conduit defined radially inward from the inner gas flow path.Type: ApplicationFiled: March 29, 2019Publication date: October 1, 2020Inventors: Jason Ryon, Philip E. O. Buelow, Lev Alexander Prociw, Brandon Phillip Williams
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Publication number: 20200309376Abstract: A nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer gas flow path, and a core conduit defined radially inward from the inner gas flow path. An injector assembly includes an outer housing, a nozzle within the outer housing, and an outer housing gas flow path defined radially outward from the nozzle between an inner surface of the outer housing and an outer surface of the nozzle. The nozzle includes an outer gas flow path, an inner gas flow path radially inward from the outer gas flow path, a liquid flow path defined radially between the inner gas flow path and the outer gas flow path and a core conduit defined radially inward from the inner gas flow path.Type: ApplicationFiled: March 29, 2019Publication date: October 1, 2020Inventors: Lev Alexander Prociw, Jason Ryon, Philip E. O. Buelow, Brandon Phillip Williams
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Publication number: 20200224876Abstract: A fuel injector for a gas turbine engine includes a fuel inlet fitting for receiving fuel, with a feed arm mounted to the inlet. The feed arm has a lattice support structure. The lattice support structure may include a plurality of three-dimensional elements, a first conduit, and a second conduit in fluid communication with the inlet for conveying fuel from the inlet fitting through the feed arm, wherein the conduits are intertwined with each other, and a nozzle body operatively connected to the feed arm for injecting fuel from the conduits into a combustor of the gas turbine engine.Type: ApplicationFiled: January 15, 2019Publication date: July 16, 2020Inventors: Jacob Greenfield, Brandon Phillip Williams
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Patent number: 9989187Abstract: A strain reliever for a hollow tube is disclosed. The strain reliever has a fitting dimensioned to fit at a tube segment and a tapered sleeve extending from the fitting. The tapered sleeve is configured to surround the tube segment and to provide relief of strain imposed by forces exerted on the tube. Strain relievers having helical conic and slotted tapered sleeves are also described.Type: GrantFiled: June 10, 2013Date of Patent: June 5, 2018Assignee: Delavan Inc.Inventors: Randy Siders, Brandon Phillip Williams, David H. Bretz
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Patent number: 9429074Abstract: A fuel nozzle for a gas turbine engine includes a nozzle body having a longitudinal axis. An elongated annular air passage is defined within the nozzle body. A plurality of circumferentially spaced apart axially extending swirl vanes is disposed within the annular air passage. Each swirl vane has an axially swept cross-sectional profile along the radial extent thereof.Type: GrantFiled: July 10, 2009Date of Patent: August 30, 2016Assignee: Rolls-Royce plcInventors: Brandon Phillip Williams, Kevin Eugene Thompson
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Patent number: 9046039Abstract: An injector includes a main nozzle body defining a central axis and having a main fuel circuit. A pilot nozzle body is mounted inboard of the main nozzle body. The pilot nozzle body includes a pilot air circuit on the central axis with fuel circuitry radially outboard of the pilot air circuit for delivering fuel to a fuel outlet in a downstream portion of the pilot nozzle body. The fuel circuitry includes a primary pilot fuel circuit configured and adapted to deliver fuel to the fuel outlet and a secondary pilot fuel circuit configured and adapted to deliver fuel to the same fuel outlet.Type: GrantFiled: November 9, 2011Date of Patent: June 2, 2015Assignee: Rolls-Royce plcInventors: Brandon Phillip Williams, Viraphand Cholvibul, David H. Bretz
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Publication number: 20140361531Abstract: A strain reliever for a hollow tube is disclosed. The strain reliever has a fitting dimensioned to fit at a tube segment and a tapered sleeve extending from the fitting. The tapered sleeve is configured to surround the tube segment and to provide relief of strain imposed by forces exerted on the tube. Strain relievers having helical conic and slotted tapered sleeves are also described.Type: ApplicationFiled: June 10, 2013Publication date: December 11, 2014Applicant: DELAVAN INCInventors: Randall D. Siders, Brandon Phillip Williams, David H. Bretz
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Patent number: 8483931Abstract: A method of actively controlling pattern factor in a gas turbine engine includes the steps of issuing fuel into a combustion chamber of a gas turbine engine through one or more circumferentially disposed fuel injectors, determining an initial circumferential pattern factor in the combustion chamber, and adjusting fuel flow through one or more selected fuel injectors based on the initial circumferential pattern factor, to yield a modified circumferential pattern factor in the combustion chamber. The step of determining the circumferential pattern factor can include the steps of detecting a chemiluminescent signature within the combustor, correlating the chemiluminescent signature to an equivalence ratio, and computing the initial circumferential pattern factor based on the equivalence ratio.Type: GrantFiled: May 22, 2012Date of Patent: July 9, 2013Assignee: Delavan Inc.Inventors: Brandon Phillip Williams, Jerry Lee Goeke
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Patent number: 8443608Abstract: A feed arm for a multiple circuit fuel injector of a gas turbine engine. The feed arm includes an elongated tubular sleeve having a central bore with an interior wall defining an inner diameter, and an elongated fuel tube positioned within the bore of the tubular sleeve. The fuel tube includes a tubular wall defining an outer diameter, which is substantially equal to the inner diameter of the central bore. A primary fuel flow passage is formed within the tubular wall of the fuel tube and bounded by the interior wall of the tubular sleeve, and the primary fuel flow passage circumferentially extends around the fuel tube at least once along the axial length of the fuel tube. A secondary fuel flow passage extends through a central portion of the fuel tube, and the fuel tube is configured to facilitate heat transfer by conduction and/or convection.Type: GrantFiled: February 26, 2008Date of Patent: May 21, 2013Assignee: Delavan IncInventor: Brandon Phillip Williams
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Patent number: 8417434Abstract: A method of actively controlling pattern factor in a gas turbine engine includes the steps of issuing fuel into a combustion chamber of a gas turbine engine through one or more circumferentially disposed fuel injectors, determining an initial circumferential pattern factor in the combustion chamber, and adjusting fuel flow through one or more selected fuel injectors based on the initial circumferential pattern factor, to yield a modified circumferential pattern factor in the combustion chamber. The step of determining the circumferential pattern factor can include the steps of detecting a chemiluminescent signature within the combustor, correlating the chemiluminescent signature to an equivalence ratio, and computing the initial circumferential pattern factor based on the equivalence ratio.Type: GrantFiled: May 22, 2012Date of Patent: April 9, 2013Assignee: Delavan IncInventors: Brandon Phillip Williams, Jerry Lee Goeke
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Patent number: 8387400Abstract: Methods of managing fuel temperatures in fuel injectors for gas turbine engines include cooling fuel circuits by initiating fuel flow therethrough using opened, closed, and semi-open control techniques. A fuel injector for a gas turbine engine includes a feed arm having a fuel inlet fitting for delivering fuel to at least one fuel conduit extending through the feed arm. A nozzle body depends from the feed arm and has at least one fuel circuit extending therethrough. The fuel circuit is configured and adapted to receive fuel from the feed arm and to issue fuel from an exit orifice of the nozzle body. Sensing means are provided adjacent to the at least one fuel circuit. The sensing means are configured and adapted to provide temperature feedback in order to control fuel flow in the at least one fuel circuit to maintain fuel temperature within a predetermined range.Type: GrantFiled: January 12, 2012Date of Patent: March 5, 2013Assignee: Delavan IncInventors: Jerry Lee Goeke, Neal A. Thomson, Brandon Phillip Williams
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Publication number: 20120117972Abstract: Methods of managing fuel temperatures in fuel injectors for gas turbine engines include cooling fuel circuits by initiating fuel flow therethrough using opened, closed, and semi-open control techniques. A fuel injector for a gas turbine engine includes a feed arm having a fuel inlet fitting for delivering fuel to at least one fuel conduit extending through the feed arm. A nozzle body depends from the feed arm and has at least one fuel circuit extending therethrough. The fuel circuit is configured and adapted to receive fuel from the feed arm and to issue fuel from an exit orifice of the nozzle body. Sensing means are provided adjacent to the at least one fuel circuit. The sensing means are configured and adapted to provide temperature feedback in order to control fuel flow in the at least one fuel circuit to maintain fuel temperature within a predetermined range.Type: ApplicationFiled: January 12, 2012Publication date: May 17, 2012Applicant: Delavan Inc.Inventors: Jerry L. Goeke, Neal A. Thomson, Brandon Phillip Williams
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Publication number: 20110005232Abstract: A fuel nozzle for a gas turbine engine includes a nozzle body having a longitudinal axis. An elongated annular air passage is defined within the nozzle body. A plurality of circumferentially spaced apart axially extending swirl vanes is disposed within the annular air passage. Each swirl vane has an axially swept cross-sectional profile along the radial extent thereof.Type: ApplicationFiled: July 10, 2009Publication date: January 13, 2011Applicant: Delavan IncInventors: Brandon Phillip Williams, Kevin Eugene Thompson