Patents by Inventor Brandon P. Williams
Brandon P. 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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Patent number: 11286862Abstract: A combustor system for a gas turbine engine includes a combustor case, a combustor liner disposed within the combustor case and defining a main combustion chamber, a dome defining an upstream end of the main combustion chamber, and at least one torch injector attached to the dome of the main combustion chamber configured to inject combustion gases into the main combustion chamber. Each torch injector includes a torch injector housing defining and surrounding a torch combustion chamber configured to house a combustion reaction, an outlet passage defined by the torch injector housing, an electrothermal ignition source extending at least partially into the torch combustion chamber, and a fuel injector configured to inject fuel into the torch combustion chamber to at least partially impinge on the electrothermal ignition source and generate the combustion gases. The outlet passage directly fluidly connects the torch combustion chamber to the main combustion chamber.Type: GrantFiled: December 18, 2020Date of Patent: March 29, 2022Assignee: Delavan Inc.Inventors: Jason Ryon, Lev Alexander Prociw, Brandon P. Williams
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Patent number: 11226103Abstract: A torch ignitor system provides a continuous flame to ignite fuel within a combustor of a gas turbine engine. The torch ignitor system includes a torch ignitor, a housing, a flow channel, and an outlet nozzle. The torch ignitor system is configured to receive high-pressure air from the high-pressure compressor region of a gas turbine engine to increase operational characteristics of the torch ignitor system, including fuel atomization, cooling of the torch ignitor system, and circulation of combustion air within the torch ignitor system.Type: GrantFiled: December 16, 2020Date of Patent: January 18, 2022Assignee: Delavan Inc.Inventors: Jason Ryon, Lev Alexander Prociw, Brandon P. Williams
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Patent number: 10429071Abstract: A staged fuel injector comprises a pilot inner air swirler arranged along a centre axis of the injector, a pilot fuel swirler arranged radially outboard of the pilot inner air swirler, a main inner air swirler arranged radially outboard of the pilot fuel swirler and a main fuel swirler arranged radially outboard of the pilot fuel swirler. A fuel feed arm is arranged in fluid communication with the pilot fuel swirler and the main fuel swirler for delivering fuel to the pilot fuel swirler and the main fuel swirler and a heat protective casing enclosing the fuel feed arm, the pilot fuel swirler and the main fuel swirler.Type: GrantFiled: March 16, 2017Date of Patent: October 1, 2019Assignee: Rolls-Royce plcInventor: Brandon P. Williams
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Patent number: 10295187Abstract: A fuel nozzle for a gas turbine engine is disclosed which includes a nozzle body having a longitudinal axis, an elongated annular air passage defined within the nozzle body, and a plurality of circumferentially spaced apart axially extending swirl vanes disposed within the annular air passage, wherein each swirl vane has multiple joined leads and a variable thickness along the axial extent thereof.Type: GrantFiled: October 24, 2016Date of Patent: May 21, 2019Assignee: Rolls-Royce plcInventors: Brandon P. Williams, Kevin E. Thompson, Robert R. Fogarty
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Patent number: 10077714Abstract: A fuel injector for a lean direct injection fuel nozzle has a pilot air swirler which sits radially outboard of a pilot fuel swirler radially outer wall. The air swirler is bounded on its radially outer side by joined wall portions. One wall portion extends axially and another wall portion converges radially. On the radially inwardly facing surface, the wall portions meet to provide a continuing wall surface of the air swirler which transitions from axial extension to radial convergence over a smooth radius. The curvature of this surface broadly mirrors the radially outwardly facing profile of the pilot fuel swirler radially outer wall. The axially extending wall portion is extended axially to form a first part of a join interface. The radially converging portion is extended in a radial direction to provide a second part of the join interface.Type: GrantFiled: November 6, 2015Date of Patent: September 18, 2018Assignee: Rolls-Royce plcInventors: Randall D. Siders, Peter J. Schnoebelen, Brandon P. Williams, Neal Thomson, Philip E. O. Buelow, David H. Bretz
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Publication number: 20170284673Abstract: A staged fuel injector comprises a pilot inner air swirler arranged along a centre axis of the injector, a pilot fuel swirler arranged radially outboard of the pilot inner air swirler, a main inner air swirler arranged radially outboard of the pilot fuel swirler and a main fuel swirler arranged radially outboard of the pilot fuel swirler. A fuel feed arm is arranged in fluid communication with the pilot fuel swirler and the main fuel swirler for delivering fuel to the pilot fuel swirler and the main fuel swirler and a heat protective casing enclosing the fuel feed arm, the pilot fuel swirler and the main fuel swirler.Type: ApplicationFiled: March 16, 2017Publication date: October 5, 2017Inventor: Brandon P. Williams
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Publication number: 20170130652Abstract: A fuel injector for a lean direct injection fuel nozzle has a pilot air swirler which sits radially outboard of a pilot fuel swirler radially outer wall. The air swirler is bounded on its radially outer side by joined wall portions. One wall portion extends axially and another wall portion converges radially. On the radially inwardly facing surface, the wall portions meet to provide a continuing wall surface of the air swirler which transitions from axial extension to radial convergence over a smooth radius. The curvature of this surface broadly mirrors the radially outwardly facing profile of the pilot fuel swirler radially outer wall. The axially extending wall portion is extended axially to form a first part of a join interface. The radially converging portion is extended in a radial direction to provide a second part of the join interface.Type: ApplicationFiled: November 6, 2015Publication date: May 11, 2017Inventors: Randall D. Siders, Peter J. Schnoebelen, Brandon P. Williams, Neal Thomson, Philip E.O. Buelow, David H. Bretz
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Patent number: 9617919Abstract: A valve includes a valve housing having a fluid inlet and a fluid outlet with a longitudinal axis defined through the valve housing. The valve also includes a toggle mechanism configured and adapted to cycle flow from the fluid inlet to the fluid outlet through a plurality of different flow rates in response to repeated impulses. The toggle mechanism is also configured to hold flow rate steady between impulses.Type: GrantFiled: December 18, 2015Date of Patent: April 11, 2017Assignee: Delavan Inc.Inventors: Brandon P. Williams, Neal A. Thomson
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Publication number: 20170038072Abstract: A fuel nozzle for a gas turbine engine is disclosed which includes a nozzle body having a longitudinal axis, an elongated annular air passage defined within the nozzle body, and a plurality of circumferentially spaced apart axially extending swirl vanes disposed within the annular air passage, wherein each swirl vane has multiple joined leads and a variable thickness along the axial extent thereof.Type: ApplicationFiled: October 24, 2016Publication date: February 9, 2017Inventors: Brandon P. Williams, Kevin E. Thompson, Robert R. Fogarty
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Publication number: 20160102614Abstract: A valve includes a valve housing having a fluid inlet and a fluid outlet with a longitudinal axis defined through the valve housing. The valve also includes a toggle mechanism configured and adapted to cycle flow from the fluid inlet to the fluid outlet through a plurality of different flow rates in response to repeated impulses. The toggle mechanism is also configured to hold flow rate steady between impulses.Type: ApplicationFiled: December 18, 2015Publication date: April 14, 2016Inventors: Brandon P. Williams, Neal A. Thomson
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Patent number: 9239167Abstract: A fuel injector for a gas turbine engine includes a nozzle body defining a central axis and having a main fuel circuit. An air circuit is formed within the nozzle body inboard of the main fuel circuit. A primary pilot fuel circuit is formed within the nozzle body inboard of the air circuit. A secondary pilot fuel circuit is formed within the nozzle body inboard of the air circuit and outboard of the primary pilot fuel circuit.Type: GrantFiled: October 18, 2013Date of Patent: January 19, 2016Assignee: Rolls-Royce plcInventors: Brandon P. Williams, Jeremy T. Rhyan
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Patent number: 9217511Abstract: A valve includes a valve housing having a fluid inlet and a fluid outlet with a longitudinal axis defined through the valve housing. The valve also includes a toggle mechanism configured and adapted to cycle flow from the fluid inlet to the fluid outlet through a plurality of different flow rates in response to repeated impulses. The toggle mechanism is also configured to hold flow rate steady between impulses.Type: GrantFiled: August 10, 2012Date of Patent: December 22, 2015Assignee: Delavan Inc.Inventors: Brandon P. Williams, Neal A. Thomson
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Publication number: 20140042347Abstract: A valve includes a valve housing having a fluid inlet and a fluid outlet with a longitudinal axis defined through the valve housing. The valve also includes a toggle mechanism configured and adapted to cycle flow from the fluid inlet to the fluid outlet through a plurality of different flow rates in response to repeated impulses. The toggle mechanism is also configured to hold flow rate steady between impulses.Type: ApplicationFiled: August 10, 2012Publication date: February 13, 2014Applicant: Delavan IncInventors: Brandon P. Williams, Neal A. Thomson
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Publication number: 20140041390Abstract: A fuel injector for a gas turbine engine includes a nozzle body defining a central axis and having a main fuel circuit. An air circuit is formed within the nozzle body inboard of the main fuel circuit. A primary pilot fuel circuit is formed within the nozzle body inboard of the air circuit. A secondary pilot fuel circuit is formed within the nozzle body inboard of the air circuit and outboard of the primary pilot fuel circuit.Type: ApplicationFiled: October 18, 2013Publication date: February 13, 2014Applicant: Delavan Inc.Inventors: Brandon P. Williams, Jeremy T. Rhyan
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Patent number: 8607571Abstract: A fuel injector for a gas turbine engine includes a nozzle body defining a central axis and having a main fuel circuit. An air circuit is formed within the nozzle body inboard of the main fuel circuit. A primary pilot fuel circuit is formed within the nozzle body inboard of the air circuit. A secondary pilot fuel circuit is formed within the nozzle body inboard of the air circuit and outboard of the primary pilot fuel circuit.Type: GrantFiled: September 18, 2009Date of Patent: December 17, 2013Assignee: Delavan IncInventors: Brandon P. Williams, Jeremy T. Rhyan
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Patent number: 8291707Abstract: A multi-stage check valve includes a valve housing defining an internal valve chamber. A main valve member within the valve chamber of the valve housing has an internal valve chamber. In the first position thereof the main valve member blocks fuel below a predetermined main pressure from flowing through a main fuel path. In the second position thereof the main valve member is displaced to allow fuel above the predetermined main pressure to flow through the main fuel path. The multi-stage check valve also includes a pilot valve member within the valve chamber of the main valve member. In the first position thereof, the pilot valve member blocks fuel below a predetermined pilot pressure from flowing through a pilot fuel path. In the second position thereof, the pilot valve member is displaced to allow fuel above the predetermined pilot pressure to flow through the pilot fuel path.Type: GrantFiled: August 18, 2008Date of Patent: October 23, 2012Assignee: Delavan IncInventors: Brandon P. Williams, Nathan J. James
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Publication number: 20120247119Abstract: 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: ApplicationFiled: May 22, 2012Publication date: October 4, 2012Applicant: DELAVAN INCInventors: Brandon P. Williams, Jerry L. Goeke
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Publication number: 20120227410Abstract: 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: ApplicationFiled: May 22, 2012Publication date: September 13, 2012Applicant: DELAVAN INCInventors: Brandon P. Williams, Jerry L. Goeke
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Patent number: 8200410Abstract: 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: March 12, 2008Date of Patent: June 12, 2012Assignee: Delavan IncInventors: Brandon P. Williams, Jerry L. Goeke
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Patent number: 8156746Abstract: A lean direct injection fuel nozzle for a gas turbine is disclosed which includes a radially outer main fuel delivery system including a main inner air swirler defined in part by a main inner air passage having a radially inner wall with a diverging downstream surface, an intermediate air swirler radially inward of the main inner air swirler for providing a cooling air flow along the downstream surface of the radially inner wall of the main inner air passage, and a radially inner pilot fuel delivery system radially inward of the intermediate air swirler.Type: GrantFiled: July 20, 2010Date of Patent: April 17, 2012Assignee: Delavan IncInventors: Philip E. O. Buelow, Brandon P. Williams, David H. Bretz, Michael Spooner, Caroline Mohamed, Helen Gill