Patents by Inventor Johnie Franklin McConnaughhay
Johnie Franklin McConnaughhay 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: 11920794Abstract: A bundled tube fuel nozzle is provided. The bundled tube fuel nozzle includes a first end wall, a second end wall, an outer band that extends between the first end wall and the second end wall, and an inner band that extends between the first end wall and the second end wall. The inner band is disposed within the outer band. A bellows wall is disposed between the inner band and the outer band. The bellows wall surrounds the inner band such that a first fuel plenum is defined annularly between the inner band and the bellows wall. The inner band defines a second fuel plenum that is in fluid communication with the first fuel plenum via one or more apertures defined in the inner band. A plurality of tubes extends in an axial direction between the first end wall and the second end wall within the second fuel plenum.Type: GrantFiled: December 15, 2022Date of Patent: March 5, 2024Assignee: GE Infrastructure Technology LLCInventors: Jonathan Dwight Berry, Johnie Franklin McConnaughhay
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Publication number: 20220397061Abstract: A vibration damper for a fuel conduit of a gas turbine combustor includes a mounting portion and a damping portion. The mounting portion is secured to the fuel conduit, and the damping portion includes a stack of damping washers, a bushing on top of the stack of damping washers, a spring clip secured around the stack of damping washers and the bushing, and a shoulder bolt disposed through the bushing and the stack of damping washers and engaged to the mounting portion.Type: ApplicationFiled: January 31, 2022Publication date: December 15, 2022Inventors: Thomas Edward Johnson, Larry Lou Thomas, Johnie Franklin McConnaughhay, Scott Robert Simmons
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Patent number: 9689572Abstract: The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a conical liner support supporting the liner.Type: GrantFiled: February 6, 2013Date of Patent: June 27, 2017Assignee: GENERAL ELECTRIC COMPANYInventors: Thomas Edward Johnson, Johnie Franklin McConnaughhay, Chrisophter Paul Keener, Heath Michael Ostebee
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Patent number: 9528702Abstract: A system includes a combustor cap assembly for a multi-tube fuel nozzle. The combustor cap assembly includes a support structure defining an interior volume configured to receive an air flow. The combustor cap assembly also includes multiple mixing tubes disposed within the interior volume, wherein each mixing tube is configured to mix air and fuel to form an air-fuel mixture. The combustor cap assembly further includes a combustor cap removably coupled to the support structure. The combustor cap includes multiple nozzles integrated within the combustor cap. Each nozzle of the multiple nozzles is coupled to a respective mixing tube of the multiple mixing tubes. The combustor cap is configured to internally cool itself via one or more cooling features integrated within the combustor cap.Type: GrantFiled: February 21, 2014Date of Patent: December 27, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Gregory Allen Boardman, Michael John Hughes, Johnie Franklin McConnaughhay
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Patent number: 9528704Abstract: A system includes a a combustor cap configured to be coupled to a plurality of mixing tubes of a multi-tube fuel nozzle, wherein each mixing tube of the plurality of mixing tubes is configured to mix air and fuel to form an air-fuel mixture. The combustor cap includes multiple nozzles integrated within the combustor cap. Each nozzle of the multiple nozzles is coupled to a respective mixing tube of the multiple mixing tubes. In addition, each nozzle of the multiple nozzles includes a first end and a second end. The first end is coupled to the respective mixing tube of the multiple mixing tubes. The second end defines a non-round outlet for the air-fuel mixture. Each nozzle of the multiple nozzles includes an inner surface having first and second portions, the first portion radially diverges along an axial direction from the first end to the second end, and the second portion radially converges along the axial direction from the first end to the second end.Type: GrantFiled: February 21, 2014Date of Patent: December 27, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Michael John Hughes, Gregory Allen Boardman, Johnie Franklin McConnaughhay, Carlo Antonio Arguinzoni
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Patent number: 9447975Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and for providing the flow of fuel therethrough. The fuel injection system also may include a number of aerodynamic fuel flanges connecting the micro-mixer fuel nozzles and the support struts.Type: GrantFiled: February 6, 2013Date of Patent: September 20, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Johnie Franklin McConnaughhay, Christopher Paul Keener, Thomas Edward Johnson, Heath Michael Ostebee
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Patent number: 9441544Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles, a fuel manifold system in communication with the micro-mixer fuel nozzles to deliver a flow of fuel thereto, and a linear actuator to maneuver the micro-mixer fuel nozzles and the fuel manifold system.Type: GrantFiled: February 6, 2013Date of Patent: September 13, 2016Assignee: GENERAL ELECTRIC COMPANYInventors: Johnie Franklin McConnaughhay, Christopher Paul Keener, Thomas Edward Johnson, Heath Michael Ostebee
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Patent number: 9435539Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles, a pre-nozzle fuel injection system supporting the fuel nozzles, and a linear actuator to maneuver the fuel nozzles and the pre-nozzle fuel injection system.Type: GrantFiled: February 6, 2013Date of Patent: September 6, 2016Assignee: General Electric CompanyInventors: Christopher Paul Keener, Thomas Edward Johnson, Johnie Franklin McConnaughhay, Heath Michael Ostebee
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Patent number: 9422867Abstract: The present application and the resultant patent provide a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a center hub for providing the flow of fuel therethrough. The center hub may include a first supply circuit for a first micro-mixer fuel nozzle and a second supply circuit for a second micro-mixer fuel nozzle.Type: GrantFiled: February 6, 2013Date of Patent: August 23, 2016Assignee: General Electric CompanyInventors: Heath Michael Ostebee, Johnie Franklin McConnaughhay, Jason Thurman Stewart, Christopher Paul Keener
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Patent number: 9423135Abstract: A combustor includes a tube bundle that extends radially across at least a portion of the combustor. The tube bundle includes an upstream surface axially separated from a downstream surface, and a plurality of tubes extend from the upstream surface through the downstream surface to provide fluid communication through the tube bundle. A barrier extends radially inside the tube bundle between the upstream and downstream surfaces, and a baffle extends axially inside the tube bundle between the upstream surface and the barrier.Type: GrantFiled: November 21, 2013Date of Patent: August 23, 2016Assignee: General Electric CompanyInventors: Michael John Hughes, Johnie Franklin McConnaughhay
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Patent number: 9222673Abstract: A fuel nozzle is provided. The fuel nozzle includes a nozzle body, a plurality of swirler vanes, and at least one outlet. The nozzle body includes a back plate, a front plate, and a mixing zone defined therebetween. The back plate includes at least one inlet defined therein and the front plate includes at least one discharge defined therein. The plurality of swirler vanes are positioned between the back plate and the front plate and spaced circumferentially about the mixing zone. Each of the plurality of swirler vanes direct air obliquely into the mixing zone. The at least one outlet is defined within at least one of the nozzle body and the plurality of swirler vanes, the at least one outlet configured to inject fuel into said mixing zone.Type: GrantFiled: October 9, 2012Date of Patent: December 29, 2015Assignee: General Electric CompanyInventors: Gregory Allen Boardman, Mark Allan Hadley, Johnie Franklin McConnaughhay
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Patent number: 9212823Abstract: A combustor having a combustion chamber is provided with an external flow sleeve and a combustor liner surrounding the combustion chamber. A plurality of flow channels are provided on the combustor liner and a plurality of nozzles are disposed at predetermined locations on the flow channels. The locations of the nozzles are selected to provide different mixing times for fuel injected through the nozzles.Type: GrantFiled: September 6, 2012Date of Patent: December 15, 2015Assignee: General Electric CompanyInventors: Gregory Allen Boardman, Ronald James Chila, Mark Allan Hadley, Johnie Franklin McConnaughhay, Sarah Lori Crothers
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Publication number: 20150241064Abstract: A system includes a combustor cap assembly for a multi-tube fuel nozzle. The combustor cap assembly includes a support structure defining an interior volume configured to receive an air flow. The combustor cap assembly also includes multiple mixing tubes disposed within the interior volume, wherein each mixing tube is configured to mix air and fuel to form an air-fuel mixture. The combustor cap assembly further includes a combustor cap removably coupled to the support structure. The combustor cap includes multiple nozzles integrated within the combustor cap. Each nozzle of the multiple nozzles is coupled to a respective mixing tube of the multiple mixing tubes. The combustor cap is configured to internally cool itself via one or more cooling features integrated within the combustor cap.Type: ApplicationFiled: February 21, 2014Publication date: August 27, 2015Applicant: General Electric CompanyInventors: Gregory Allen Boardman, Michael John Hughes, Johnie Franklin McConnaughhay
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Publication number: 20150241065Abstract: A system includes a a combustor cap configured to be coupled to a plurality of mixing tubes of a multi-tube fuel nozzle, wherein each mixing tube of the plurality of mixing tubes is configured to mix air and fuel to form an air-fuel mixture. The combustor cap includes multiple nozzles integrated within the combustor cap. Each nozzle of the multiple nozzles is coupled to a respective mixing tube of the multiple mixing tubes. In addition, each nozzle of the multiple nozzles includes a first end and a second end. The first end is coupled to the respective mixing tube of the multiple mixing tubes. The second end defines a non-round outlet for the air-fuel mixture. Each nozzle of the multiple nozzles includes an inner surface having first and second portions, the first portion radially diverges along an axial direction from the first end to the second end, and the second portion radially converges along the axial direction from the first end to the second end.Type: ApplicationFiled: February 21, 2014Publication date: August 27, 2015Applicant: General Electric CompanyInventors: Michael John Hughes, Gregory Allen Boardman, Johnie Franklin McConnaughhay, Carlo Antonio Arguinzoni
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Publication number: 20150135718Abstract: A combustor includes a tube bundle that extends radially across at least a portion of the combustor. The tube bundle includes an upstream surface axially separated from a downstream surface, and a plurality of tubes extend from the upstream surface through the downstream surface to provide fluid communication through the tube bundle. A barrier extends radially inside the tube bundle between the upstream and downstream surfaces, and a baffle extends axially inside the tube bundle between the upstream surface and the barrier.Type: ApplicationFiled: November 21, 2013Publication date: May 21, 2015Applicant: General Electric CompanyInventors: Michael John Hughes, Johnie Franklin McConnaughhay
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Patent number: 8960525Abstract: A brazing process and plate assembly are disclosed. The brazing process includes positioning a braze foil on a first workpiece, then securing the braze foil to the first workpiece to form a brazable component, then positioning a second workpiece proximal to the brazable component, and then brazing the second workpiece to the brazable component. Additionally or alternatively, the brazing process includes positioning the braze foil on a tube, then securing the braze foil to the tube to form a brazable tube, then positioning a plate of a plate assembly proximal to the brazable tube, and then brazing the plate to the brazable tube. The plate assembly includes a plate and a tube brazed to the plate by a braze foil secured to the tube.Type: GrantFiled: January 31, 2013Date of Patent: February 24, 2015Assignee: General Electric CompanyInventors: David Edward Schick, Srikanth Chandrudu Kottilingam, Johnie Franklin McConnaughhay, Brian Lee Tollison, Yan Cui
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Publication number: 20140216039Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles and a fuel injection system for providing a flow of fuel to the micro-mixer fuel nozzles. The fuel injection system may include a number of support struts supporting the fuel nozzles and for providing the flow of fuel therethrough. The fuel injection system also may include a number of aerodynamic fuel flanges connecting the micro-mixer fuel nozzles and the support struts.Type: ApplicationFiled: February 6, 2013Publication date: August 7, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Johnie Franklin McConnaughhay, Christopher Paul Keener, Thomas Edward Johnson, Heath Michael Ostebee
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Publication number: 20140216050Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles, a fuel manifold system in communication with the micro-mixer fuel nozzles to deliver a flow of fuel thereto, and a linear actuator to maneuver the micro-mixer fuel nozzles and the fuel manifold system.Type: ApplicationFiled: February 6, 2013Publication date: August 7, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Johnie Franklin McConnaughhay, Christopher Paul Keener, Thomas Edward Johnson, Heath Michael Ostebee
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Publication number: 20140216049Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles, a pre-nozzle fuel injection system supporting the fuel nozzles, and a linear actuator to maneuver the fuel nozzles and the pre-nozzle fuel injection system.Type: ApplicationFiled: February 6, 2013Publication date: August 7, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Christopher Paul Keener, Thomas Edward Johnson, Johnie Franklin McConnaughhay, Heath Michael Ostebee
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Publication number: 20140216040Abstract: The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a conical liner support supporting the liner.Type: ApplicationFiled: February 6, 2013Publication date: August 7, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Thomas Edward Johnson, Johnie Franklin McConnaughhay, Chrisophter Paul Keener, Heath Michael Ostebee