Patents by Inventor Ronnie Ray Pentecost
Ronnie Ray Pentecost 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: 9038394Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface feature for interfacing with an adjacent transition duct. The turbine system further includes a convolution seal contacting the interface feature to provide a seal between the interface feature and the adjacent transition duct.Type: GrantFiled: April 30, 2012Date of Patent: May 26, 2015Assignee: General Electric CompanyInventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Daniel Jackson Dillard, Ronnie Ray Pentecost
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Patent number: 8978388Abstract: A loading assembly for a turbine system is disclosed. The loading assembly includes a transition duct and a load member. The transition duct extends between a fuel nozzle and a turbine section, and has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The load member extends from the transition duct and is configured to transfer a load between the transition duct and an adjacent transition duct along at least one of the longitudinal axis, the radial axis, or the tangential axis.Type: GrantFiled: June 3, 2011Date of Patent: March 17, 2015Assignee: General Electric CompanyInventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Ronnie Ray Pentecost
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Patent number: 8974179Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a convolution seal contacting the interface member to provide a seal between the interface member and the turbine section.Type: GrantFiled: November 9, 2011Date of Patent: March 10, 2015Assignee: General Electric CompanyInventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Daniel Jackson Dillard, Ronnie Ray Pentecost
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Publication number: 20140260277Abstract: A combustion module for a combustor of a gas turbine includes an annular fuel distribution manifold disposed at an upstream end of the combustion module. The fuel distribution manifold includes an annular support sleeve having an inner surface. The combustion module further includes a fuel injection assembly having an annular combustion liner that extends downstream from the fuel distribution manifold and that terminates at an aft frame, and an annular flow sleeve that circumferentially surrounds the combustion liner. The flow sleeve extends downstream from the fuel distribution manifold and terminates at the aft frame. The flow sleeve extends continuously between the support sleeve and the aft frame. A forward portion of the flow sleeve is positioned concentrically within the support sleeve where the forward portion is slidingly engaged with the inner surface of the support sleeve.Type: ApplicationFiled: March 18, 2013Publication date: September 18, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Richard Martin DiCintio, Patrick Benedict Melton, Lucas John Stoia, Christopher Paul Willis, Ronnie Ray Pentecost
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Publication number: 20140260318Abstract: A side seal slot extends along a one side of an aft frame for a combustion liner of a gas turbine. The side seal slot is at least partially defined between a downstream wall and an upstream wall that extend outward from the first side of the aft frame. A first segment of the upstream wall extends from an inner portion of the aft frame towards an outer portion of the aft frame at a first outward distance from the first side. A second segment of the upstream wall extends from the first segment to the outer portion of the aft frame at a second outward distance from the first side. The second segment of the upstream wall at least partially defines a side seal guide feature to allow for axial insertion of a bottom portion of a side seal into the side seal slot.Type: ApplicationFiled: March 18, 2013Publication date: September 18, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Christopher Paul Willis, Richard Martin DiCintio, Ronnie Ray Pentecost, Christopher Crookshanks
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Publication number: 20140144122Abstract: A crossfire tube assembly between adjacent combustors includes a first sleeve adapted to provide fluid communication from a first combustor and a second sleeve adapted to connect to provide fluid communication from a second combustor. The second sleeve extends at least partially inside the first sleeve. A bias is between the first and second sleeves.Type: ApplicationFiled: November 29, 2012Publication date: May 29, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Brandon Taylor Overby, Keith Cletus Belsom, Jonathan Kay Allen, Kyle Eric Benson, Patrick Benedict Melton, Richard Martin DiCintio, Lucas John Stoia, Ronnie Ray Pentecost
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Patent number: 8707673Abstract: Turbine systems are provided. A turbine system includes a transition duct comprising an inlet, an outlet, and a duct passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The duct passage includes an upstream portion and a downstream portion. The upstream portion extends from the inlet between an inlet end and an aft end. The downstream portion extends from the outlet between an outlet end and a head end. The turbine system further includes a joint coupling the aft end of the upstream portion and the head end of the downstream portion together. The joint is configured to allow movement of the upstream portion and the downstream portion relative to each other about or along at least one axis.Type: GrantFiled: January 4, 2013Date of Patent: April 29, 2014Assignee: General Electric CompanyInventors: James Scott Flanagan, Kevin Weston McMahan, Jeffrey Scott LeBegue, Ronnie Ray Pentecost
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Patent number: 8701415Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a flexible metallic seal contacting the interface member to provide a seal between the interface member and the turbine section.Type: GrantFiled: November 9, 2011Date of Patent: April 22, 2014Assignee: General Electric CompanyInventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Daniel Jackson Dillard, Ronnie Ray Pentecost
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Patent number: 8650852Abstract: A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis. The support assembly further includes an annular contact member extending from the transition duct. The contact member is configured to allow movement of the transition duct about at least one axis.Type: GrantFiled: July 5, 2011Date of Patent: February 18, 2014Assignee: General Electric CompanyInventors: Jeffrey Scott LeBegue, Kevin Weston McMahan, Ronnie Ray Pentecost, James Scott Flanagan
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Publication number: 20130283817Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface feature for interfacing with an adjacent transition duct. The turbine system further includes a flexible seal contacting the interface feature to provide a seal between the interface feature and the adjacent transition duct. The flexible seal includes a sheet having a first surface, an opposing second surface, and a peripheral edge therebetween.Type: ApplicationFiled: April 30, 2012Publication date: October 31, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Daniel Jackson Dillard, Ronnie Ray Pentecost
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Publication number: 20130283804Abstract: A system for supplying an injection fluid to a combustor is disclosed. The system includes a transition duct comprising an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The passage defines a combustion chamber. The system further includes a tube providing fluid communication for the injection fluid to flow through the transition duct and into the combustion chamber.Type: ApplicationFiled: April 30, 2012Publication date: October 31, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Jeffrey Scott LeBegue, Ronnie Ray Pentecost, James Scott Flanagan, Won-Wook Kim, Kevin Weston McMahan
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Publication number: 20130283818Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface feature for interfacing with an adjacent transition duct. The turbine system further includes a convolution seal contacting the interface feature to provide a seal between the interface feature and the adjacent transition duct.Type: ApplicationFiled: April 30, 2012Publication date: October 31, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Daniel Jackson Dillard, Ronnie Ray Pentecost
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Patent number: 8459041Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a leaf seal contacting the interface member to provide a seal between the interface member and the turbine section.Type: GrantFiled: November 9, 2011Date of Patent: June 11, 2013Assignee: General Electric CompanyInventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Daniel Jackson Dillard, Ronnie Ray Pentecost
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Patent number: 8448450Abstract: A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis. The support assembly further includes a plurality of protrusions extending from the transition duct. The plurality of protrusions are configured to allow movement of the transition duct about at least one axis.Type: GrantFiled: July 5, 2011Date of Patent: May 28, 2013Assignee: General Electric CompanyInventors: Jeffrey Scott LeBegue, Kevin Weston McMahan, Ronnie Ray Pentecost, James Scott Flanagan
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Publication number: 20130111911Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a leaf seal contacting the interface member to provide a seal between the interface member and the turbine section.Type: ApplicationFiled: November 9, 2011Publication date: May 9, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Daniel Jackson Dillard, Ronnie Ray Pentecost
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Publication number: 20130111912Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a flexible metallic seal contacting the interface member to provide a seal between the interface member and the turbine section.Type: ApplicationFiled: November 9, 2011Publication date: May 9, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Daniel Jackson Dillard, Ronnie Ray Pentecost
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Publication number: 20130115048Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a convolution seal contacting the interface member to provide a seal between the interface member and the turbine section.Type: ApplicationFiled: November 9, 2011Publication date: May 9, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Daniel Jackson Dillard, Ronnie Ray Pentecost
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Publication number: 20130008177Abstract: A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis. The support assembly further includes a plurality of protrusions extending from the transition duct. The plurality of protrusions are configured to allow movement of the transition duct about at least one axis.Type: ApplicationFiled: July 5, 2011Publication date: January 10, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Jeffrey Scott LeBegue, Kevin Weston McMahan, Ronnie Ray Pentecost, James Scott Flanagan
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Publication number: 20130008178Abstract: A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis. The support assembly further includes an annular contact member extending from the transition duct. The contact member is configured to allow movement of the transition duct about at least one axis.Type: ApplicationFiled: July 5, 2011Publication date: January 10, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Jeffrey Scott LeBegue, Kevin Weston McMahan, Ronnie Ray Pentecost, James Scott Flanagan
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Publication number: 20120304653Abstract: A loading assembly for a turbine system is disclosed. The loading assembly includes a transition duct and a load member. The transition duct extends between a fuel nozzle and a turbine section, and has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The load member extends from the transition duct and is configured to transfer a load between the transition duct and an adjacent transition duct along at least one of the longitudinal axis, the radial axis, or the tangential axis.Type: ApplicationFiled: June 3, 2011Publication date: December 6, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Ronnie Ray Pentecost