Patents by Inventor Daniel Jackson Dillard
Daniel Jackson Dillard 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: 9328623Abstract: A turbine system is disclosed. The turbine system includes a transition duct having 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 turbine system further includes a turbine section connected to the transition duct. The turbine section includes a plurality of shroud blocks at least partially defining a hot gas path, a plurality of buckets at least partially disposed in the hot gas path, and a plurality of nozzles at least partially disposed in the hot gas path. At least one of a shroud block, a bucket, or a nozzle includes means for withstanding high temperatures.Type: GrantFiled: October 5, 2011Date of Patent: May 3, 2016Assignee: General Electric CompanyInventors: Kevin Weston McMahan, Daniel Jackson Dillard
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Patent number: 9194237Abstract: A gas turbine nozzle section of a gas turbine may include an inner endwall with a leading edge. A serpentine passage may be configured substantially within the leading edge. The serpentine passage may have an inlet and an outlet. Air may be received at the inlet and exhausted at the outlet, cooling the leading edge.Type: GrantFiled: September 10, 2012Date of Patent: November 24, 2015Assignee: General Electric CompanyInventors: Daniel Jackson Dillard, Christopher Donald Porter
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Patent number: 9080447Abstract: Turbine systems are provided. In one embodiment, 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 extending from the inlet and a downstream portion extending from the outlet. The turbine system further includes a rib extending from an outer surface of the duct passage, the rib dividing the upstream portion and the downstream portion.Type: GrantFiled: March 21, 2013Date of Patent: July 14, 2015Assignee: General Electric CompanyInventors: Kevin Weston McMahan, Jeffrey Scott LeBegue, Jaime Javier Maldonado, Daniel Jackson Dillard, James Scott Flanagan
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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: 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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Patent number: 8926269Abstract: A seal carrier for a seal used between rotating and non-rotating components includes an arcuate sheet metal seal carrier body formed to include a stepped, conical configuration wherein an inner diameter at a forward end is larger than the diameter at an aft end, with plural stepped sections defined by alternating radial and axial portions between the forward end and the aft end. Each axial portion is adapted to carry a seal element, preferably a honeycomb seal. Mounting flanges are provided at the forward end and the aft end of the arcuate sheet metal seal carrier body to enable attachment to the non-rotating component.Type: GrantFiled: September 6, 2011Date of Patent: January 6, 2015Assignee: General Electric CompanyInventors: Daniel Jackson Dillard, Gregory Thomas Foster, Niranjan Gokuldas Pai
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Publication number: 20140283520Abstract: Turbine systems are provided. In one embodiment, 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 extending from the inlet and a downstream portion extending from the outlet. The turbine system further includes a rib extending from an outer surface of the duct passage, the rib dividing the upstream portion and the downstream portion.Type: ApplicationFiled: March 21, 2013Publication date: September 25, 2014Applicant: General Electric CompanyInventors: Kevin Weston McMahan, Jeffrey Scott LeBegue, Jaime Javier Maldonado, Daniel Jackson Dillard, James Scott Flanagan
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Patent number: 8827641Abstract: A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.Type: GrantFiled: November 28, 2011Date of Patent: September 9, 2014Assignee: General Electric CompanyInventors: Paul Kendall Smith, Mary Virginia Holloway, San Jason Nguyen, Daniel Jackson Dillard
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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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Publication number: 20140072400Abstract: A gas turbine nozzle section of a gas turbine may include an inner endwall with a leading edge. A serpentine passage may be configured substantially within the leading edge. The serpentine passage may have an inlet and an outlet. Air may be received at the inlet and exhausted at the outlet, cooling the leading edge.Type: ApplicationFiled: September 10, 2012Publication date: March 13, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Daniel Jackson Dillard, Christopher Donald Porter
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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: 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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Publication number: 20130269821Abstract: Disclosed herein are methods, systems, and apparatuses for hot gas flow. In an embodiment, a transition piece comprises a surface that conforms to an approximately straight line path stretching approximately from the forward end of a transition piece to the aft end of the transition piece wherein the surface may help direct the flow of gases.Type: ApplicationFiled: April 13, 2012Publication date: October 17, 2013Applicant: General Electric CompanyInventors: Richard Martin DiCintio, Patrick Benedict Melton, Daniel Jackson Dillard
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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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Publication number: 20130136592Abstract: A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.Type: ApplicationFiled: November 28, 2011Publication date: May 30, 2013Inventors: Paul Kendall Smith, Mary Virginia Holloway, San Jason Nguyen, Daniel Jackson Dillard
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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: 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: 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: 20130086914Abstract: A turbine system is disclosed. The turbine system includes a transition duct having 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 turbine system further includes a turbine section connected to the transition duct. The turbine section includes a plurality of shroud blocks at least partially defining a hot gas path, a plurality of buckets at least partially disposed in the hot gas path, and a plurality of nozzles at least partially disposed in the hot gas path. At least one of a shroud block, a bucket, or a nozzle includes means for withstanding high temperatures.Type: ApplicationFiled: October 5, 2011Publication date: April 11, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Kevin Weston McMahan, Daniel Jackson Dillard
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Publication number: 20130058764Abstract: A seal carrier for a seal used between rotating and non-rotating components includes an arcuate sheet metal seal carrier body formed to include a stepped, conical configuration wherein an inner diameter at a forward end is larger than the diameter at an aft end, with plural stepped sections defined by alternating radial and axial portions between the forward end and the aft end. Each axial portion is adapted to carry a seal element, preferably a honeycomb seal. Mounting flanges are provided at the forward end and the aft end of the arcuate sheet metal seal carrier body to enable attachment to the non-rotating component.Type: ApplicationFiled: September 6, 2011Publication date: March 7, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Daniel Jackson DILLARD, Gregory Thomas FOSTER, Niranjan Gokuldas PAI