Patents by Inventor JESSE BLAIR BUTLER
JESSE BLAIR BUTLER 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: 9360221Abstract: A gas turbine includes a compressor and at least one combustor downstream from the compressor. The combustor includes a burner having an inner shroud extending axially along at least a portion of the burner, an outer shroud radially separated from the inner shroud and extending axially along at least a portion of the burner, and a plurality of stator vanes extending radially between the inner shroud and the outer shroud. The stator vanes have an inner end proximate the inner shroud and an outer end proximate the outer shroud. The burner further includes a vortex tip at one of either the inner end or the outer end of the stator vanes. The vortex tip provides a gap between the inner end and the inner shroud or the outer end and the outer shroud, and the vortex tip includes a plurality of fuel ports. The gas turbine further includes a turbine downstream from the combustor.Type: GrantFiled: November 15, 2013Date of Patent: June 7, 2016Assignee: General Electric CompanyInventors: Jesse Blair Butler, David Leach, Kevin Weston McMahan, Mark Allan Hadley, Geoffrey David Myers
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Patent number: 9097126Abstract: A system includes at least one gas turbine blade that includes at least one recess disposed in a surface of the at least one gas turbine blade. The system also includes a porous insert that includes multiple pores that enable a cooling fluid to flow through the porous insert. The system further includes a cover plate, wherein the porous insert is disposed within the at least one recess, and the cover plate is disposed over the porous insert to enclose the porous insert within the at least one recess.Type: GrantFiled: September 12, 2012Date of Patent: August 4, 2015Assignee: GENERAL ELECTRIC COMPANYInventors: Christopher Michael Prue, Jesse Blair Butler
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Publication number: 20140123652Abstract: A gas turbine includes a compressor and at least one combustor downstream from the compressor. The combustor includes a burner having an inner shroud extending axially along at least a portion of the burner, an outer shroud radially separated from the inner shroud and extending axially along at least a portion of the burner, and a plurality of stator vanes extending radially between the inner shroud and the outer shroud. The stator vanes have an inner end proximate the inner shroud and an outer end proximate the outer shroud. The burner further includes a vortex tip at one of either the inner end or the outer end of the stator vanes. The vortex tip provides a gap between the inner end and the inner shroud or the outer end and the outer shroud, and the vortex tip includes a plurality of fuel ports. The gas turbine further includes a turbine downstream from the combustor.Type: ApplicationFiled: November 15, 2013Publication date: May 8, 2014Applicant: General Electric CompanyInventors: Jesse Blair Butler, David Leach, Kevin Weston McMahan, Mark Allan Hadley, Geoffrey David Myers
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Publication number: 20140116660Abstract: A method of fabricating a component is provided. The component includes a substrate having an outer surface and an inner surface, where the inner surface defines at least one interior space. The fabrication method includes forming at least one groove in the outer substrate surface. Each groove extends at least partially along the outer substrate surface and has an asymmetric cross-section. The method further includes forming at least one access hole in the substrate. Each access hole connects the respective groove in fluid communication with the respective interior space. A coating is disposed over at least a portion of the substrate surface, such that the groove(s) and the coating together define one or more channels for cooling the component. A component is also disclose and has at least one groove with an asymmetric cross-section.Type: ApplicationFiled: October 31, 2012Publication date: May 1, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Jesse Blair Butler, Ronald Scott Bunker, Scott Andrew Weaver, Kevin Richard Kirtley
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Publication number: 20140072448Abstract: A system includes at least one gas turbine blade that includes at least one recess disposed in a surface of the at least one gas turbine blade. The system also includes a porous insert that includes multiple pores that enable a cooling fluid to flow through the porous insert. The system further includes a cover plate, wherein the porous insert is disposed within the at least one recess, and the cover plate is disposed over the porous insert to enclose the porous insert within the at least one recess.Type: ApplicationFiled: September 12, 2012Publication date: March 13, 2014Applicant: General Electric CompanyInventors: Christopher Michael Prue, Jesse Blair Butler
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Publication number: 20140044557Abstract: A turbine blade includes an outer surface, and a rim surrounds at least a portion of the outer surface. A trench in the rim extends around at least a portion of the outer surface.Type: ApplicationFiled: August 9, 2012Publication date: February 13, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Anthony Louis Giglio, Scott Edmond Ellis, Jesse Blair Butler, Camilo Andres Sampayo
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Publication number: 20120301319Abstract: A turbine component may generally comprise an airfoil having a base and a tip disposed opposite the base. The airfoil may further include a pressure side surface and a suction side surface extending between a leading edge and a trailing edge. An airfoil circuit may be at least partially disposed within the airfoil and may be configured to supply a medium through the airfoil. The turbine component may also include a curved passage defined in the airfoil so as to be in flow communication with the airfoil circuit. Additionally, an outlet may be defined through the pressure side surface or the suction side surface of the airfoil. The outlet may be in flow communication with the curved passage and may have a cross-sectional area that is greater than a cross-sectional area of the curved passage.Type: ApplicationFiled: May 24, 2011Publication date: November 29, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Benjamin Paul Lacy, Jesse Blair Butler
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Publication number: 20120087803Abstract: A turbine bucket includes an airfoil portion at one end thereof; a root portion at an opposite end thereof; a platform portion between the airfoil portion and the root portion; at least one internal cavity within or radially inward of the platform portion having at least one film cooling hole extending between the at least one cavity and an external surface of the platform portion. The film cooling hole is curved along a length dimension of the film cooling hole.Type: ApplicationFiled: October 12, 2010Publication date: April 12, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Jesse Blair BUTLER, Benjamin LACY
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Publication number: 20110023494Abstract: A gas turbine includes a compressor and at least one combustor downstream from the compressor. The combustor includes a burner having an inner shroud extending axially along at least a portion of the burner, an outer shroud radially separated from the inner shroud and extending axially along at least a portion of the burner, and a plurality of stator vanes extending radially between the inner shroud and the outer shroud. The stator vanes have an inner end proximate the inner shroud and an outer end proximate the outer shroud. The burner further includes a vortex tip at one of either the inner end or the outer end of the stator vanes. The vortex tip provides a gap between the inner end and the inner shroud or the outer end and the outer shroud, and the vortex tip includes a plurality of fuel ports. The gas turbine further includes a turbine downstream from the combustor.Type: ApplicationFiled: July 28, 2009Publication date: February 3, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: JESSE BLAIR BUTLER, DAVID LEACH, KEVIN WESTON MCMAHAN, MARK ALLAN HADLEY, GEOFFREY DAVID MYERS