Patents by Inventor Thomas Raymond Farrell

Thomas Raymond Farrell 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).

  • Publication number: 20180045057
    Abstract: A component configured for impingement cooling includes an inner wall defining a plurality of apertures extending therethrough. Each aperture of the plurality of apertures is configured to emit a cooling fluid therethrough. The component also includes an outer wall that includes an exterior surface, an opposite interior surface, and a thickness defined therebetween. The component further includes a plurality of recesses defined in the outer wall. Each recess of the plurality of recesses extends from a recess first end to an opposite recess second end. The second recess end is defined at the interior surface, and the recess first end is positioned within the outer wall at a depth less than the thickness. Each recess is aligned with a corresponding aperture of the plurality of apertures to receive the cooling fluid therefrom.
    Type: Application
    Filed: August 9, 2016
    Publication date: February 15, 2018
    Inventors: James Albert Tallman, Thomas Raymond Farrell
  • Patent number: 9458767
    Abstract: One embodiment of the present invention is a turbine nozzle segment for a turbine section of a gas turbine. The turbine nozzle segment includes an inner platform, an outer platform and an airfoil that extends therebetween. The airfoil includes a forward portion and an aft portion that is disposed downstream from the forward portion. The turbine nozzle segment further includes a fuel injection insert that extends between the inner platform and the outer platform downstream from the aft portion of the airfoil. The fuel injection insert includes a fuel circuit that extends within the fuel injection insert, and a plurality of fuel injection ports disposed within the fuel injection insert. The plurality of fuel injection ports provide for fluid communication with the fuel circuit.
    Type: Grant
    Filed: March 18, 2013
    Date of Patent: October 4, 2016
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Thomas Raymond Farrell
  • Patent number: 8845284
    Abstract: An apparatus for restricting fluid flow in a turbo-machine is disclosed. The apparatus includes: a first inter-stage sealing member configured to be located between a first rotating airfoil stage and a second rotating airfoil stage attached to a rotor shaft, the first inter-stage sealing member including a segmented structure that includes a plurality of segments forming a circumferential surface, the first inter-stage sealing member including: a first base portion including a securing mechanism configured to at least substantially radially and tangentially secure the inter-stage sealing member to an inter-stage support structure; a first axial retention mechanism; and a first axially extending sealing portion configured to be outwardly radially loaded against at least one of the first rotating airfoil stage and the second rotating airfoil stage.
    Type: Grant
    Filed: July 2, 2010
    Date of Patent: September 30, 2014
    Assignee: General Electric Company
    Inventors: Thomas Raymond Farrell, Gary Charles Liotta, Ian David Wilson
  • Publication number: 20140260263
    Abstract: One embodiment of the present invention is a turbine nozzle segment for a turbine section of a gas turbine. The turbine nozzle segment includes an inner platform, an outer platform and an airfoil that extends therebetween. The airfoil includes a forward portion and an aft portion that is disposed downstream from the forward portion. The turbine nozzle segment further includes a fuel injection insert that extends between the inner platform and the outer platform downstream from the aft portion of the airfoil. The fuel injection insert includes a fuel circuit that extends within the fuel injection insert, and a plurality of fuel injection ports disposed within the fuel injection insert. The plurality of fuel injection ports provide for fluid communication with the fuel circuit.
    Type: Application
    Filed: March 18, 2013
    Publication date: September 18, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Thomas Raymond Farrell
  • Publication number: 20140127008
    Abstract: Transition ducts, hot gas path assemblies, and turbomachines are provided. A hot gas path assembly includes an outer support ring, an inner support ring, and a transition duct coupled to the outer support ring and the inner support ring. The transition duct includes a conduit defining a passage extending between an inlet and an outlet. The inlet and the outlet are generally aligned along a longitudinal axis. The transition duct further includes an airfoil disposed within the conduit and configured to alter a hot gas flow direction.
    Type: Application
    Filed: November 8, 2012
    Publication date: May 8, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Michael Alan Davi, Khan Mohamed Khirullah Genghis Khan, Thomas Raymond Farrell
  • Patent number: 8371815
    Abstract: An apparatus for cooling an airfoil is provided. The airfoil includes an upper airfoil section, a lower airfoil section, at least one cooling passage, and a transition section. The at least one cooling passage is defined at least partially within the lower airfoil section. The at least one cooling passage is configured to flow a cooling medium therethrough, cooling at least a portion of the airfoil. The transition section is disposed between the upper airfoil section and the lower airfoil section and has an outer surface. The outer surface defines at least one cooling hole. The at least one cooling hole is fluidly connected to the at least one cooling passage. At least a portion of the cooling medium is exhausted through the at least one cooling hole.
    Type: Grant
    Filed: March 17, 2010
    Date of Patent: February 12, 2013
    Assignee: General Electric Company
    Inventor: Thomas Raymond Farrell
  • Patent number: 8221062
    Abstract: A device for reducing secondary airflow in a gas turbine is disclosed. The device includes an inter-stage sealing member located between a plurality of first turbine buckets attached to a first rotor disk, and a plurality of second turbine buckets attached to a second rotor disk. The first rotor disk and the second rotor disk are rotatable about a central axis. The inter-stage sealing member is configured to be attached in a fixed position relative to the first rotor disk and the second rotor disk, and to contact the plurality of first buckets and the plurality of second buckets in a sealing engagement.
    Type: Grant
    Filed: January 14, 2009
    Date of Patent: July 17, 2012
    Assignee: General Electric Company
    Inventors: Gary Charles Liotta, Thomas Raymond Farrell
  • Publication number: 20120087799
    Abstract: An axial retention device for a turbine is disclosed. The axial retention device includes a latch associated with a mating surface of one of a turbine component and a support structure. The latch has an outward bias and includes an axial load surface. The axial retention device further includes a pocket defined in a mating surface of the other of the turbine component and the support structure. The pocket is configured to accept the latch therein and includes a mating axial load surface. Engagement of the latch and the pocket allows the axial load surface and the mating axial load surface to interact, preventing axial movement of the turbine component with respect to the support structure in at least one direction.
    Type: Application
    Filed: October 12, 2010
    Publication date: April 12, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Thomas Raymond Farrell, Gary Charles Liotta
  • Publication number: 20120003079
    Abstract: An apparatus for restricting fluid flow in a turbo-machine is disclosed. The apparatus includes: a first inter-stage sealing member configured to be located between a first rotating airfoil stage and a second rotating airfoil stage attached to a rotor shaft, the first inter-stage sealing member including a segmented structure that includes a plurality of segments forming a circumferential surface, the first inter-stage sealing member including: a first base portion including a securing mechanism configured to at least substantially radially and tangentially secure the inter-stage sealing member to an inter-stage support structure; a first axial retention mechanism; and a first axially extending sealing portion configured to be outwardly radially loaded against at least one of the first rotating airfoil stage and the second rotating airfoil stage.
    Type: Application
    Filed: July 2, 2010
    Publication date: January 5, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: THOMAS RAYMOND FARRELL, GARY CHARLES LIOTTA, IAN DAVID WILSON
  • Publication number: 20110255958
    Abstract: A seal member for a hot gas path component in a gas turbine system is provided. The seal member includes a first seal pin, a second seal pin spaced from the first seal pin, and at least one cross-member. The at least one cross-member has a first end and a second end, and may be joined at the first end to the first seal pin and at the second end to the second seal pin. The at least one cross-member is configured to force the first and second seal pins apart when the seal member is subjected to a centrifugal force.
    Type: Application
    Filed: April 16, 2010
    Publication date: October 20, 2011
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Thomas Raymond Farrell
  • Publication number: 20110229343
    Abstract: An apparatus for cooling an airfoil is provided. The airfoil includes an upper airfoil section, a lower airfoil section, at least one cooling passage, and a transition section. The at least one cooling passage is defined at least partially within the lower airfoil section. The at least one cooling passage is configured to flow a cooling medium therethrough, cooling at least a portion of the airfoil. The transition section is disposed between the upper airfoil section and the lower airfoil section and has an outer surface. The outer surface defines at least one cooling hole. The at least one cooling hole is fluidly connected to the at least one cooling passage. At least a portion of the cooling medium is exhausted through the at least one cooling hole.
    Type: Application
    Filed: March 17, 2010
    Publication date: September 22, 2011
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Thomas Raymond Farrell
  • Publication number: 20100178160
    Abstract: A device for reducing secondary airflow in a gas turbine is disclosed. The device includes an inter-stage sealing member located between a plurality of first turbine buckets attached to a first rotor disk, and a plurality of second turbine buckets attached to a second rotor disk. The first rotor disk and the second rotor disk are rotatable about a central axis. The inter-stage sealing member is configured to be attached in a fixed position relative to the first rotor disk and the second rotor disk, and to contact the plurality of first buckets and the plurality of second buckets in a sealing engagement.
    Type: Application
    Filed: January 14, 2009
    Publication date: July 15, 2010
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Gary Charles Liotta, Thomas Raymond Farrell
  • Patent number: 7620461
    Abstract: Embodiments of the invention can provide systems and methods for using a combustion dynamics tuning algorithm with a multi-can combustor. According to one embodiment of the invention, a method for controlling a gas turbine engine with an engine model can be implemented for an engine comprising multiple cans. The method can include obtaining operating frequency information associated with multiple cans of the engine. In addition, the method can include determining variation between operating frequency information of at least two cans. Furthermore, the method can include determining a median value based at least in part on the variation. Moreover, the method can include inputting the median value to an engine model, wherein based at least in part on the median value, the engine model determines an engine control action. In addition, the method can include outputting a control command to implement the engine control action.
    Type: Grant
    Filed: June 26, 2007
    Date of Patent: November 17, 2009
    Assignee: General Electric Company
    Inventors: Garth Frederick, II, Thomas Raymond Farrell, Timothy Andrew Healy, John Carver Maters, Jonathan Carl Thatcher
  • Publication number: 20090005951
    Abstract: Embodiments of the invention can provide systems and methods for using a combustion dynamics tuning algorithm with a multi-can combustor. According to one embodiment of the invention, a method for controlling a gas turbine engine with an engine model can be implemented for an engine comprising multiple cans. The method can include obtaining operating frequency information associated with multiple cans of the engine. In addition, the method can include determining variation between operating frequency information of at least two cans. Furthermore, the method can include determining a median value based at least in part on the variation. Moreover, the method can include inputting the median value to an engine model, wherein based at least in part on the median value, the engine model determines an engine control action. In addition, the method can include outputting a control command to implement the engine control action.
    Type: Application
    Filed: June 26, 2007
    Publication date: January 1, 2009
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Garth Frederick, Thomas Raymond Farrell, Timothy Andrew Healy, John Carver Maters, Jonathan Carl Thatcher
  • Patent number: 7238002
    Abstract: A damper and seal system for a stage of a turbine that includes inner shrouds disposed circumferentially of a hot gas path through the turbine stage and shroud body(s) for supporting the inner shroud(s). A damper block engages a backside surface of the inner shroud and a damping mechanism is carried by the shroud body and connected to the damper block for applying a load to the damper block and inner shroud through the engagement of the block with the backside surface of the inner shroud, thereby damping vibratory movement of the inner shroud. The seal system includes at least one primary, integral seal and at least one secondary, non-integral seal to limit axial and radial hot gas leakage through the stage.
    Type: Grant
    Filed: November 3, 2005
    Date of Patent: July 3, 2007
    Assignee: General Electric Company
    Inventors: Ronald Ralph Cairo, Kevin Leon Bruce, Thomas Raymond Farrell
  • Patent number: 7093438
    Abstract: A gas fuel injector includes a first header plate; a second header plate spaced downstream from the upstream header plate; and a plurality of venturi tubes arranged in rows and sealably secured to the first and second header plates. Each of the venturi tubes includes an inlet section, a throat section and an exit. The exit is shaped into a pattern that reduces space between each of the venturi tubes at the exit of each of the plurality of venturi tubes.
    Type: Grant
    Filed: January 17, 2005
    Date of Patent: August 22, 2006
    Assignee: General Electric Company
    Inventors: Constantin Dinu, Thomas Raymond Farrell, Kevin M. Gordon, James Michael Storey, Krishna Kumar Venkataraman
  • Patent number: 6983600
    Abstract: A combustor for a gas turbine includes a main fuel injector for receiving compressor discharge air and mixing the air with fuel for flow to a downstream catalytic section. The main fuel injector includes an array of venturis each having an inlet, a throat and a diffuser. A main fuel supply plenum between forward and aft plates supplies fuel to secondary annular plenums having openings for supplying fuel into the inlets of the venturis upstream of the throats. The diffusers transition from a circular cross-section at the throat to multiple discrete angularly related side walls at the diffuser exits without substantial gaps therebetween. With this arrangement, uniform flow distribution of the fuel/air, velocity and temperature is provided at the catalyst inlet.
    Type: Grant
    Filed: June 30, 2004
    Date of Patent: January 10, 2006
    Assignee: General Electric Company
    Inventors: Constantin Alexandru Dinu, Iris Ziqin Hu, James Michael Storey, Thomas Raymond Farrell
  • Patent number: 6726448
    Abstract: A gas turbine having a metallic outer shroud and a ceramic inner shroud. The ceramic inner shroud being secured to the outer shroud by hooks carried on the outer shroud. The hooks on the outer shroud being coated with TBC. A pin and spring system being provided to hold the ceramic inner shroud against the forward hook of the outer shroud. An anti-rotation pin being provided to trap the aft bend of the ceramic inner shroud against the aft hook of the outer shroud. The gas turbine further including a damping spring and pin system, disposed between a heat shield, within the outer shroud, and the ceramic inner shroud, to provide damping of the inner shroud.
    Type: Grant
    Filed: May 15, 2002
    Date of Patent: April 27, 2004
    Assignee: General Electric Company
    Inventors: Edward Lee McGrath, Gregory S. Corman, Anthony J. Dean, Mark Stewart Schroder, Chris Basil Jiomacas, Thomas Raymond Farrell, Kenneth Lorenzo Parks
  • Publication number: 20030215328
    Abstract: A gas turbine having a metallic outer shroud and a ceramic inner shroud. The ceramic inner shroud being secured to the outer shroud by hooks carried on the outer shroud. The hooks on the outer shroud being coated with TBC. A pin and spring system being provided to hold the ceramic inner shroud against the forward hook of the outer shroud. An anti-rotation pin being provided to trap the aft bend of the ceramic inner shroud against the aft hook of the outer shroud. The gas turbine further including a damping spring and pin system, disposed between a heat shield, within the outer shroud, and the ceramic inner shroud, to provide damping of the inner shroud.
    Type: Application
    Filed: May 15, 2002
    Publication date: November 20, 2003
    Inventors: Edward Lee McGrath, Gregory S. Corman, Anthony J. Dean, Mark Steward Schroder, Chris Basil Jiomacas, Thomas Raymond Farrell, Kenneth Lorenzo Parks
  • Patent number: 5934687
    Abstract: A gas-path leakage seal for generally sealing a gas-path leakage-gap between spaced-apart first and second members of a turbine (such as combustor casing segments of a gas turbine). The seal includes a flexible and generally imperforate metal sheet assemblage having opposing first and second surfaces and two opposing raised edges extending a generally identical distance above and below the surfaces. A first cloth layer assemblage has a thickness generally equal to the previously-defined identical distance and is superimposed on the first surface between the raised edges. A second cloth layer assemblage is generally identical to the first cloth layer assemblage and is superimposed on the second surface between the raised edges.
    Type: Grant
    Filed: July 7, 1997
    Date of Patent: August 10, 1999
    Assignee: General Electric Company
    Inventors: Bharat Sampathkumaran Bagepalli, Mahmut Faruk Aksit, Thomas Raymond Farrell