Patents by Inventor Clive Andrew Morgan

Clive Andrew Morgan 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).

  • Automatic blocked hole identification
    Patent number: 10589370
    Abstract: A method for hole formation using an electrical discharge machining tool configured to penetrate metal. The method includes the steps of: penetrating the metal using an electrode to form a hole by moving the electrode away from a starting point; verifying that the hole is complete using the electrical discharge machine; and wherein the verifying step includes the step of probing the hole with the electrode.
    Type: Grant
    Filed: May 8, 2017
    Date of Patent: March 17, 2020
    Assignee: General Electric Company
    Inventors: Wilson Frost, Russell L. Bouchard, Clive Andrew Morgan
  • AUTOMATIC BLOCKED HOLE IDENTIFICATION
    Publication number: 20180318952
    Abstract: A method for hole formation using an electrical discharge machining tool configured to penetrate metal. The method includes the steps of: penetrating the metal using an electrode to form a hole by moving the electrode away from a starting point; verifying that the hole is complete using the electrical discharge machine; and wherein the verifying step includes the step of probing the hole with the electrode.
    Type: Application
    Filed: May 8, 2017
    Publication date: November 8, 2018
    Inventors: Wilson Frost, Russell L. Bouchard, Clive Andrew Morgan
  • Setting Gas Turbine Firing to Maintain Metal Surface Temperatures
    Publication number: 20150118014
    Abstract: The systems, methods, and computer-readable media set a gas turbine firing temperature to maintain gas turbine metal surface temperatures. In certain embodiments, a method of setting a gas turbine firing temperature is disclosed that may comprise determining a critical temperature at which ash from ash bearing fuels becomes unremovable by conventional water wash procedures, determining hot gas path component metal surface temperatures, and adjusting the gas turbine firing temperature to maintain the metal surface temperatures below the critical temperature. Determining the metal surface temperatures may be based at least in part on measured gas turbine parameters, gas turbine performance models, and empirical models.
    Type: Application
    Filed: October 29, 2013
    Publication date: April 30, 2015
    Applicant: General Electric Company
    Inventors: Kevin Michael Elward, Scott Alan Kopcho, Robert Thomas Thatcher, Ariel Harter Lomas, Bradley Steven Carey, Clive Andrew Morgan
  • Turbine nozzle segment
    Patent number: 8257028
    Abstract: A turbine nozzle segment includes a band having a plurality of tabs, an airfoil extending from the band and a support structure attached to the tabs. The support structure has a plurality of biasing structures.
    Type: Grant
    Filed: December 29, 2007
    Date of Patent: September 4, 2012
    Assignee: General Electric Company
    Inventors: Clive Andrew Morgan, Todd Stephen Heffron, Sanjeewa Thusitha Fonseka
  • Method and system for assembling a turbine engine
    Patent number: 7771164
    Abstract: A method of assembling a turbine includes positioning a turbine nozzle against a forward inner nozzle support extending from a rotor assembly, and coupling a cover to the forward inner nozzle support. The method also includes inserting a tab that extends from the cover within at least one aperture defined in the turbine nozzle.
    Type: Grant
    Filed: December 18, 2006
    Date of Patent: August 10, 2010
    Assignee: General Electric Company
    Inventors: John Alan Manteiga, Clive Andrew Morgan, John Christopher Brauer, Todd Stephen Heffron
  • Turbine Nozzle Segment and Method for Repairing a Turbine Nozzle Segment
    Publication number: 20090169376
    Abstract: A turbine nozzle segment includes a first band, an airfoil extending from the first band and a support attached to the first band. The support may have a plurality of circumferentially spaced apart tabs.
    Type: Application
    Filed: December 29, 2007
    Publication date: July 2, 2009
    Inventors: Clive Andrew Morgan, Todd Stephen Heffron, Sanjeewa Thusitha Fonseka, Peter Robert Griffiths
  • TURBINE NOZZLE SEGMENT AND ASSEMBLY
    Publication number: 20090169369
    Abstract: A turbine nozzle segment includes a band having a plurality of circumferentially spaced apart tabs and a single airfoil extending from the band.
    Type: Application
    Filed: December 29, 2007
    Publication date: July 2, 2009
    Inventors: Clive Andrew Morgan, Todd Stephen Heffron, Sanjeewa Thusitha Fonseka
  • TURBINE NOZZLE SEGMENT
    Publication number: 20090169370
    Abstract: A turbine nozzle segment includes a band having a plurality of tabs, an airfoil extending from the band and a support structure attached to the tabs. The support structure has a plurality of biasing structures.
    Type: Application
    Filed: December 29, 2007
    Publication date: July 2, 2009
    Inventors: Clive Andrew Morgan, Todd Stephen Heffron, Sanjeewa Thusitha Fonseka
  • METHOD AND SYSTEM FOR ASSEMBLING A TURBINE ENGINE
    Publication number: 20080145218
    Abstract: A method of assembling a turbine includes positioning a turbine nozzle against a forward inner nozzle support extending from a rotor assembly, and coupling a cover to the forward inner nozzle support. The method also includes inserting a tab that extends from the cover within at least one aperture defined in the turbine nozzle.
    Type: Application
    Filed: December 18, 2006
    Publication date: June 19, 2008
    Inventors: John Alan Manteiga, Clive Andrew Morgan, John Christopher Brauer, Todd Stephen Heffron