Patents by Inventor Jason Randolph Marshall

Jason Randolph Marshall 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).

  • Combined Gas Turbine Auxiliary Systems
    Publication number: 20150377126
    Abstract: The present application provides a gas turbine engine. The gas turbine engine may include a compressor, a combustor, a number of auxiliary systems, and a common auxiliary system manifold. The common auxiliary system manifold is in communication with the compressor, the combustor, and the auxiliary systems.
    Type: Application
    Filed: June 30, 2014
    Publication date: December 31, 2015
    Inventors: James Harper, Jason Randolph Marshall
  • Systems and methods for detecting a flame in a fuel nozzle of a gas turbine
    Patent number: 8434291
    Abstract: A system may detect a flame about a fuel nozzle of a gas turbine. The gas turbine may have a compressor and a combustor. The system may include a first pressure sensor, a second pressure sensor, and a transducer. The first pressure sensor may detect a first pressure upstream of the fuel nozzle. The second pressure sensor may detect a second pressure downstream of the fuel nozzle. The transducer may be operable to detect a pressure difference between the first pressure sensor and the second pressure sensor.
    Type: Grant
    Filed: January 8, 2009
    Date of Patent: May 7, 2013
    Assignee: General Electric Company
    Inventors: Gilbert Otto Kraemer, James Michael Storey, John Lipinski, Julio Enrique Mestroni, David Lee Williamson, Jason Randolph Marshall, Anthony Krull
  • COMBUSTOR NOZZLE AND METHOD FOR SUPPLYING FUEL TO A COMBUSTOR
    Publication number: 20120282558
    Abstract: A combustor nozzle includes a fuel supply in fluid communication with a fuel passage that terminates at a fuel outlet. An oxidant supply is in fluid communication with an oxidant passage radially displaced from the fuel passage and that terminates at an oxidant outlet radially displaced from the fuel outlet. A diluent passage radially displaced from the fuel passage and the oxidant passage terminates at a diluent outlet disposed between the fuel outlet and the oxidant outlet. A method for supplying fuel to a combustor includes flowing the fuel through a fuel outlet and flowing an oxidant through an oxidant outlet radially displaced from the fuel outlet. The method further includes flowing a diluent through a diluent outlet radially disposed between the fuel outlet and the oxidant outlet.
    Type: Application
    Filed: May 5, 2011
    Publication date: November 8, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Gilbert Otto Kraemer, Jonathan Dwight Berry, Jason Randolph Marshall
  • SYSTEMS AND METHODS FOR DETECTING A FLAME IN A FUEL NOZZLE OF A GAS TURBINE
    Publication number: 20100170217
    Abstract: A system may detect a flame about a fuel nozzle of a gas turbine. The gas turbine may have a compressor and a combustor. The system may include a first pressure sensor, a second pressure sensor, and a transducer. The first pressure sensor may detect a first pressure upstream of the fuel nozzle. The second pressure sensor may detect a second pressure downstream of the fuel nozzle. The transducer may be operable to detect a pressure difference between the first pressure sensor and the second pressure sensor.
    Type: Application
    Filed: January 8, 2009
    Publication date: July 8, 2010
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Gilbert Otto Kraemer, James Michael Storey, John Lipinski, Julio Enrique Mestroni, David Lee Williamson, Jason Randolph Marshall, Anthony Krull