Patents by Inventor Wayne R. Grady

Wayne R. Grady 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).

  • In situ gas turbine prevention of crack growth progression
    Patent number: 10247002
    Abstract: A method for remotely stopping a crack in a component of a gas turbine engine is provided. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning the tip adjacent to a defect within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface on the component; supplying a new material to the area to fill the defect; and heating the new material to fuse the new material to the component within the defect.
    Type: Grant
    Filed: February 3, 2016
    Date of Patent: April 2, 2019
    Assignee: General Electric Company
    Inventors: Herbert Chidsey Roberts, David Scott Diwinsky, Wayne R. Grady
  • In situ gas turbine prevention of crack growth progression
    Patent number: 10094221
    Abstract: Methods for remotely joining material a surface area of a component of a gas turbine engine are provided. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning a tip of the integrated repair interface adjacent to a defect defined within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface of the component; and supplying a new material to the area to fill the defect.
    Type: Grant
    Filed: February 3, 2016
    Date of Patent: October 9, 2018
    Assignee: General Electric Company
    Inventors: Herbert Chidsey Roberts, David Scott Diwinsky, Wayne R. Grady
  • In Situ Gas Turbine Prevention of Crack Growth Progression
    Publication number: 20170218764
    Abstract: Methods for remotely joining material a surface area of a component of a gas turbine engine are provided. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning a tip of the integrated repair interface adjacent to a defect defined within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface of the component; and supplying a new material to the area to fill the defect.
    Type: Application
    Filed: February 3, 2016
    Publication date: August 3, 2017
    Inventors: Herbert Chidsey Roberts, David Scott Diwinsky, Wayne R. Grady
  • In Situ Gas Turbine Prevention of Crack Growth Progression
    Publication number: 20170218761
    Abstract: A method for remotely stopping a crack in a component of a gas turbine engine is provided. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning the tip adjacent to a defect within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface on the component; supplying a new material to the area to fill the defect; and heating the new material to fuse the new material to the component within the defect.
    Type: Application
    Filed: February 3, 2016
    Publication date: August 3, 2017
    Inventors: Herbert Chidsey Roberts, David Scott Diwinsky, Wayne R. Grady
  • Turbine nozzle segment and repair method
    Patent number: 7837437
    Abstract: A method of repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes using an salvageable part, such as honeycomb backing strip remnant, from a nozzle segment that is unrepairable, and joining the honeycomb backing strip to a replacement casting. The replacement casting includes a tenon formed on the inner band that mates with a mortise formed on the back side of the honeycomb backing strip. A nozzle segment and nozzle segment casting used in connection with the method is also disclosed.
    Type: Grant
    Filed: March 7, 2007
    Date of Patent: November 23, 2010
    Assignee: General Electric Company
    Inventors: Wayne R. Grady, Timothy L. Siebert
  • TURBINE NOZZLE SEGMENT AND REPAIR METHOD
    Publication number: 20080273971
    Abstract: A method of repairing a turbine nozzle segment having at least one vane disposed between outer and inner bands. The method includes using an salvageable part, such as honeycomb backing strip remnant, from a nozzle segment that is unrepairable, and joining the honeycomb backing strip to a replacement casting. The replacement casting includes a tenon formed on the inner band that mates with a mortise formed on the back side of the honeycomb backing strip. A nozzle segment and nozzle segment casting used in connection with the method is also disclosed.
    Type: Application
    Filed: March 7, 2007
    Publication date: November 6, 2008
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Wayne R. Grady, Timothy L. Siebert