Patents by Inventor Travis M. Frazier

Travis M. Frazier 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).

  • Aircraft propulsion system nozzle with internal flow passage
    Patent number: 11746726
    Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a nozzle extending axially along and circumferentially about an axial centerline. The nozzle includes a nozzle panel and a nozzle fairing fixedly connected to the nozzle panel at an axial end of the nozzle. The nozzle is configured with an internal flow passage radially between the nozzle panel and the nozzle fairing. The internal flow passage extends axially within the nozzle to an outlet between the nozzle panel and the nozzle fairing at the axial end of the nozzle.
    Type: Grant
    Filed: May 4, 2021
    Date of Patent: September 5, 2023
    Assignee: Rohr, Inc.
    Inventors: Adam Saunders, Bryce T. Kelford, Travis M. Frazier, Richard Haslim, Richard S. Alloway, Vijay V. Pujar
  • Transpirationally cooled exhaust center body for an aircraft propulsion system
    Patent number: 11560847
    Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes an exhaust center body and a duct system. The exhaust center body includes an exterior skin. The duct system is fluidly coupled with a plurality of exterior skin perforations in the exterior skin. The duct system is configured to direct bypass air received from a bypass flow path within the aircraft propulsion system to the exterior skin perforations.
    Type: Grant
    Filed: April 7, 2021
    Date of Patent: January 24, 2023
    Assignee: Rohr, Inc.
    Inventors: Bryce T. Kelford, Adam Saunders, Richard S. Alloway, Richard Haslim, Travis M. Frazier
  • AIRCRAFT PROPULSION SYSTEM NOZZLE WITH INTERNAL FLOW PASSAGE
    Publication number: 20210348581
    Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a nozzle extending axially along and circumferentially about an axial centerline. The nozzle includes a nozzle panel and a nozzle fairing fixedly connected to the nozzle panel at an axial end of the nozzle. The nozzle is configured with an internal flow passage radially between the nozzle panel and the nozzle fairing. The internal flow passage extends axially within the nozzle to an outlet between the nozzle panel and the nozzle fairing at the axial end of the nozzle.
    Type: Application
    Filed: May 4, 2021
    Publication date: November 11, 2021
    Inventors: Adam Saunders, Bryce T. Kelford, Travis M. Frazier, Richard Haslim, Richard S. Alloway, Vijay V. Pujar
  • TRANSPIRATIONALLY COOLED EXHAUST CENTER BODY FOR AN AIRCRAFT PROPULSION SYSTEM
    Publication number: 20210310411
    Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes an exhaust center body and a duct system. The exhaust center body includes an exterior skin. The duct system is fluidly coupled with a plurality of exterior skin perforations in the exterior skin. The duct system is configured to direct bypass air received from a bypass flow path within the aircraft propulsion system to the exterior skin perforations.
    Type: Application
    Filed: April 7, 2021
    Publication date: October 7, 2021
    Inventors: Bryce T. Kelford, Adam Saunders, Richard S. Alloway, Richard Haslim, Travis M. Frazier