Patents by Inventor Michael F. BRYANT

Michael F. BRYANT 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).

  • Patent number: 10196896
    Abstract: A rotor stage (100) of a gas turbine engine (10) comprises a platform (120) from which rotor blades extend. The platform is provided with a circumferentially extending damper ring (200), the damper ring having an engagement surface (210) that engages with a platform engagement surface (110) of the platform (120). In use, the damper engagement surface (210) and the platform engagement surface (110) move relative to each other in a radial direction, in response to diametral mode excitation. This causes friction between the two surfaces, thereby dissipating energy and damping the excitation. The rotor stage (100) is arranged such that the engagement load between the damper engagement surface (210) and the platform engagement surface (110) is a function of the rotational speed of the rotor stage (100).
    Type: Grant
    Filed: April 8, 2016
    Date of Patent: February 5, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Michael F Bryant, Garry M Edwards
  • Publication number: 20160298459
    Abstract: A rotor stage of a gas turbine engine includes a platform from which rotor blades extend. The platform is provided with a circumferentially extending damper ring, the damper ring having an engagement surface that engages with a platform engagement surface of the platform. The platform engagement surface and the damper engagement surface can move relative to each other in the radial direction. In use, the damper engagement surface moves less in the radial direction than the platform engagement surface in response to diametral mode excitation. This causes friction between the two surfaces, thereby dissipating energy and damping the excitation. The platform engagement surface and the damper engagement surface engage over at least two separate engagement portions separated by a gap.
    Type: Application
    Filed: April 8, 2016
    Publication date: October 13, 2016
    Applicant: ROLLS-ROYCE plc
    Inventors: Michael F. BRYANT, Garry M. EDWARDS
  • Publication number: 20160298460
    Abstract: A rotor stage (100) of a gas turbine engine (10) comprises a platform (120) from which rotor blades extend. The platform is provided with a circumferentially extending damper ring (200), the damper ring having an engagement surface (210) that engages with a platform engagement surface (110) of the platform (120). In use, the damper engagement surface (210) and the platform engagement surface (110) move relative to each other in a radial direction, in response to diametral mode excitation. This causes friction between the two surfaces, thereby dissipating energy and damping the excitation. The rotor stage (100) is arranged such that the engagement load between the damper engagement surface (210) and the platform engagement surface (110) is a function of the rotational speed of the rotor stage (100).
    Type: Application
    Filed: April 8, 2016
    Publication date: October 13, 2016
    Applicant: ROLLS-ROYCE PLC
    Inventors: Michael F BRYANT, Garry M. EDWARDS