Patents by Inventor Martin Clermont

Martin Clermont 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).

  • Propeller blade angle feedback arrangement and method
    Patent number: 11780561
    Abstract: There is provided a blade angle feedback assembly for a propeller of an aircraft engine. The propeller is rotatable about an axis and has propeller blades rotatable about respective spanwise axes to adjust a blade angle thereof. The blade angle feedback assembly comprises a feedback ring having a plurality of position markers disposed thereon, at least one sensor configured to provide feedback on the blade angle of the propeller blades by detecting a relative movement between the feedback ring and the at least one sensor, and at least one shielding element provided between the feedback ring and the propeller, the at least one shielding element configured to shield the feedback ring from electromagnetism.
    Type: Grant
    Filed: May 21, 2021
    Date of Patent: October 10, 2023
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Joseph Ernesto Marone, Ella Yakobov, Ian Farrell, Olivier Basse, Martin Dobson, Martin Clermont, Marc Lavoie
  • Propeller blade angle feedback arrangement and method
    Patent number: 11279465
    Abstract: A blade angle feedback ring assembly for an aircraft engine propeller having adjustable angle blades is provided. The feedback ring assembly comprises a feedback ring coupled to rotate with the propeller, the engine configured such that a first electrically-conductive path is defined between the propeller and the engine via the feedback ring, and an electric current conduction element provided between the propeller and the engine to define a second electrically-conductive path between the propeller and the engine in parallel to the first path, the second electrically-conductive path configured with a lower electrical resistance to conduction between the propeller and the engine than the first electrically-conductive path.
    Type: Grant
    Filed: July 16, 2018
    Date of Patent: March 22, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Joseph Ernesto Marone, Olivier Basse, Martin Dobson, Martin Clermont, Marc Lavoie
  • PROPELLER BLADE ANGLE FEEDBACK ARRANGEMENT AND METHOD
    Publication number: 20210284322
    Abstract: There is provided a blade angle feedback assembly for a propeller of an aircraft engine. The propeller is rotatable about an axis and has propeller blades rotatable about respective spanwise axes to adjust a blade angle thereof. The blade angle feedback assembly comprises a feedback ring having a plurality of position markers disposed thereon, at least one sensor configured to provide feedback on the blade angle of the propeller blades by detecting a relative movement between the feedback ring and the at least one sensor, and at least one shielding element provided between the feedback ring and the propeller, the at least one shielding element configured to shield the feedback ring from electromagnetism.
    Type: Application
    Filed: May 21, 2021
    Publication date: September 16, 2021
    Inventors: Joseph Ernesto Marone, Ella Yakobov, Ian Farrell, Olivier Basse, Martin Dobson, Martin Clermont, Marc Lavoie
  • PROPELLER BLADE ANGLE FEEDBACK ARRANGEMENT AND METHOD
    Publication number: 20200017195
    Abstract: A blade angle feedback ring assembly for an aircraft engine propeller having adjustable angle blades is provided. The feedback ring assembly comprises a feedback ring coupled to rotate with the propeller, the engine configured such that a first electrically-conductive path is defined between the propeller and the engine via the feedback ring, and an electric current conduction element provided between the propeller and the engine to define a second electrically-conductive path between the propeller and the engine in parallel to the first path, the second electrically-conductive path configured with a lower electrical resistance to conduction between the propeller and the engine than the first electrically-conductive path.
    Type: Application
    Filed: July 16, 2018
    Publication date: January 16, 2020
    Inventors: Joseph Ernesto MARONE, Olivier BASSE, Martin DOBSON, Martin CLERMONT, Marc LAVOIE
  • Turbine shroud segment feather seal located in radial shroud legs
    Patent number: 7374395
    Abstract: A turbine shroud assembly is configured to adequately adjust a distribution of cooling air flow such that air leakage between radial shroud legs of adjacent shroud segments is minimized, while permitting cooling air to leak between platforms of adjacent shroud segments in order to cool sides of the platforms thereof.
    Type: Grant
    Filed: July 19, 2005
    Date of Patent: May 20, 2008
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Martin Clermont
  • Turbine shroud segment feather seal located in radial shroud legs
    Publication number: 20070020087
    Abstract: A turbine shroud assembly is configured to adequately adjust a distribution of cooling air flow such that air leakage between radial shroud legs of adjacent shroud segments is minimized, while permitting cooling air to leak between platforms of adjacent shroud segments in order to cool sides of the platforms thereof.
    Type: Application
    Filed: July 19, 2005
    Publication date: January 25, 2007
    Inventors: Eric Durocher, Martin Clermont