Patents by Inventor Jean Philippe Pierre-Alain REIGNER

Jean Philippe Pierre-Alain REIGNER 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).

  • Turbine engine with a pair of contrarotating propellers placed upstream of the gas generator
    Patent number: 10584641
    Abstract: Engine comprising a propeller unit with a pair of contrarotating propellers (31, 32), a gas generator (5) supplying a power turbine (53), the pair of propellers being rotationally driven by the shaft (53A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset (7) and a first stage (6) comprising a simple gearset connecting the turbine shaft (53A) and the differential gearset (7), the engine air intake comprising an air intake duct (11), the air intake duct (11) being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset (7).
    Type: Grant
    Filed: April 14, 2016
    Date of Patent: March 10, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Didier Rene Andre Escure, Jean-Francois Endy Bersot, Tewfik Boudebiza, Gilles Alain Charier, Thomas Julien Nguyen Van, Jean Philippe Pierre-Alain Reigner
  • TURBINE ENGINE WITH A PAIR OF CONTRAROTATING PROPELLERS PLACED UPSTREAM OF THE GAS GENERATOR
    Publication number: 20180128183
    Abstract: Engine comprising a propeller unit with a pair of contrarotating propellers (31, 32), a gas generator (5) supplying a power turbine (53), the pair of propellers being rotationally driven by the shaft (53A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset (7) and a first stage (6) comprising a simple gearset connecting the turbine shaft (53A) and the differential gearset (7), the engine air intake comprising an air intake duct (11), the air intake duct (11) being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset (7).
    Type: Application
    Filed: April 14, 2016
    Publication date: May 10, 2018
    Inventors: Didier Rene Andre ESCURE, Jean-Francois Endy BERSOT, Tewfik BOUDEBIZA, Gilles Alain CHARIER, Thomas Julien NGUYEN VAN, Jean Philippe Pierre-Alain REIGNER