Patents by Inventor Rémy Henri Pierre Princivalle

Rémy Henri Pierre Princivalle 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).

  • METHOD AND SYSTEM FOR REGULATING THE THRUST OF AN AIRCRAFT TURBOMACHINE
    Publication number: 20230366358
    Abstract: A method and system control the thrust of an aircraft turbomachine having a high bypass ratio by direct action on a variable-pitch system. The variable-pitch system varies the pitch of the vanes of a stator of a low-pressure compressor for the open-loop control of the thrust of the turbomachine. The method also provides closed-loop control of the pitch of the blades of a propeller based on a rotational speed of the propeller.
    Type: Application
    Filed: August 10, 2021
    Publication date: November 16, 2023
    Applicant: SAFRAN AERO BOOSTERS
    Inventor: Rémy Henri Pierre PRINCIVALLE
  • Transonic turbomachine compressor
    Patent number: 11781562
    Abstract: A transonic compressor of a turbomachine comprising exactly two or exactly three annular rows of rotor blades and respectively exactly one or exactly two annular rows of intermediate stator vanes interposed between two respective rows of rotor blades, wherein the flow velocity relative to the rotor downstream of the intermediate stator vanes is less than or equal to a Mach number of 0.9 over a radial portion of the blades extending over the radially inner 40% of the blades, and less than or equal to a Mach number of 1 over a radial portion extending over the radially inner 80% of the blades, and less than or equal to a Mach number of 1.05 over a radial portion extending over the radially outer 20% of the blades.
    Type: Grant
    Filed: February 26, 2021
    Date of Patent: October 10, 2023
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Rémy Henri Pierre Princivalle
  • TRANSONIC TURBOMACHINE COMPRESSOR
    Publication number: 20230057786
    Abstract: A transonic compressor of a turbomachine comprising exactly two or exactly three annular rows of rotor blades and respectively exactly one or exactly two annular rows of intermediate stator vanes interposed between two respective rows of rotor blades, wherein the flow velocity relative to the rotor downstream of the intermediate stator vanes is less than or equal to a Mach number of 0.9 over a radial portion of the blades extending over the radially inner 40% of the blades, and less than or equal to a Mach number of 1 over a radial portion extending over the radially inner 80% of the blades, and less than or equal to a Mach number of 1.05 over a radial portion extending over the radially outer 20% of the blades.
    Type: Application
    Filed: February 26, 2021
    Publication date: February 23, 2023
    Inventor: Rémy Henri Pierre PRINCIVALLE
  • HEAT EXCHANGE DEVICE AND AIRCRAFT TURBINE ENGINE WITH THE DEVICE
    Publication number: 20220356844
    Abstract: Heat exchange devices for aircraft turbine engines include a heat exchanger and an inlet scoop comprising an air intake configured for supplying the heat exchanger. The air intake of the inlet scoop is divided into several mouthpieces, each defining an air flux supplying the heat exchanger.
    Type: Application
    Filed: May 4, 2022
    Publication date: November 10, 2022
    Applicant: SAFRAN AERO BOOSTERS S.A.
    Inventors: Gilles Ayoub, David Weicker, Alexandre Carre, Rémy Henri Pierre Princivalle