Patents by Inventor Vincent POUMAREDE

Vincent POUMAREDE 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).

  • Publication number: 20220212547
    Abstract: A hybrid propulsion installation for an aircraft, including an internal combustion engine having at least one combustion chamber; at least one electricity generator; an electrical propulsion system; electromechanical protection mechanism arranged between the or each electricity generator and the electrical propulsion system; wherein the installation also includes: an electronic computer configured to: receive at least one piece of information on a position of the electromechanical protection mechanism; receive at least one piece of information on a speed of rotation of a shaft of the internal combustion engine; and control the flow of fuel supplying the combustion chamber depending on the information received.
    Type: Application
    Filed: April 10, 2020
    Publication date: July 7, 2022
    Inventors: Vincent POUMAREDE, Jean-Philippe Jacques MARIN
  • Publication number: 20220204173
    Abstract: An electrical energy supply network of an aircraft equipped with a plurality of electrical loads to be supplied includes at least two generators of a turbogenerator of the aircraft, each suitable for providing an electrical energy source, and at least one stator associated with a rectifier. The stators of the generators are mounted in parallel on at least two distribution buses designed to supply the plurality of electrical loads. The supply network also includes contactors suitable for electrically connecting or disconnecting the distribution buses from each other.
    Type: Application
    Filed: April 23, 2020
    Publication date: June 30, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Barraco, Thomas Klonowski, Vincent Poumarede
  • Publication number: 20220185497
    Abstract: Methods for controlling an electrical power supply network for an aircraft, include pre-charging at least one capacitor in a normal operating mode when a gas turbine is available, pre-charging the at least one capacitor in a backup operating mode when the gas turbine is not available, and discharging the at least one capacitor at the end of use of the electrical power supply network when the at least one capacitor is charged.
    Type: Application
    Filed: April 10, 2020
    Publication date: June 16, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas Barraco, Thomas Klonowski, Vincent Poumarede
  • Publication number: 20220178311
    Abstract: A method for controlling a non-propulsive power generation turbine engine configured to supply power to a plurality of propulsion rotors of an aircraft, each propulsion rotor being connected to a power distribution module through at least one power supply bus, the turbine engine supplying each power supply bus via the power distribution module at a supply rate, the control method comprising a step of determining the power requirement of each power supply bus depending on the power requirement of each propulsion rotor, a step of determining the basic power requirement of each power supply bus, a step of determining the overall power requirement based on all the basic power requirements of the power supply buses and a step of determining an anticipation parameter based on the overall power requirement.
    Type: Application
    Filed: March 20, 2020
    Publication date: June 9, 2022
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Stéphane Meyer Beddok, Vincent Poumarede
  • Patent number: 10753280
    Abstract: A field of turbine engines, and more particularly to an engine including a compressor; a combustion chamber; a first turbine connected to the compressor by a first rotary shaft; an actuator device for actuating the first rotary shaft in order to keep the first turbine and the compressor in rotation while the combustion chamber is extinguished; and a lubrication circuit for lubricating the engine. The circuit passes through at least one heat source suitable for heating the lubricant in the lubrication circuit while the first turbine and the compressor are rotating with the combustion chamber extinguished.
    Type: Grant
    Filed: September 29, 2014
    Date of Patent: August 25, 2020
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Vincent Poumarede, Camel Serghine
  • Patent number: 10450962
    Abstract: There is provided a starting system for reliably starting a turbine engine, the system including first and second circuits connected in parallel and arranged between a battery of the engine and a DC starter of the engine, the first circuit including a DC-DC converter connected in series with a first switch and the second circuit including a second switch; a sensor configured to sense a speed of rotation of a compressor of the engine; a sensor configured to sense a temperature at an inlet to a free turbine of the engine; and a control circuit configured to control the first and second switches as a function of information supplied by the sensor configured to sense the speed of rotation of the compressor and by the sensor configured to sense the inlet temperature of the free turbine.
    Type: Grant
    Filed: December 15, 2014
    Date of Patent: October 22, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Vincent Poumarede, Pierre Harriet
  • Patent number: 10435167
    Abstract: The invention relates to a method for automatically controlling an operating mode of a turboshaft engine of a helicopter, comprising a step (10) of receiving data (27, 28, 29) that are representative of the flight of the helicopter; a step (11) of selecting the turboshaft engine for which a change of mode would be most relevant; a step (12) of determining an operating mode of said turboshaft engine, known as the selected mode, selected from a plurality of predetermined operating modes; and a step (14) of ordering the operating mode of said turboshaft engine into said selected mode. The invention also relates to a corresponding control device.
    Type: Grant
    Filed: December 15, 2014
    Date of Patent: October 8, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Caroline Seve, Vincent Poumarede
  • Patent number: 10294868
    Abstract: An assistance device for an aircraft free-turbine turbine engine, the device including first electrical power supply for powering a winding of a starter rotary machine, referred to as a “first” winding, in order to provide first assistance in accelerating the gas generator of the engine. The device further includes a monitor for monitoring the first assistance, and a second power supply for electrically powering a second winding of the rotary machine to provide second assistance in accelerating the gas generator if the monitor observes that the first assistance is insufficient.
    Type: Grant
    Filed: March 26, 2015
    Date of Patent: May 21, 2019
    Assignee: Safran Helicopter Engines
    Inventors: Vincent Poumarede, Jean-Michel Bazet, Thomas Klonowski
  • Patent number: 10151246
    Abstract: An assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines, the device including an electrical starter machine for providing prolonged assistance to the gas generator of a first engine using energy produced by an electric generator machine driven by the second engine, the device further including at least one electricity storage member electrically connected to the electrical starter machine for providing a burst of assistance to the gas generator, wherein the electrical starter machine is powered by a first power converter enabling it to exchange energy with the storage member for providing the burst of assistance, and that transmits thereto the energy supplied by a second power converter for the prolonged assistance.
    Type: Grant
    Filed: March 26, 2015
    Date of Patent: December 11, 2018
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Vincent Poumarede, Thomas Klonowski, Fabien Mercier-Calvairac, Camel Serghine
  • Patent number: 10054053
    Abstract: A field of turbine engines, and more particularly to an engine including a compressor; a combustion chamber; a first turbine connected to the compressor by a first rotary shaft; an actuator device for actuating the first rotary shaft in order to keep the first turbine and the compressor in rotation while the combustion chamber is extinguished; and a lubrication circuit for lubricating the engine. The circuit passes through at least one heat source suitable for heating the lubricant in the lubrication circuit while the first turbine and the compressor are rotating with the combustion chamber extinguished.
    Type: Grant
    Filed: September 29, 2014
    Date of Patent: August 21, 2018
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Vincent Poumarede, Camel Serghine
  • Publication number: 20180187604
    Abstract: An assistance device for a free-turbine engine of an aircraft having at least two free-turbine engines, the device including an electrical starter machine for providing prolonged assistance to the gas generator of a first engine using energy produced by an electric generator machine driven by the second engine, the device further including at least one electricity storage member electrically connected to the electrical starter machine for providing a burst of assistance to the gas generator, wherein the electrical starter machine is powered by a first power converter enabling it to exchange energy with the storage member for providing the burst of assistance, and that transmits thereto the energy supplied by a second power converter for the prolonged assistance.
    Type: Application
    Filed: March 26, 2015
    Publication date: July 5, 2018
    Inventors: Vincent POUMAREDE, Thomas KLONOWSKI, Fabien MERCIER-CALVAIRAC, Camel SERGHINE
  • Publication number: 20180171874
    Abstract: The system for rapidly reactivating a turbine engine of an aircraft includes an electrical machine that is DC powered from an on-board electrical power supply network. The system also includes a switch interposed between the on-board network and the electrical machine, an additional set including a plurality N electrical energy storage elements, and a control unit for controlling a device for discharging the storage elements and adapted to enable a series circuit including at least some of the N electrical energy storage elements to be connected in parallel with the on-board network so that when the rapid reactivation system is in operation the electrical machine is powered by a voltage level higher than the voltage level of its nominal characteristics.
    Type: Application
    Filed: March 19, 2015
    Publication date: June 21, 2018
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Thomas KLONOWSKI, Jean-Michel BAZET, Vincent POUMAREDE, Pierre HARRIET
  • Publication number: 20170292491
    Abstract: A system for igniting a combustion chamber of a turboshaft engine, comprising: a plurality of start-up injectors which are suitable for injecting fuel into said chamber during a combustion-initiating phase; a circuit for supplying fuel to said start-up injectors, comprising a first sub-circuit, referred to as the primary start-up circuit, designed to supply fuel to some of said plurality of start-up injectors; a second sub-circuit, referred to as the secondary start-up circuit, designed to supply fuel to the other start-up injectors of said plurality.
    Type: Application
    Filed: October 6, 2015
    Publication date: October 12, 2017
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Romain THIRIET, Jean-Michel BAZET, Guillaume COTTIN, Camel SERGHINE, Patrick MARCONI, Bertrand MOINE, Vincent POUMAREDE
  • Publication number: 20170184032
    Abstract: An assistance device for an aircraft free-turbine turbine engine, the device including first electrical power supply for powering a winding of a starter rotary machine, referred to as a “first” winding, in order to provide first assistance in accelerating the gas generator of the engine. The device further includes a monitor for monitoring the first assistance, and a second power supply for electrically powering a second winding of the rotary machine to provide second assistance in accelerating the gas generator if the monitor observes that the first assistance is insufficient.
    Type: Application
    Filed: March 26, 2015
    Publication date: June 29, 2017
    Inventors: Vincent POUMAREDE, Jean-Michel Bazet, Thomas Klonowski
  • Publication number: 20170002744
    Abstract: There is provided a starting system for reliably starting a turbine engine, the system including first and second circuits connected in parallel and arranged between a battery of the engine and a DC starter of the engine, the first circuit including a DC-DC converter connected in series with a first switch and the second circuit including a second switch; a sensor configured to sense a speed of rotation of a compressor of the engine; a sensor configured to sense a temperature at an inlet to a free turbine of the engine; and a control circuit configured to control the first and second switches as a function of information supplied by the sensor configured to sense the speed of rotation of the compressor and by the sensor configured to sense the inlet temperature of the free turbine.
    Type: Application
    Filed: December 15, 2014
    Publication date: January 5, 2017
    Applicant: TURBOMECA
    Inventors: Vincent POUMAREDE, Pierre HERRIET
  • Publication number: 20160311548
    Abstract: The invention relates to a method for automatically controlling an operating mode of a turboshaft engine of a helicopter, comprising a step (10) of receiving data (27, 28, 29) that are representative of the flight of the helicopter; a step (11) of selecting the turboshaft engine for which a change of mode would be most relevant; a step (12) of determining an operating mode of said turboshaft engine, known as the selected mode, selected from a plurality of predetermined operating modes; and a step (14) of ordering the operating mode of said turboshaft engine into said selected mode. The invention also relates to a corresponding control device.
    Type: Application
    Filed: December 15, 2014
    Publication date: October 27, 2016
    Inventors: Romain THIRIET, Caroline SEVE, Vincent POUMAREDE
  • Publication number: 20160237900
    Abstract: A field of turbine engines, and more particularly to an engine including a compressor; a combustion chamber; a first turbine connected to the compressor by a first rotary shaft; an actuator device for actuating the first rotary shaft in order to keep the first turbine and the compressor in rotation while the combustion chamber is extinguished; and a lubrication circuit for lubricating the engine. The circuit passes through at least one heat source suitable for heating the lubricant in the lubrication circuit while the first turbine and the compressor are rotating with the combustion chamber extinguished.
    Type: Application
    Filed: September 29, 2014
    Publication date: August 18, 2016
    Applicant: TURBOMECA
    Inventors: Romain THIRIET, Vincent POUMAREDE, Camel SERGHINE
  • Publication number: 20160230671
    Abstract: A field of turbine engines, and more particularly to an engine including a compressor; a combustion chamber; a first turbine connected to the compressor by a first rotary shaft; an actuator device for actuating the first rotary shaft in order to keep the first turbine and the compressor in rotation while the combustion chamber is extinguished; and a lubrication circuit for lubricating the engine. The circuit passes through at least one heat source suitable for heating the lubricant in the lubrication circuit while the first turbine and the compressor are rotating with the combustion chamber extinguished.
    Type: Application
    Filed: September 29, 2014
    Publication date: August 11, 2016
    Applicant: TURBOMECA
    Inventors: Romain THIRIET, Vincent POUMAREDE, Camel SERGHINE