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).
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Patent number: 11905893Abstract: 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: GrantFiled: March 20, 2020Date of Patent: February 20, 2024Assignee: SAFRAN HELICOPTER ENGINESInventors: Stéphane Meyer Beddok, Vincent Poumarede
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Publication number: 20240052783Abstract: A method for igniting a continuous combustion engine including an electronic engine control member, a high energy box, a spark plug ignition circuit and a fuel solenoid valve, cooperating with a starter motor, the method being implemented by the electronic engine control member and including precharging the high energy box before an engine starting procedure, activated on an engine starting command, the precharging being controlled by switching on the electronic engine control member, or by putting the engine in idle mode.Type: ApplicationFiled: December 20, 2021Publication date: February 15, 2024Inventors: Eric Michel BONDIVENNE, Vincent POUMAREDE
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Publication number: 20220212547Abstract: 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: ApplicationFiled: April 10, 2020Publication date: July 7, 2022Inventors: Vincent POUMAREDE, Jean-Philippe Jacques MARIN
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Publication number: 20220204173Abstract: 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: ApplicationFiled: April 23, 2020Publication date: June 30, 2022Applicant: SAFRAN HELICOPTER ENGINESInventors: Thomas Barraco, Thomas Klonowski, Vincent Poumarede
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Publication number: 20220185497Abstract: 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: ApplicationFiled: April 10, 2020Publication date: June 16, 2022Applicant: SAFRAN HELICOPTER ENGINESInventors: Thomas Barraco, Thomas Klonowski, Vincent Poumarede
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Publication number: 20220178311Abstract: 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: ApplicationFiled: March 20, 2020Publication date: June 9, 2022Applicant: SAFRAN HELICOPTER ENGINESInventors: Stéphane Meyer Beddok, Vincent Poumarede
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Patent number: 10753280Abstract: 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: GrantFiled: September 29, 2014Date of Patent: August 25, 2020Assignee: SAFRAN HELICOPTER ENGINESInventors: Romain Thiriet, Vincent Poumarede, Camel Serghine
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Patent number: 10450962Abstract: 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: GrantFiled: December 15, 2014Date of Patent: October 22, 2019Assignee: SAFRAN HELICOPTER ENGINESInventors: Vincent Poumarede, Pierre Harriet
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Patent number: 10435167Abstract: 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: GrantFiled: December 15, 2014Date of Patent: October 8, 2019Assignee: SAFRAN HELICOPTER ENGINESInventors: Romain Thiriet, Caroline Seve, Vincent Poumarede
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Patent number: 10294868Abstract: 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: GrantFiled: March 26, 2015Date of Patent: May 21, 2019Assignee: Safran Helicopter EnginesInventors: Vincent Poumarede, Jean-Michel Bazet, Thomas Klonowski
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Patent number: 10151246Abstract: 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: GrantFiled: March 26, 2015Date of Patent: December 11, 2018Assignee: SAFRAN HELICOPTER ENGINESInventors: Vincent Poumarede, Thomas Klonowski, Fabien Mercier-Calvairac, Camel Serghine
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Patent number: 10054053Abstract: 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: GrantFiled: September 29, 2014Date of Patent: August 21, 2018Assignee: SAFRAN HELICOPTER ENGINESInventors: Romain Thiriet, Vincent Poumarede, Camel Serghine
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Publication number: 20180187604Abstract: 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: ApplicationFiled: March 26, 2015Publication date: July 5, 2018Inventors: Vincent POUMAREDE, Thomas KLONOWSKI, Fabien MERCIER-CALVAIRAC, Camel SERGHINE
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Publication number: 20180171874Abstract: 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: ApplicationFiled: March 19, 2015Publication date: June 21, 2018Applicant: SAFRAN HELICOPTER ENGINESInventors: Thomas KLONOWSKI, Jean-Michel BAZET, Vincent POUMAREDE, Pierre HARRIET
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Publication number: 20170292491Abstract: 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: ApplicationFiled: October 6, 2015Publication date: October 12, 2017Applicant: SAFRAN HELICOPTER ENGINESInventors: Romain THIRIET, Jean-Michel BAZET, Guillaume COTTIN, Camel SERGHINE, Patrick MARCONI, Bertrand MOINE, Vincent POUMAREDE
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Publication number: 20170184032Abstract: 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: ApplicationFiled: March 26, 2015Publication date: June 29, 2017Inventors: Vincent POUMAREDE, Jean-Michel Bazet, Thomas Klonowski
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Publication number: 20170002744Abstract: 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: ApplicationFiled: December 15, 2014Publication date: January 5, 2017Applicant: TURBOMECAInventors: Vincent POUMAREDE, Pierre HERRIET
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Publication number: 20160311548Abstract: 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: ApplicationFiled: December 15, 2014Publication date: October 27, 2016Inventors: Romain THIRIET, Caroline SEVE, Vincent POUMAREDE
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Publication number: 20160237900Abstract: 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: ApplicationFiled: September 29, 2014Publication date: August 18, 2016Applicant: TURBOMECAInventors: Romain THIRIET, Vincent POUMAREDE, Camel SERGHINE
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Publication number: 20160230671Abstract: 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: ApplicationFiled: September 29, 2014Publication date: August 11, 2016Applicant: TURBOMECAInventors: Romain THIRIET, Vincent POUMAREDE, Camel SERGHINE