Patents by Inventor Jean-Michel Bazet

Jean-Michel Bazet 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: 20220024568
    Abstract: The present disclosure relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterized in that it comprises: at least one hybrid turboshaft engine capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems for controlling each hybrid turboshaft engine, each system comprising an electric machine connected to the hybrid turboshaft engine and suitable for rotating the gas generator thereof, and at least one source of electrical power for the electric machine, each reactivation system being configured such that it can drive the turboshaft engine in at least one operating mode among a plurality of predetermined modes.
    Type: Application
    Filed: October 4, 2021
    Publication date: January 27, 2022
    Applicants: SAFRAN HELICOPTER ENGINES, SAFRAN ELECTRICAL & POWER
    Inventors: Philippe Vallart, Jean-Michel Bazet, Loic LeDuigou
  • Patent number: 11198505
    Abstract: The invention relates to a method for controlling an emergency device of a helicopter, said helicopter comprising a rotor suitable for being rotated, said emergency device being suitable for supplying additional emergency propulsion power to the helicopter, in said method comprising a step (10) of measuring the rotation speed of the helicopter rotor, a step (12) of calculating the drift of the measured rotation speed, a step (20) of continuously verifying conditions such that the speed of rotation of the rotor is higher than a predetermined value, referred to as arming speed, and the drift of the rotation speed is lower than a predetermined value, referred to as arming drift, and a step (22) of activating the emergency device if the verified conditions are validated.
    Type: Grant
    Filed: February 14, 2018
    Date of Patent: December 14, 2021
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Jean Michel Bazet, Jean-Luc Charles Gilbert Frealle, Pierre Darfeuil
  • Patent number: 11161603
    Abstract: The invention relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterised in that it comprises: at least one hybrid turboshaft engine (20) capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems (30; 40) for controlling each hybrid turboshaft engine (20), each system (30; 40) comprising an electric machine (31; 41) connected to the hybrid turboshaft engine (20) and suitable for rotating the gas generator thereof, and at least one source (33; 43) of electrical power for said electric machine (31; 41), each reactivation system (30; 40) being configured such that it can drive said turboshaft engine (20) in at least one operating mode among a plurality of predetermined modes.
    Type: Grant
    Filed: October 6, 2015
    Date of Patent: November 2, 2021
    Assignees: SAFRAN HELICOPTER ENGINES, SAFRAN ELECTRICAL & POWER
    Inventors: Philippe Vallart, Jean-Michel Bazet, Loïc Le Duigou
  • Publication number: 20190337611
    Abstract: The invention relates to a method for controlling an emergency device of a helicopter, said helicopter comprising a rotor suitable for being rotated, said emergency device being suitable for supplying additional emergency propulsion power to the helicopter, in said method comprising a step (10) of measuring the rotation speed of the helicopter rotor, a step (12) of calculating the drift of the measured rotation speed, a step (20) of continuously verifying conditions such that the speed of rotation of the rotor is higher than a predetermined value, referred to as arming speed, and the drift of the rotation speed is lower than a predetermined value, referred to as arming drift, and a step (22) of activating the emergency device if the verified conditions are validated.
    Type: Application
    Filed: February 14, 2018
    Publication date: November 7, 2019
    Inventors: Romain THIRIET, Jean Michel BAZET, Jean-Luc Charles Gilbert FREALLE, Pierre DARFEUIL
  • 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: 10253699
    Abstract: A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter, includes a pneumatic turbine that is mechanically connected to the turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurized air from the turboshaft engine and a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas. The device further includes a sensor for determining the rotational speed of the pneumatic turbine.
    Type: Grant
    Filed: September 21, 2015
    Date of Patent: April 9, 2019
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Jean-Michel Bazet, Camel Serghine, Patrick Marconi, Jérôme Irigoyen, Stephen Langford
  • 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
  • Patent number: 9982758
    Abstract: A transmission assembly for an aircraft, and a helicopter including such an assembly for controlling independently the speed of rotation of an engine and of a torque receiver. According to the invention, the assembly comprises a first inlet shaft (10a) configured to receive torque from a first engine (10), an outlet shaft (60a) configured to transmit torque to a torque receiver (60), a first transmission member (20) having at least two degrees of freedom and comprising first, second, and third movable portions, a first reversible electrical regulator machine (30), and a first reversible electrical balancing machine (40), wherein the inlet shaft (10a) is coupled to the first movable portion, the outlet shaft (60a) is coupled to the second movable portion, the first electrical regulator machine (30) is coupled to the third movable portion, and the first electrical balancing machine (40) is coupled in series with the inlet shaft or the outlet shaft (60a).
    Type: Grant
    Filed: March 20, 2015
    Date of Patent: May 29, 2018
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Stéphane Beddok, Jean-Michel Bazet
  • Publication number: 20170305541
    Abstract: The invention relates to an architecture of a propulsion system of a multi-engine helicopter comprising turboshaft engines connected to a power transmission gearbox, characterised in that it comprises: at least one hybrid turboshaft engine (20) capable of operating in at least one standby mode during a stable cruise flight of the helicopter; at least two systems (30; 40) for controlling each hybrid turboshaft engine (20), each system (30; 40) comprising an electric machine (31; 41) connected to the hybrid turboshaft engine (20) and suitable for rotating the gas generator thereof, and at least one source (33; 43) of electrical power for said electric machine (31; 41), each reactivation system (30; 40) being configured such that it can drive said turboshaft engine (20) in at least one operating mode among a plurality of predetermined modes.
    Type: Application
    Filed: October 6, 2015
    Publication date: October 26, 2017
    Applicants: SAFRAN HELICOPTER ENGINES, SAFRAN ELECTRICAL & POWER
    Inventors: Philippe Vallart, Jean-Michel Bazet, Loïc Le Duigou
  • 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: 20170218847
    Abstract: A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter includes a pneumatic turbine that is mechanically connected to said turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurised air from the turboshaft engine; a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas The device further includes a sensor for determining the rotational speed of the pneumatic turbine.
    Type: Application
    Filed: September 21, 2015
    Publication date: August 3, 2017
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Romain Thiriet, Jean-Michel Bazet, Camel Serghine, Patrick Marconi, Jérôme Irigoyen, Stephen Langford
  • 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: 20170175856
    Abstract: A transmission assembly for an aircraft, and a helicopter including such an assembly for controlling independently the speed of rotation of an engine and of a torque receiver. According to the invention, the assembly comprises a first inlet shaft (10a) configured to receive torque from a first engine (10), an outlet shaft (60a) configured to transmit torque to a torque receiver (60), a first transmission member (20) having at least two degrees of freedom and comprising first, second, and third movable portions, a first reversible electrical regulator machine (30), and a first reversible electrical balancing machine (40), wherein the inlet shaft (10a) is coupled to the first movable portion, the outlet shaft (60a) is coupled to the second movable portion, the first electrical regulator machine (30) is coupled to the third movable portion, and the first electrical balancing machine (40) is coupled in series with the inlet shaft or the outlet shaft (60a).
    Type: Application
    Filed: March 20, 2015
    Publication date: June 22, 2017
    Applicant: SAFRAN HELICOPTER ENGINES
    Inventors: Stéphane BEDDOK, Jean-Michel BAZET
  • Patent number: 6700805
    Abstract: An electrical power supply apparatus, especially for a motor vehicle electrical system, comprising at least two power supply sources (1, 2) which are both connected between ground and a supply line, and each of which comprises at least one induced current winding and a bridge of rectifier elements (P1, P2), characterised in that one of the two said sources comprises an auxiliary bridge of rectifier elements of positive type (Paux1), the other one comprising an auxiliary bridge of rectifier elements of negative type (Paux2), with means (I; Dc1, Dc2, Dc3; Id), connected to each of the said two bridges and being adapted to be controlled for the purpose of: in a first state, connecting the two auxiliary bridges (Paux1; Paux2) in series, the rectified voltage supplied to the power supply line then being the sum of the voltages supplied by the induced current winding or windings of each of the two sources and then rectified, in a second state, blocking the connection between the two auxiliary bridges (Paux1; Paux
    Type: Grant
    Filed: November 15, 2001
    Date of Patent: March 2, 2004
    Assignee: Valeo Equipments Electriques Moteur
    Inventors: Cédric Plasse, Jean-Michel Bazet, David Huart, Marcel Vogelsberger
  • Publication number: 20020159278
    Abstract: An electrical power supply apparatus, especially for a motor vehicle electrical system, comprising at least two power supply sources (1, 2) which are both connected between ground and a supply line, and each of which comprises at least one induced current winding and a bridge of rectifier elements (P1, P2), characterised in that one of the two said sources comprises an auxiliary bridge of rectifier elements of positive type (Paux1), the other one comprising an auxiliary bridge of rectifier elements of negative type (Paux2), with means (I; Dc1, Dc2, Dc3; Id), connected to each of the said two bridges and being adapted to be controlled for the purpose of:
    Type: Application
    Filed: November 15, 2001
    Publication date: October 31, 2002
    Inventors: Cedric Plasse, Jean-Michel Bazet, David Huart, Marcel Vogelsberger