Patents by Inventor Fabien Mercier-Calvairac
Fabien Mercier-Calvairac 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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Publication number: 20240092497Abstract: Propulsion system (2) for a helicopter (1) comprising a main engine (9), a main rotor (3), a main gearbox (4) including an output mechanically connected to the main rotor (3), a reduction gearbox (13) mechanically coupled between the main engine (9) and a first input of the main gearbox (4), and an assistance device (10). The assistance device (10) comprises a first electric machine mechanically coupled to the reduction gearbox (13) and configured to operate as an electric generator to take off energy produced by the main engine (9), and a second electric machine mechanically coupled to a second input of the main gearbox (4), the second electric machine being supplied with electrical power by the first electric machine and configured to operate as an electric motor to deliver additional mechanical power to the main gearbox (4).Type: ApplicationFiled: December 3, 2021Publication date: March 21, 2024Applicant: SAFRAN HELICOPTER ENGINESInventors: Romain Jean Gilbert THIRIET, Fabien MERCIER-CALVAIRAC, Stéphane Albert André DOUILLARD
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Publication number: 20240003261Abstract: This method for stopping at least one aircraft turbogenerator (1) comprises: —controlling the stopping (E1) of the turbogenerator (1); —passing from the nominal operating speed (Nref) of the power shaft (3, 12) to a first operating speed (N1) lower than the nominal speed (Nref), for a first predetermined duration (t2); —controlling the extinction of the combustion chamber (6) of the gas turbine (2); —maintaining the rotation of the gas turbine at a second speed (N2) for a second predetermined duration (t3), the power shaft (3, 12) being at a second speed (N2) lower than the first operating speed (N1) and, —controlling the stopping of the reversible electric machine (7) in order to no longer drive the power shaft (3, 12), in order to cause a progressive stopping (E9, E10) of the rotation of the gas turbine (2).Type: ApplicationFiled: December 1, 2021Publication date: January 4, 2024Inventors: Fabien Mercier-Calvairac, Nicolas Claude Parmentier, Denis Antoine Julien Real
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Publication number: 20220213842Abstract: A propulsion assembly for aircraft includes a single-shaft engine turbomachine including a combustion chamber and a rotatably mounted shaft that turns at a turbomachine rating; an electrical generator coupled to the shaft; and a control system. The control system includes a fuel pump that brings fuel into the combustion chamber at a fuel flow rate which is a direct function of an ambient pressure and of the turbomachine rating, and power electronics that are coupled to the electrical generator and that control an electrical power drawn off the electrical generator so as to attain a target turbomachine rating.Type: ApplicationFiled: July 3, 2020Publication date: July 7, 2022Applicants: SAFRAN HELICOPTER ENGINES, SAFRAN POWER UNITSInventors: Fabien MERCIER-CALVAIRAC, Patrick MARCONI, Denis Antoine Julien REAL
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Patent number: 10953981Abstract: The invention relates to a helicopter including a structural framework, at least one main rotor for lift and propulsion integral with said structural framework and a drive train for driving said main rotor including a power transmission gearbox and at least one main engine, wherein it further includes a plurality of extra booster power units fixed to said structural framework and configured so as to be able to supply extra lift of the helicopter in case of failure of the helicopter's drive train.Type: GrantFiled: September 2, 2016Date of Patent: March 23, 2021Assignee: SAFRAN HELICOPTER ENGINESInventors: Eric Pierre Seinturier, Romain Thiriet, Fabien Mercier-Calvairac
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Patent number: 10766629Abstract: An architecture of a propulsion system of a multi-engine helicopter is disclosed, comprising turboshaft engines that are connected to a power transmission gearbox. It comprises: a hybrid turboshaft engine that is capable of operating in at least one standby mode during a stable flight of the helicopter; a pack for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a nominal operating mode; an auxiliary power unit that is connected to said electrotechnical restart pack by means of a first AC/DC converter and is capable of providing said restart pack, on demand, with power required for bringing said hybrid turboshaft engine out of said standby mode.Type: GrantFiled: March 20, 2015Date of Patent: September 8, 2020Assignees: SAFRAN HELICOPTER ENGINES, SAFRAN POWER UNITSInventors: Fabien Mercier-Calvairac, Stéphane Beddok, Stéphane Chevalier, Sophie Humbert
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Patent number: 10737795Abstract: The hybrid propulsion system for a multi-engine aircraft includes a plurality of free-turbine engines, each having a gas generator, among which at least a first engine, or hybrid engine, is suitable for operating in at least one standby mode during stabilized flight of the aircraft, while other engines of the plurality of engines operate alone during such stabilized flight. The hybrid engine is associated with first and second identical electric powertrains, each including a respective electrical machine capable of operating as a starter and as a generator, itself connected to a respective electronic power module, itself selectively connected to a specific electrical power supply network, such as an onboard network, and to a respective at least one electrical energy storage member. Each of the electric powertrains is adapted to deliver maximum power not less than half the total power needed for rapid reactivation of the hybrid engine.Type: GrantFiled: October 15, 2015Date of Patent: August 11, 2020Assignee: SAFRAN HELICOPTER ENGINESInventors: Frederic Moulon, Fabien Mercier-Calvairac, David Le Maux
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Patent number: 10338540Abstract: The invention relates to a method and to a device for optimized global management of a power network of an aircraft comprising a plurality of items of power equipment, characterized in that it comprises a module 40 for selecting at least one optimization objective (19) from a plurality of predetermined objectives, a module (42) for receiving equipment data, a module (41) for receiving aircraft data, and a module (43) for determining operating setpoints (22) of the power equipment from equipment data (21) and aircraft data (20) which is suitable for achieving at least one selected optimization objective (19).Type: GrantFiled: March 20, 2015Date of Patent: July 2, 2019Assignee: SAFRAN HELICOPTER ENGINESInventors: Fabien Mercier-Calvairac, Antoine Drachsler, Romain Thiriet
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Patent number: 10214296Abstract: The invention relates to an architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines (1, 2) that are connected to a power transmission gearbox (3), and comprising a low DC voltage onboard network (7) for supplying helicopter equipment during flight, characterized in that it comprises: a hybrid turboshaft engine (1) that is capable of operating in at least one standby mode during a stable flight of the helicopter; an electrotechnical pack (20) for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a mode in which it provides mechanical power, said restart pack (20) being connected to said onboard network (7); and at least two sources (4, 16, 18) of electrical power for said onboard network (7).Type: GrantFiled: March 20, 2015Date of Patent: February 26, 2019Assignee: SAFRAN HELICOPTER ENGINESInventors: Fabien Mercier-Calvairac, Sophie Humbert, Stephane Beddok
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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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Publication number: 20180251213Abstract: The invention relates to a helicopter including a structural framework, at least one main rotor for lift and propulsion integral with said structural framework and a drive train for driving said main rotor including a power transmission gearbox and at least one main engine, wherein it further includes a plurality of extra booster power units fixed to said structural framework and configured so as to be able to supply extra lift of the helicopter in case of failure of the helicopter's drive train.Type: ApplicationFiled: September 2, 2016Publication date: September 6, 2018Inventors: Eric Pierre SEINTURIER, Romain THIRIET, Fabien MERCIER-CALVAIRAC
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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: 20170247114Abstract: The hybrid propulsion system for a multi-engine aircraft includes a plurality of free-turbine engines, each having a gas generator, among which at least a first engine, or hybrid engine, is suitable for operating in at least one standby mode during stabilized flight of the aircraft, while other engines of the plurality of engines operate alone during such stabilized flight. The hybrid engine is associated with first and second identical electric powertrains, each including a respective electrical machine capable of operating as a starter and as a generator, itself connected to a respective electronic power module, itself selectively connected to a specific electrical power supply network, such as an onboard network, and to a respective at least one electrical energy storage member. Each of the electric powertrains is adapted to deliver maximum power not less than half the total power needed for rapid reactivation of the hybrid engine.Type: ApplicationFiled: October 15, 2015Publication date: August 31, 2017Applicant: SAFRAN HELICOPTER ENGINESInventors: Frédéric MOULON, Fabien MERCIER-CALVAIRAC, David LE MAUX
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Publication number: 20170152055Abstract: An architecture of a propulsion system of a multi-engine helicopter is disclosed, comprising turboshaft engines that are connected to a power transmission gearbox. It comprises: a hybrid turboshaft engine that is capable of operating in at least one standby mode during a stable flight of the helicopter; a pack for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a nominal operating mode; an auxiliary power unit that is connected to said electrotechnical restart pack by means of a first AC/DC converter and is capable of providing said restart pack, on demand, with power required for bringing said hybrid turboshaft engine out of said standby mode.Type: ApplicationFiled: March 20, 2015Publication date: June 1, 2017Applicants: SAFRAN HELICOPTER ENGINES, SAFRAN POWER UNITSInventors: Fabien Mercier-Calvairac, Stéphane Beddok, Stéphane Chevalier, Sophie Humbert
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Publication number: 20170131687Abstract: The invention relates to a method and to a device for optimised global management of a power network of an aircraft comprising a plurality of items of power equipment, characterised in that it comprises a module 40 for selecting at least one optimisation objective (19) from a plurality of predetermined objectives, a module (42) for receiving equipment data, a module (41) for receiving aircraft data, and a module (43) for determining operating setpoints (22) of the power equipment from equipment data (21) and aircraft data (20) which is suitable for achieving at least one selected optimisation objective (19).Type: ApplicationFiled: March 20, 2015Publication date: May 11, 2017Applicant: SAFRAN HELICOPTER ENGINESInventors: Fabien Mercier-Calvairac, Antoine Drachsler, Romain Thiriet
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Publication number: 20170096233Abstract: The invention relates to an architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines (1, 2) that are connected to a power transmission gearbox (3), and comprising a low DC voltage onboard network (7) for supplying helicopter equipment during flight, characterised in that it comprises: a hybrid turboshaft engine (1) that is capable of operating in at least one standby mode during a stable flight of the helicopter; an electrotechnical pack (20) for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a mode in which it provides mechanical power, said restart pack (20) being connected to said onboard network (7); and at least two sources (4, 16, 18) of electrical power for said onboard network (7).Type: ApplicationFiled: March 20, 2015Publication date: April 6, 2017Inventors: Fabien MERCIER-CALVAIRAC, Sophie HUMBERT, Stephane BEDDOK
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Publication number: 20110282534Abstract: The invention relates to a method and a device for managing the power from a power train of a hybrid motor vehicle, taking into account one or more operational parameters of at least one element of said power train. The method is characterised in that the determination of the consumption gain (6) is based on one or more operational parameters of at least one or part of said elements (1 to 5) in the power train. Advantageously, said operational parameter is the respective temperature of at least one or part of the elements (1 to 5) in the power train. The invention is suitable for use in the field of motor vehicles.Type: ApplicationFiled: December 24, 2009Publication date: November 17, 2011Applicant: PEUGEOT CITROEN AUTOMOBILES SAInventors: Nawal Jaljal, Fabien Mercier-Calvairac, Vincent Mulot, Patrick Lagonotte
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Publication number: 20110163724Abstract: In a hybrid vehicle system comprising an electric power storage system and an electric motor, the method includes a first step of allowing the electric power storage system to be discharged: upon detecting a condition of a charge of the electric power storage system that is greater than a first threshold to optimize power consumption; and upon detecting a condition of the charge of the electric power storage system that is greater than a second threshold to increase performance.Type: ApplicationFiled: September 22, 2009Publication date: July 7, 2011Applicant: Peugeot Citroen Automobiles SAInventors: Melaine Migaud, Nicolas Dollinger, Nicolas Robart, Fabien Mercier-Calvairac