Patents by Inventor Jean-Philippe Hervé SALANNE
Jean-Philippe Hervé SALANNE 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: 11945592Abstract: An aircraft propelled by at least one turbojet engine on which power can be bled or injected via a high-pressure and/or low-pressure turbine shaft and including at least one gas turbine to provide power transients, having a system for converting and transporting electrical energy wherein each of the high-pressure and/or low-pressure turbine shafts is connected to a first doubly-fed asynchronous machine delivering, a first three-phase AC voltage over an AC distribution grid and a second polyphase AC voltage for a first AC/DC bidirectional converter supplying a DC voltage over a DC distribution grid, at least one second DC/AC bidirectional converter connected to the DC distribution grid converting this DC voltage into a third polyphase AC voltage supplying at least one second doubly-fed asynchronous machine engaged with a rotation shaft of the gas turbine, the second doubly-fed asynchronous machine further delivering a fourth polyphase AC voltage over the AC distribution grid.Type: GrantFiled: October 22, 2019Date of Patent: April 2, 2024Assignee: SAFRANInventors: Jean-Philippe Hervé Salanne, Stéphane Petibon, Florent Rougier, René Meunier, Meriem Abdellatif
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Patent number: 11932408Abstract: Series hybrid propulsion unit including a gas turbine driving a mechanical shaft of an electric generator having n output phases and supplying an AC busbar, and a system for monitoring the speed of the gas turbine, the AC busbar supplying a plurality of AC distribution channels each composed of an electric rectifier and a battery sharing the power required to supply a DC bus, the DC bus in turn supplying a plurality of propulsion sub-channels composed of electric inverters supplying, under the monitoring of a control module, motors driving thrusters, further including a battery charger for charging the battery from the DC bus, a power management module delivering a power reference for the electric generator, and a hybridization rate management module monitoring the voltage of the DC bus, the battery being directly connected on the DC bus via a passive component and the electric rectifier being a passive converter.Type: GrantFiled: September 2, 2019Date of Patent: March 19, 2024Assignee: SAFRANInventors: Jean-Philippe Hervé Salanne, Stéphane Petibon, Florent Rougier
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Patent number: 11365686Abstract: Electrical power generation system for an aircraft, including: a gas turbine having a high-pressure shaft and outputting a gas flow to actuate a free turbine, a polyphase permanent magnet generator coupled to the gas turbine and able to output a first alternating voltage for supplying through first conversion means a primary power supply network of the aircraft, the free turbine and the permanent magnet generator being mounted on the same drive shaft concentric with the high-pressure shaft of the gas turbine, a starter mounted on the high-pressure shaft able to ensure the starting of the gas turbine, the starter being a permanent magnet starter/generator able to output a second alternating voltage for supplying a secondary power supply network of the aircraft and auxiliary equipment of the gas turbine and the first conversion means include two first AC/DC converters controlled from a management unit.Type: GrantFiled: July 26, 2019Date of Patent: June 21, 2022Assignee: SAFRANInventors: Florent Rougier, Stéphane Petibon, Jean-Philippe Hervé Salanne
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Patent number: 11338928Abstract: A system for supplying electrical energy to at least one electrical load of an aircraft, this system including a main source of electrical energy connected to at least one electrical load through an electrical network, the system including a control device connected to the main source of electrical energy and configured to deliver a variable voltage level on the electrical network based on a predetermined voltage variation law depending on at least one parameter characterizing the altitude of the aircraft and according to the Paschen law with a predefined margin.Type: GrantFiled: October 4, 2019Date of Patent: May 24, 2022Assignee: SAFRANInventors: Jean-Philippe Hervé Salanne, Stephane Petibon, Florent Rougier, René Meunier, Meriem Abdellatif
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Publication number: 20210380264Abstract: An aircraft propelled by at least one turbojet engine on which power can be bled or injected via a high-pressure and/or low-pressure turbine shaft and including at least one gas turbine to provide power transients, having a system for converting and transporting electrical energy wherein each of the high-pressure and/or low-pressure turbine shafts is connected to a first doubly-fed asynchronous machine delivering, a first three-phase AC voltage over an AC distribution grid and a second polyphase AC voltage for a first AC/DC bidirectional converter supplying a DC voltage over a DC distribution grid, at least one second DC/AC bidirectional converter connected to the DC distribution grid converting this DC voltage into a third polyphase AC voltage supplying at least one second doubly-fed asynchronous machine engaged with a rotation shaft of the gas turbine, the second doubly-fed asynchronous machine further delivering a fourth polyphase AC voltage over the AC distribution grid.Type: ApplicationFiled: October 22, 2019Publication date: December 9, 2021Applicant: SAFRANInventors: Jean-Philippe Hervé SALANNE, Stéphane PETIBON, Florent ROUGIER, René MEUNIER, Meriem ABDELLATIF
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Publication number: 20210347492Abstract: A system for supplying electrical energy to at least one electrical load of an aircraft, this system including a main source of electrical energy connected to at least one electrical load through an electrical network, the system including a control device connected to the main source of electrical energy and configured to deliver a variable voltage level on the electrical network based on a predetermined voltage variation law depending on at least one parameter characterizing the altitude of the aircraft and according to the Paschen law with a predefined margin.Type: ApplicationFiled: October 4, 2019Publication date: November 11, 2021Applicant: SAFRANInventors: Jean-Philippe Hervé SALANNE (Deceased), Stephane PETIBON, Florent ROUGIER, René MEUNIER, Meriem ABDELLATIF
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Publication number: 20210339877Abstract: Series hybrid propulsion unit including a gas turbine driving a mechanical shaft of an electric generator having n output phases and supplying an AC busbar, and a system for monitoring the speed of the gas turbine, the AC busbar supplying a plurality of AC distribution channels each composed of an electric rectifier and a battery sharing the power required to supply a DC bus, the DC bus in turn supplying a plurality of propulsion sub-channels composed of electric inverters supplying, under the monitoring of a control module, motors driving thrusters, further including a battery charger for charging the battery from the DC bus, a power management module delivering a power reference for the electric generator, and a hybridization rate management module monitoring the voltage of the DC bus, the battery being directly connected on the DC bus via a passive component and the electric rectifier being a passive converter.Type: ApplicationFiled: September 2, 2019Publication date: November 4, 2021Applicant: SAFRANInventors: Jean-Philippe Hervé SALANNE, Stéphane PETIBON, Florent ROUGIER
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Publication number: 20210207543Abstract: Electrical power generation system for an aircraft, including: a gas turbine having a high-pressure shaft and outputting a gas flow to actuate a free turbine, a polyphase permanent magnet generator coupled to the gas turbine and able to output a first alternating voltage for supplying through first conversion means a primary power supply network of the aircraft, the free turbine and the permanent magnet generator being mounted on the same drive shaft concentric with the high-pressure shaft of the gas turbine, a starter mounted on the high-pressure shaft able to ensure the starting of the gas turbine, the starter being a permanent magnet starter/generator able to output a second alternating voltage for supplying a secondary power supply network of the aircraft and auxiliary equipment of the gas turbine and the first conversion means include two first AC/DC converters controlled from a management unit.Type: ApplicationFiled: July 26, 2019Publication date: July 8, 2021Applicant: SAFRANInventors: Florent ROUGIER, Stéphane PETIBON, Jean-Philippe Hervé SALANNE