Safran

Meriem Abdellatif

René Meunier

Florent Rougier

Stéphane Petibon

Jean-Philippe Hervé Salanne

Vincent Pauvert

A power supply system comprising: a first converter module comprising an AC/DC converter and being arranged to produce an intermediate voltage from an input voltage; a second converter module comprising a DC/DC converter and being controllable to use the intermediate voltage to produce selectively at least two distinct output voltage levels; and a control unit arranged to acquire a flight parameter representative of the flight phase and/or of the altitude, and to control the power supply system in such a manner that the second converter module delivers to each electrical system a power supply voltage that depends on the flight parameter and on said electrical system, and that is equal to one of the output voltage levels.

Configurable power supply system

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.

System for converting and transporting electrical energy for the internal hybridization of an aircraft with turbojet engines

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.

Growing community of inventors

Moissy-Cramayel, France

Meriem Abdellatif