Safran

Safran Electrical & Power

Safran Helicopter Engines

Florent Rougier

Stéphane Petibon

Jean-Philippe Hervé Salanne

René Meunier

Meriem Abdellatif

Stéphane Beddok

Christelle Saber

Rémy Biaujaud

Jean-Philippe Salanne

Garance Vinson

Christophe Ludovic Jean-Claude Viguier

José Del Castillo

Jerome Valire

Jerome Didier Mora

Adrian Florescu

Mallika Nadheria

Alexander Salimian

Antoine Duquerrois

Jérôme Valire

Jérôme Didier Mora

Yann Fefermann

A method for determining a first setpoint for a first vector component of the phase currents along a first axis of a rotating reference frame connected to a rotor of the electric generator, and a second setpoint for a second vector component of the phase currents along a second axis of the rotating reference frame. The second vector component of the phase currents is to bring about defluxing of the rotor; and controlling the rectifier on the basis of the first and second setpoints for the vector components of the phase currents. The first setpoint for the first vector component of the phase currents is determined on the basis of an external feedback loop designed to feedback-control a voltage on a DC bus or to regulate a current from a battery connected to the DC bus.

Method for controlling a rectifier connected to a permanent-magnet synchronous electric generator to provide a direct voltage, corresponding device and computer program

A propulsion channel for aircraft at least one first dual-fed polyphase asynchronous rotating electric machine configured to be mechanically coupled to a turbine engine. The propulsion channel further includes at least one second polyphase rotating electric machine electrically coupled to the first asynchronous rotating electric machine, and a control and storage module configured to control the first polyphase asynchronous rotating electric machine. The module is connected to the first dual-feed polyphase asynchronous rotating electric machine as well as to the at least second polyphase rotating electric machine. The at least second polyphase rotating electric machine includes a polyphase synchronous rotating electric machine with permanent magnet.

Propulsion channel for aircraft

The invention relates to a hybrid propulsion architecture () for an aircraft, comprising: —a first source () of a first energy type, —second sources () of a second energy type different from the first energy type, —electrical propulsion systems (), —an electric power supply network () connecting the first and second sources () to the electrical propulsion systems, such that each electrical propulsion system is powered by the first source and by one of the second sources, the architecture being characterised in that it further comprises: —means for segregating () the electrical propulsion systems, which means are arranged in the electric power supply network and configured to impose a direction of flow of the electric power from the first source to the electrical propulsion systems.

Hybrid propulsion architecture and aircraft containing such an architecture

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

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.

Hybrid propulsion assembly for aircraft

The invention relates to a system for sychronising energy sources coupled to an electrical grid supplying at least one electrical load of an aircraft, said system comprising: a main source of electrical energy supplying said electrical load comprising a multi-stage generator, said multi-stage generator comprising: a primary stage comprising a generator with permanent magnets, a secondary stage comprising an excitation, and a tertiary stage comprising a main generator; an auxiliary source of electrical energy supplying said electrical load; and a device for synchronising the main source and the auxiliary source, designed to measure an electrical voltage at the outlet of the primary stage of the main source, and to control the supply of said electrical load by means of the auxiliary source of electrical energy at an electrical voltage slaved to the characteristics of frequency and phase of the electrical voltage of the primary stage.

System for synchronising energy sources coupled to an aircraft

Method for monitoring the distribution of power in a hybrid propulsion system comprising one or more electrical sources delivering an AC voltage, each of which is associated with an AC-to-DC controlled rectifier and one or more batteries, wherein, the AC-to-DC controlled rectifier and the battery each being connected directly to an HVDC bus supplying one or more electrical loads with power, the monitoring of the distribution of power is performed through the individual AC-to-DC controlled rectifier by a feedback loop to a power setpoint (Pref) on the basis of a measured power of the battery (Pbat) and a feedback loop to a voltage setpoint (Vref) on the basis of a measured voltage of the HVDC bus (V), either one of these two feedback loops delivering an RMS current setpoint Idref and Iqref for a feedback loop on the basis of a current (Igen) of the electrical source delivering an AC voltage.

Method and device for monitoring the hybridization of an aircraft

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.

System for generating electric power for an aircraft

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.

On-board power supply network of an electrically propelled aircraft

A method of electrically powering an electrical load in an aircraft, the method including electrically powering the electrical load with a main source that generates electricity; measuring an instantaneous parameter characterizing the main source; determining a level of use of the main source from the measured instantaneous parameter; adjusting the voltage of the main source as a function of the level of use; measuring an output voltage from the main source; comparing the measured voltage or the level of use with a predetermined threshold value; and whenever the measured voltage is less than the predetermined threshold value, electrically powering the electrical load from an auxiliary source that stores electricity so as to supply additional electric power to the electrical load.

Growing community of inventors

Moissy-Cramayel, France

Florent Rougier