Airbus Helicopters

Mbda France

Sintertech

Damien Mariotto

Matthieu Connaulte

Christian Mercier

Michel Jamot

Stephane Cerqueira

Jean-François Logeais

Alix Bernot

Stéphane Cerqueira

A method and a system for stopping a gas turbine comprising a gas generator provided with rotary members and a combustion chamber. The gas turbine includes a fuel circuit controlled by calculation means in communication with a selector. The method includes a step of closing of the fuel circuit on order of the calculation means when the selector is positioned in a first position for causing the gas turbine to stop. If the gas turbine was not idling prior to the closure, or if it was idling, but for a length of time shorter than a threshold, then an electrical machine automatically rotates the rotary members for a limited duration.

Method and a system for stopping a gas turbine, and a vehicle

An electrical architecture for an aircraft having a primary three-phase electrical network powering a transformer-rectifier unit serving to power two secondary DC electrical networks. Each of the two secondary electrical networks includes a contactor electrically connected to a generator-starter. The contactors are linked in pairs to prevent them from being closed simultaneously. The second secondary network powers the generator-starter to start a fuel-burning engine. The first secondary network can be powered by the generator-starter to power electrical components. A secondary voltage of the second secondary electrical network is greater than the voltage of the first secondary electrical network, thus making it possible to optimize the weight of the electrical architecture. The two secondary electrical networks may also be powered from autonomous sources of electricity as a replacement for the primary network to power the generator-starter and the electrical components.

Electrical architecture with paired secondary electrical networks for starting engines of an aircraft

A reversible electrical machine () comprising: a first electrical device () having a first stator () and a first rotor (); a second electrical device () including a second rotor () and a second stator () together with an outlet shaft () and first disengageable coupling means () enabling said first and second rotors () to be associated and dissociated in rotation. Said reversible electrical machine () also includes second disengageable coupling means () that are disengageable under a predetermined force and that mechanically connect said second rotor () to said outlet shaft (). Said first electrical device () is a motor for transmitting high mechanical power to said outlet shaft (), while said second electrical device () is a motor-generator for operating in motor mode to transmit additional mechanical power to said outlet shaft (), and in generator mode for receiving mechanical power from said outlet shaft ().

Reversible electrical machine for an aircraft

A separately excited electric machine having a stator provided with at least one exciter unit and a rotor provided with strips. Each exciter unit comprises two secondary magnetic circuits and one primary magnetic circuit. Each secondary magnetic circuit comprises a stator exciter winding and two annular yokes provided with teeth. The primary magnetic circuit comprises a rotor exciter winding and an annular ring. First magnetic fluxes generated by the primary magnetic circuit circulate around loops in each strip and second magnetic fluxes generated by the secondary magnetic circuits circulate around loops in the strips, the teeth, and the ring. Each strip thus has a first north pole and a first south pole, with the teeth comprising in alternation second north poles and second south poles.

Separately excited electric machine with at least one primary magnetic circuit and at least two secondary magnetic circuits

An electric machine includes a stator and a rotor, with the stator being equipped with at least one annular exciter unit that includes a coil and at least two annular yokes, with the rotor being equipped with a structure and at least one annular receiver unit. Each receiver unit includes at least two rows of magnets. Two sides of each yoke include teeth distributed angularly in a regular manner, and the teeth of the two adjacent yokes fit onto a face of the exciter unit, alternately forming north poles and south poles. Each row of the magnets is positioned opposite one face, forming an air gap with the exciter unit, with the electric machine thus including at least two air gaps, with a 3D magnetic flux thus circulating inside the said electric machine, dividing and regrouping itself in the vicinity of the magnets and of the yokes.

Electric machine with multiple air gaps and a 3D magnetic flux

An electric machine including a stator that is provided with at least one exciter unit including a coil, at least two annular yokes and at least one row of intermediate pieces, and a rotor having a structure and at least one receiver unit including at least two series of at least two rows of magnets. Two sides of each yoke include the first teeth, fitting with the intermediate pieces on a face of the exciter unit and alternatingly forming the second north poles and the second south poles. Each series is positioned opposite one face, forming an air gap with the exciter unit, with the electric machine thus including at least two air gaps, with a flux thus circulating inside the electric machine, dividing and regrouping itself in the vicinity of the magnets and of the yokes.

Electric machine with intermediate pieces having multiple air gaps and a 3D magnetic flux

An aircraft () having at least one rotor () driven by a main gearbox (), at least one fuel-burning engine (), an on-board electricity network (), and at least one electrical machine () corresponding to the engine () and capable of operating both in electric motor mode and also in electricity generator mode, each electrical machine () being mechanically connected to said main gearbox () by first connection means () and being electrically connected to said on-board electricity network (). Second mechanical connection means () connect each electrical machine () mechanically to a gas generator () of an engine.

Rotary wing aircraft with a hybrid power plant

A method of assisting a pilot of a single-engined rotary wing aircraft () during a stage of flight in autorotation, said aircraft () including a hybrid power plant having an engine (), an electric machine (), and a main gearbox (). Said aircraft () also includes electrical energy storage means () and a main rotor () mechanically connected to said hybrid power plant (). According to said method, while in flight, the operation of said engine () is monitored in order to detect a failure thereof, in particular by monitoring for a drop of power on said main rotor (), and then in the event of a failure of said engine () being detected, said electric machine () is controlled to deliver auxiliary power Wto said main rotor (), thereby enabling the pilot of said aircraft () to be assisted in maneuvering said aircraft () during said stage of flight in autorotation following said failure.

Growing community of inventors

Lambesc, France

Damien Mariotto