Safran Helicopter Engines

Airbus Helicopters

Olivier Lafargue

Thomas Klonowski

Sébastien Brotier

Camel Serghine

Antoine Pascal Moutaux

Bertrand Nogarede

Jean-Julien Camille Vonfelt

Alphonse Puerto

David Cazaux

Didier Chartrain

Sebastien Brotier

The invention relates to an aircraft power architecture comprising a power transmission gearbox (), located in a first compartment (), a gas turbine (), located in a second compartment () comprising a gas generator () and a free turbine () connected to the power transmission gearbox () by a power shaft () of the gas turbine (), and an accessory gearbox (), the gas turbine () being set into the main transmission gearbox (), characterized in that the gas turbine () comprises a first electric machine (), and in that the accessory gearbox () is placed in the first compartment () and comprises a second electric machine () configured to supply energy to the accessory equipment and to receive electrical energy transmitted via the first electric machine ().

Aircraft power architecture

An electrical generator is housed in an annular cavity between the casing and the propeller shaft of a turboprop, while imposing little or no additional space requirement and with lightweight ancillary equipment. The rotor of the generator is mounted on an autonomous shaft end. A flange of the outer casing is removable in order to access the generator and to enable its easy removal and remounting.

Turboprop comprising an incorporated electricity generator

A turboshaft engine for a helicopter, comprising a case inside which a gas generator and a turbine are accommodated, the turbine being mounted on a power shaft that extends along a longitudinal direction. The turboshaft engine further comprises means for removably mounting the power shaft into a reduction gearbox inside which at least one gear of a first reduction stage is accommodated. The means for removably mounting the power shaft include a pinion having a central bore, the shape of which is adapted to that of the power shaft in such a way that the pinion can slide over the power shaft; furthermore, the contour of the pinion is adapted to the shape of the gear of the first stage in such a way that the pinion can form a leading input pinion of the gearbox in said gear once the power shaft has been mounted in the reduction gearbox.

Turboshaft engine embeddable in a reduction gearbox

The electrical machine according to the invention is a dual machine, and comprises a first machine which can be reversed and a second machine functioning through induction between two windings. The second machine can be used for de-icing a propeller, the induction-receiving winding being mounted on the propeller shaft. The first electrical machine can function as an electrical engine to 'taxi' the aircraft. In certain embodiments, the winding mounted on the stator is common to the two machines and different magnetic flows are utilised to control them. A separate functioning of the two machines and a very good integration into the aircraft engine, with space-saving and low mass, are possible.

Aircraft turboprop engine provided with an electric machine

A propulsion unit, notably for an aircraft, including a turbomachine; a propeller that can be selectively coupled to the turbomachine; a rotary electrical machine able to drive at least the turbomachine, and selective coupling of the rotary electric machine to the propeller and/or the turbomachine that is able to couple only the propeller to the rotary electrical machine during a defined stage of operation of the propulsion unit and that is able to couple or not couple the rotary electric machine to a gas generator and/or a free turbine of the turbomachine.

Propulsion unit with selective coupling means

A turboshaft engine includes a casing in which is arranged a gas generator and a free turbine fitted to a power shaft. The power shaft is configured to be mechanically connected to/disconnected from a reduction gearbox. The turboshaft engine includes at least one centralizer movable between an active position, in which the centralizer forms a bearing for the power shaft and which corresponds to a mechanical disconnection between the power shaft and the reduction gearbox, and a passive position, in which the centralizer is distanced from the power shaft and which corresponds to a mechanical connection between the power shaft the reduction gearbox.

Growing community of inventors

Moissy-Cramayel, France

Olivier Lafargue