Safran Helicopter Engines

Safran Power Units

Microturbo Sa

Safran Electrical & Power

Stéphane Chevalier

Jean-Francois Rideau

Fabien Mercier-Calvairac

Stéphane Beddok

Fabien Silet

Alexis Renotte

Sophie Humbert

Jean-François Rideau

Serge Marie Gabriel Cot

Jean-Paul Salvador Lopez

An architecture of a propulsion system of a multi-engine helicopter is disclosed, comprising turboshaft engines that are connected to a power transmission gearbox. It comprises: a hybrid turboshaft engine that is capable of operating in at least one standby mode during a stable flight of the helicopter; a pack for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a nominal operating mode; an auxiliary power unit that is connected to said electrotechnical restart pack by means of a first AC/DC converter and is capable of providing said restart pack, on demand, with power required for bringing said hybrid turboshaft engine out of said standby mode.

Architecture of a multiple-engine helicopter propulsion system, and corresponding helicopter

A system for supplying compressed air to a pneumatic network includes a load compressor, an air supply and a power shaft driving the load compressor. The system also includes in an air outlet of such load compressor, a connecting channel connected, on the one side, with a channel connected with the pneumatic network and, on the other side, with an air discharge conduct towards an exhaust nozzle. Air flow rate bleed valves are controlled by a processing unit via servo-loops as a function of the pressure sensors and the speed sensor.

Controlling method and system for compressed air supply to a pneumatic network, in particular in an aircraft

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Colomiers, France

Stéphane Chevalier