Safran Helicopter Engines

Safran Power Units

Sophie Humbert

Fabien Mercier-Calvairac

Stéphane Beddok

Bertrand Moine

Laurent Minel

Stéphane Chevalier

Patrice Laborde

Remy Princivalle

Rémy Princivalle

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

The invention relates to an architecture of a propulsion system of a multi-engine helicopter, comprising turboshaft engines () that are connected to a power transmission gearbox (), and comprising a low DC voltage onboard network () for supplying helicopter equipment during flight, characterized in that it comprises: a hybrid turboshaft engine () that is capable of operating in at least one standby mode during a stable flight of the helicopter; an electrotechnical pack () for quickly restarting said hybrid turboshaft engine in order to bring said engine out of said standby mode and to reach a mode in which it provides mechanical power, said restart pack () being connected to said onboard network (); and at least two sources () of electrical power for said onboard network ().

Architecture of a multi-engine helicopter propulsion system and corresponding helicopter

A device and a method of temporarily increasing power of at least a first turbine engine is disclosed. The device includes a coolant liquid tank and a first injection circuit connected to the tank and leading to at least one injection nozzle suitable for being installed upstream from at least one compressor stage of the first turbine engine. This first injection circuit includes at least a first flow valve configured to open when a pressure exceeds a predetermined threshold compared with a downstream pressure from at least one compressor stage of a second turbine engine so as to enable the coolant liquid to flow towards the injection nozzle of the first injection circuit.

Device and method for temporarily increasing power

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Pau, France

Sophie Humbert