Safran Helicopter Engines

Turbomeca

Caroline Seve

Romain Thiriet

Patrick Marconi

Pierre Darfeuil

Camel Serghine

Vincent Poumarede

A method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines configured to operate in parallel and together to supply a necessary power to the aircraft during a flight phase includes: placing one of the turbine engines in a maximum take-off power regime, and adjusting a power supplied by the other turbine engine, such that the turbine engines continue to supply the necessary power to the aircraft during the flight phase; determining a power supplied by the turbine engine placed in the maximum take-off power regime, and processing the supplied power determined in this way, in order to deduce a piece of information relating to the maximum available power.

Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines

The invention relates to a removable reactivation pack for a turboshaft engine of a helicopter, comprising a gas generator equipped with a drive shaft, said turboshaft engine () being capable of operating in at least one standby mode during a stable flight of the helicopter, said removable pack comprising: a removable gearbox comprising a gearbox output shaft; controlled means for rotating said gearbox output shaft, referred to as reactivation means of said turboshaft engine; mechanical means for reversibly coupling said gearbox output shaft to said drive shaft of said gas generator.

Removable pack for reactivating a turboshaft engine, architecture for a multi-engine system for propelling a helicopter, provided with such a pack, and corresponding helicopter

The invention relates to a method for automatically controlling an operating mode of a turboshaft engine of a helicopter, comprising a step () of receiving data () that are representative of the flight of the helicopter; a step () of selecting the turboshaft engine for which a change of mode would be most relevant; a step () of determining an operating mode of said turboshaft engine, known as the selected mode, selected from a plurality of predetermined operating modes; and a step () of ordering the operating mode of said turboshaft engine into said selected mode. The invention also relates to a corresponding control device.

Method for automatically controlling the operating speed of a helicopter turboshaft engine, corresponding control device and helicopter provided with such a device

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Pau, France

Caroline Seve