Eurocopter

Airbus Helicopters

François-Xavier Gaulmin

Lionel Iraudo

Daniel Chaniot

Guillaume Dumur

Olivier Voinchet

A method for stopping an engine of a rotorcraft in overspeed, the rotorcraft comprising at least one engine, the engine comprising a gas generator and a power assembly, the power assembly comprising at least one power turbine rotated by gases originating from the gas generator, the power assembly comprising at least one power shaft rotationally secured to the power turbine, the power assembly rotating about a longitudinal axis at a speed referred to as the 'speed of rotation'. The method comprises steps consisting in measuring a current value of the speed of rotation, determining a time derivative of the current value of the speed of rotation, referred to as the 'current derivative and automatically stopping the engine when the current derivative changes sign.

Method for stopping an engine in overspeed, and associated system and rotorcraft

The present invention relates to a method and to an associated fuel metering system for balancing the power delivered by two aircraft turboshaft engines by determining first and second limiting margins of the engines (M, M) which are transformed into first and second power margins. Thereafter, the values of the first and second power margins are compared in order to determine a primary difference between said first and second power margins. Finally, the engine having the greater power margin is accelerated in order to balance the first and second engines in power by minimizing the primary difference to as great as extent as possible.

Balancing the power of two turboshaft engines of an aircraft

An assisted piloting method for an aircraft having at least two engines () includes monitoring a set of parameters (Ng, T, Tq) of the engines. A first limit indicator () displays information relating to a value of a limiting parameter of the engines. The limiting parameter is the parameter (Ng, T, Tq) of the engines that is the closest to its limit. An assisted piloting mode is activated during which each parameter (Ng, T, Tq) is maintained below a predetermined threshold whenever the first limit indicator is not in a position to display the information.

Assisted piloting method and device for an aircraft for use in the event of a first limit indicator breaking down

The present invention relates to a method and to an instrument for determining the limiting margin of a surveillance parameter of a turboshaft engine. During a preliminary stage, a secondary processor means () determines a preliminary comfort margin. Thereafter, during a main stage, it estimates a useful comfort margin from the preliminary comfort margin, and then an apparent difference between the current value and the limit value of the surveillance parameter, and finally the limiting margin by subtracting the useful comfort margin from the apparent difference.

Method and an instrument for determining the limiting parameter of a turboshaft engine

The present invention relates to a method and to a device (D) enabling a health check to be performed on at least a first turbine engine (M) of a rotorcraft, the rotorcraft being provided with first and second turbine engines (Mand M) controlled respectively by first and second control means (MCand MC). The device is remarkable in that it comprises check means (C) provided with main means (C), the main means (C) controlling the first and second control means (MCand MC) so that the surveillance parameters of the first and second turbine engines (Mand M) respectively reach the real first and second final values (Vand V) as determined in accordance with the method of the invention.

Method and a device for performing a check on the state of health of a turbine engine of a twin-engined rotorcraft

The present invention relates to a power plant () comprising at least one turboshaft engine () behind a gearbox () for driving a rotor () of a rotary wing aircraft (), the air inlet body () of the engine () having a first end () opening out into the ambient atmosphere in front of the engine, and a second end () connected to the engine at the rearmost portion thereof.

Growing community of inventors

Salon de Provence, France

François-Xavier Gaulmin