Safran Helicopter Engines

Turbomeca

Jean Philippe Jacques Marin

Philippe Etchepare

Pierre Harriet

Fabien Lescher

Matthieu Julien Gallot

The invention relates to a method for detecting a malfunction in a first turboshaft engine, referred to as an inoperative engine (), of a twin-engine helicopter, and for controlling a second turboshaft engine, referred to as a healthy engine (), each engine () comprising protective stops regulated by a regulation device which define a maximum power regime, characterised in that it comprises: a step () of detecting an indication of failure of said inoperative engine (); a step () of modifying said protective stops of said healthy engine () into protective stops which correspond to a maximum power single-engine regime, in the case of the detected indication of failure; a step () of confirming a failure of said inoperative engine (); a step () of controlling an increase in the flow rate of fuel supply of said healthy engine (), in the event of a confirmed failure.

Method for detecting a failure of a first turbine engine of a twin-engine helicopter and for operating the second turbine engine, and corresponding device

The invention relates to a device for controlling an auxiliary engine () comprising a gas generator and a free turbine suitable for being able to be connected mechanically to the rotor () of a helicopter in order to supply it with thrust power, characterised in that said control device comprises a proportional-integral controller () having a proportional gain (Kp) and an integral gain (Ki), which are dependent on the rotation speed of said gas generator, said controller () being configured to receive an error signal representing a speed error of said free turbine, and to generate a signal (Sc) for correcting the drive speed of said gas generator obtained by adding a signal proportional to said error signal in accordance with said proportional gain (Kp), and an integrated signal (Si) resulting from the addition of a signal proportional to said error signal in accordance with said integral gain (Ki) and a memory signal (Sm), supplied by a feedback loop () of said integrated signal (Si), said memory signal (Sm) being dependent on a measurement representing the rotation speed of said free turbine.

Device and method for controlling an auxiliary engine suitable for supplying thrust power to the rotor of a helicopter

The invention relates to a method for starting an aircraft turboshaft engine, said turboshaft engine comprising a combustion chamber, a compressor shaft on which a compressor wheel is mounted to feed compressed air to said combustion chamber, at least one starter connected to said shaft so as to provide it with a specified starting torque for driving it in rotation. The method comprises accelerating the compressor shaft during a first start-up phase, then stabilizing the rotational speed of the compressor shaft during a second start-up phase. During acceleration of the compressor shaft, the rotational speed of the shaft is regulated such that the acceleration of the shaft remains substantially constant.

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Jurancon, France

Jean Philippe Jacques Marin