Safran Helicopter Engines

Matthieu Julien Gallot

Philippe Jean René Marie Benezech

Jean-Luc Charles Gilbert Frealle

Jean Philippe Jacques Marin

Philippe Etchepare

Pascal Rizzo

Luc Jacques Pierre Reberga

The invention concerns a method for monitoring the operating state of a system for positioning variable-geometry members () of a turbomachine (), the members () being configured to travel over an operating area comprising a first position Pand a second position P, the method comprising the steps of: —(E) determining a first pivoting speed Vfrom the first position Pto the second position P; —(E) determining a second pivoting speed from the second position Pto the first position P; and—(E) determining an anomaly in the operation of the system for positioning the members () if the first speed Vis lower than a first determined speed threshold and/or if the second speed Vis lower than a second determined speed threshold.

Method for monitoring the operating state of a system for positioning variable-geometry members of a turbomachine

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

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Moissy-Cramayel, France

Matthieu Julien Gallot