The invention relates to a method for detecting a malfunction in a first turboshaft engine, referred to as an inoperative engine (4), of a twin-engine helicopter, and for controlling a second turboshaft engine, referred to as a healthy engine (5), each engine (4, 5) comprising protective stops regulated by a regulation device which define a maximum power regime, characterised in that it comprises: a step (10) of detecting an indication of failure of said inoperative engine (4); a step (11) of modifying said protective stops of said healthy engine (5) into protective stops which correspond to a maximum power single-engine regime, in the case of the detected indication of failure; a step (12) of confirming a failure of said inoperative engine (4); a step (13) of controlling an increase in the flow rate of fuel supply of said healthy engine (5), in the event of a confirmed failure.
PROCEDE DE DETECTION D'UNE DEFAILLANCE D'UN PREMIER TURBOMOTEUR D'UN HELICOPTERE BIMOTEUR ET DE COMMANDE DU SECOND TURBOMOTEUR, ET DISPOSITIF CORRESPONDANT
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
VERFAHREN FÜR DEN NACHWEIS EINES DEFEKTS EINES ERSTEN TURBINENMOTORS EINES ZWEIMOTORIGEN HUBSCHRAUBERS UND FÜR DEN BETRIEB DES ZWEITEN TURBINENMOTORS SOWIE ENTSPRECHENDE VORRICHTUNG
2019-01-30
Patent
Electronic Resource
French
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