The invention relates to a hydraulic control circuit (17) of a steering actuator (21) having a first and a second chamber (18, 19), for orienting the blades of an aircraft engine propeller, this circuit (17) comprising a high-pressure line (23) and a low-pressure line (24), a first protection valve (33) being able to assume a deactivated position or an activated position for placing the first chamber (18) in communication with the high-pressure line (23), a second protection valve (34) being able to assume a deactivated position or an activated position for placing the second chamber (19) in communication with the low-pressure line (24), each protection valve (33, 34) comprising a hydraulic activation inlet (37, 41) and a hydraulic deactivation inlet (38, 42) which can be pressurised in order to activate or deactivate these valves (33, 34). The circuit includes a solenoid protection valve (31) controlling an amplification valve (32) connected to the inlets of the protection valves (33, 34) in order to activate them upon the activation of the solenoid protection valve (31).
PROTECTION POUR CIRCUIT DE COMMANDE D'ORIENTATION DE PALES D'HELICES DE MOTEUR D'AERONEF
PROTECTION FOR A CIRCUIT FOR CONTROLLING THE ORIENTATION OF PROPELLER BLADES OF AN AIRCRAFT ENGINE
SCHUTZ FÜR EINE SCHALTUNG ZUR STEUERUNG DER AUSRICHTUNG VON PROPELLERBLÄTTERN EINES FLUGZEUGMOTORS
2025-05-14
Patent
Electronic Resource
French
IPC: | B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS |
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