System for engine restart following complete inflight engine...

Details System for engine restart following complete inflight engine... System for engine restart following complete inflight engine...

F - Mech Eng,Light,Heat,Weapons

02

C

F02C 7/262 (2006.01) F02C 7/268 (2006.01)

Patent

CA 2193167

system to help restart at least one motor (1) of an aircraft in flight in the event that all motors fail. The aircraft has a hydraulic circuit (5) for servo-controls (6), which is normally supplied by a main pump (4) that is driven by the motor (1) and an emergency pump (16) that is driven by a ram air turbine (19) that deploys from the fuselage should engine power be lost during flight. The excess hydraulic energy of the emergency pump (16) serves to drive the main pump (4), which shall be of the reversible type and shall be able to function as a motor to increase the autorotation speed of the stopped motor (1) and help relight it, even at a slow airspeed.

Système d'aide au redémarrage d'au moins un moteur (1) d'un avion en vol, en cas de perte totale de motorisation. L'avion comporte un circuit hydraulique (5) pour les servo-commandes (6), normalement alimenté par une pompe principale (4) entraînée par le moteur (1), et une pompe de secours (16) entraînée par une turbine à air (19) sous pression dynamique qui est déployée à partir de fuselage en cas de perte de motorisation de l'avion. L'énergie hydraulique excédentaire de la pompe de secours (16) sert à entraîner la pompe principale (4) qui sera d'un type réversible et qui fonctionne en moteur, afin d'augmenter la vitesse d'autorotation du moteur éteint (1) et faciliter le réallumage de ce dernier, même à faible vitesse de l'avion

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