Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Philippe Bodet

Daniel A Agram

Francedillaois G Dhyser

Gerard D Prigent

A rotor disk arrangement for a turbojet engine includes a balancing and damping system which has a ring having a circumferential surface recessed with housings and balance masses respectively positioned in the housings. A disk having a circumferential surface is provided which engages the circumferential surface of the ring. The circumferential surfaces are provided with a plurality of bayonet couplings, the couplings including a tenon and a groove engaged with the tenon. The groove includes a straight entrance portion which is substantially parallel to the axis of the engine and a crooked hind part which is substantially circumferentially positioned in the engine. In addition, a plurality of tongues are provided which are respectively inserted into the entrance portions of the grooves and fastened to the ring.

Growing community of inventors

Villeneuve La Guyard, France

Philippe Bodet