FIELD: non-displacement compressors and pumps.
SUBSTANCE: invention relates to a device for guiding adjustable stator vanes of a turbojet engine, comprising a plurality of angular inner ring sectors placed end-to-end to form an inner ring, each inner ring sector including shafts passing radially through the inner ring sector, a plurality of cylindrical bushes which are each mounted in a shaft of the inner ring from the inside and which are each intended for receiving a guiding pivot of a stator blade, a plurality of angular reconstitution ring sectors which are placed end-to-end to form a reconstitution ring and which are mounted radially from the inside on the inner ring, and a plurality of locking elements passing axially through the inner and reconstitution rings so as to assemble said rings together.
EFFECT: invention allows to simplify the installation of the device.
10 cl, 5 dwg
