Abstract: A turbine engine includes a ferrule formed of a plurality of ferrule elements in the shape of circular sectors, each bearing on one internal face thereof fixed vanes and a circular housing surrounding the ferrule. The turbine has a support ring including a plurality of circular ring sectors each secured to the housing and having a U-shaped section whose opening is directed towards the ferrule, each ferrule element includes a hooking mechanism (9a) to be introduced into the opening of at least one ring sector so as to integrally connect the ring sector and the ferrule element.

Abstract: A system for locking the radial extremity of vanes, wherein the extremities include heels situated behind a ring for delimiting the flow of gases, the heels including hooks between which extend other hooks of the ring. Bolts are disposed in the notches of both types of hooks and fasteners are used to secure the bolts. The assembly obtained is compact, rigid and able to be embodied easily and effectively. It is also virtually free of clearances and vibrations.

Abstract: A control ring for a stage of pivotable vanes on the stator of a turbomachine carries a plurality of adjustable shoes for contacting a circular surface to set and maintain the coaxiality of the control ring during rotation thereof to pivot the vanes. The radial position of each shoe is adjusted by virtue of a double screw having two screw-threaded portions, one engaging with an internally threaded portion of a bush fixed to the control ring and the other engaging with an internally threaded portion of a shoe-holder which is mounted slidably and non-rotatably in the bush, the two screw-threaded portions having slightly different pitches so as to permit very fine adjustment of the shoe postion.

Abstract: A turboshaft engine in which the stator comprises an outer casing surrounding a ring formed by a number of ring elements each having an apertured rib which spaces the element from the casing, the ribs dividing the space between the casing and the ring into separate compartments, and each rib having a sealing element disposed alongside it to cover the apertures and seal one compartment from the next. The casing and the ring are fixed together by virtue of bolts which have their axes inclined to the radial direction so that tightening the bolts causes the casing to press radially on the sealing elements at the same time as pressing them axially against the respective ribs.

Abstract: A turbjet engine includes various elements for adjustment of play of the stator by having the stator heated or cooled by a gas. The outer housing to which the ferrule bearing the fixed vane stages is secured may be formed of two skins between which the gas is injected. The ferrule may be composed of sectors extending over one circumference fraction and fixed via their center and simply guided at their extremity; finally, it is possible to provide sealing devices between the outer housing and the support bearing surfaces of the ribs of the ferrule elements. The volume between the ferrule and the housing is then sectioned and is able to receive separate gas feedings for play adjustment.

Abstract: Each blade of a stage of variably settable stator blades in a compressor of gas turbine engine is supported at its outer end by a journal which is rotatably mounted in a radial bore in a parallelepipedic journal box of trapezoidal section mounted in a housing of complementary shape formed between connected upstream and downstream rings of the outer casing of the compressor. The blade is held radially in the journal box by two parallel pins arranged longitudinally through the box so as to engage in a peripheral groove extending at least partly around the journal of the blade.

Abstract: The device consists of an arm having structure for attachment to the bottom pivot of a stator blade. Stopping elements are provided in the inner stator ring against which the arm can come to rest. The stopping elements consist of the sides of a circumferential notch formed in the inner surface of the inner ring. A C-shaped molding fastened onto the inner ring makes the notch leak-proof.

Abstract: A device for moving air from the jet flow of an axial compressor of a gas rbine group, to be conducted along the axis of the group to the turbine to be cooled. The air is moved by a wheel having an outer rim serving as a brace between two adjacent compressor disks and centripetal blading which moves the air through openings formed in the rim, to accelerate it and discharge it into a space surrounding the axis of the compressor.