Abstract: A turbine stage for a turbomachine, the stage comprising a rotor wheel mounted inside a sectorized ring carried by an outer casing, and a sectorized nozzle fastened to the casing downstream from the wheel, each ring sector having a downstream end that is held bearing radially outwards against a cylindrical rail of the casing by means of the nozzle, the casing rail including an annular row of through radial notches reducing the areas for heat exchange by conduction both between the casing and the ring sectors and between the casing and the nozzle.

Abstract: Assembly of the connection of an arm to a ferrule is done by imbricating a side wing (21, 23) protruding from the end of the arm (10) and keys (22) bolted to the ferrule (11). The assembly may be supplemented with positioning pins (30).

Abstract: Turbine shroud ring sector for a turbomachine intended to be supported at the upstream end by a downstream support (8) of a turbine casing (3) with circular sliding, comprising a first stop (11) able to collaborate with a second stop (12) borne by an element (13) of said turbomachine adjacent to said shroud ring in order to immobilize it circularly, said sector (4) comprising, on an end facing said element (13), a recess (10) able to allow said second stop (12) to pass to come into contact with said first stop (11), said recess being cut substantially in the form of a rectangle having, at the bottom of the recess (10), corners that are rounded in a circular arc of radius r, wherein the bottom of the recess (10) has a convex shape tangential to the circular arcs of the rounded corners and with a curvature that evolves between a radius of curvature r where it meets the rounded corners and a radius of R, greater than the radius r, at a point situated between the two rounded corners.

Abstract: A joining device including a clevis and a connecting member is disclosed. The connecting member includes a through hole which is housed between a first and a second lug of the clevis. These lugs respectively have a first clevis hole and a second clevis hole. The device further includes a shear pin system passing through each of the holes and includes a threaded end collaborating with a nut system which abuts against the second lug. The shear pin system includes a widened portion passing through the first hole and forming a shoulder situated between the two lugs. The member is situated away from the first lug. A first side of the member is pressed against the shoulder and a second side of the member is pressed against the second lug.

Abstract: The present invention relates to a two-spool gas turbine engine including an HP turbine stator ring and an exterior wall of the transition channel between the HP and LP stages, a first enclosure for controlling the stator ring, and a second enclosure for distributing air for blowing the exterior wall of the transition channel. The engine is characterized in that the two enclosures are placed in communication via an orifice controlled by a valve adapted to be open when the pressure P1 in the first enclosure is greater than the pressure P2 in the second enclosure, and closed when P1<P2.

Abstract: The exhaust casing of a turbomachine includes a cylindrical jacket for guiding a flow of exhaust gas and for defining a hub cavity inside the casing, the jacket including at its ends an annular flange and a radial annular portion extending inwards and formed with an annular rim that is designed to be received in an annular groove of the inner wall of the exhaust casing to close the hub cavity in substantially sealed manner.

Abstract: A sectorized nozzle for a turbomachine, the nozzle being made up of cylindrical sectors and comprising two annular platforms interconnected by substantially radial vanes, together with an annular rail for supporting elements of abradable material, each inner platform having longitudinally-extending edges that are V-shaped, and each rail sector having, on at least one of its sides, means for bearing axially on corresponding means provided on an adjacent nozzle sector.

Abstract: The connection assembly of an arm (10) to a sleeve (11) is carried out substantially by parts of axes (21) crossing the arm and the spacers (26) between the parts of axes and the sleeve and the assembly bolts (32). The assembly and the disassembly are easy, even with highly reduced encumbrance, the connection is light and devoid of high internal efforts and a good position precision is obtained. Application to the stators with an exterior sleeve and, an interior hub and radial link arms, which are encountered in certain turbomachines as in aeronautics.

Abstract: The present invention relates to a joining device (10) comprising a clevis (22) and a connecting member (28), the member (28) pierced with a through hole (30) being housed between a first and a second lug (26a, 26b) of the clevis, these lugs respectively having a first clevis hole (32a) and a second clevis hole (32b), the device further comprising a shear pin system (36) passing through each of said holes (32a, 32b, 30) and comprising a threaded end (46) collaborating with a nut system (44) bearing against the second lug. According to the invention, the shear pin system comprises a widened portion (42) passing through the first hole and forming a shoulder (50) situated between the two lugs, the member situated some distance from the first lug being pressed against the shoulder (50) on the one hand and against the second lug (26b) on the other.

Abstract: The invention relates to an inter-turbine casing (40) for a turbofan (2), comprising an outer ring (44), an inner ring (54), and an intermediate ring (52) between the inner ring and the outer ring, the inner (54) and intermediate (52) rings having respective openings (540, 520) for the passage of cooling air. The casing is distinguished in that it comprises at least one sealing device (80), arranged between the outer ring (44) and the intermediate ring (52), with a base (82), provided with at least one orifice (90) for the passage of cooling air, and a peripheral skirt (84) which is able to be compressed and expanded elastically, the base (82) bearing against the outer ring (44) and the peripheral skirt (84) bearing against the intermediate ring (52).

Abstract: A device for lubricating a component in a turbomachine, in particular a shaft bearing in a turbojet, the device comprising an annular support part defining a lubrication chamber around the component, an annular cover mounted in sealed manner on the part and including a lubricating oil inlet, and an annular channel for passing a flow of pressurizing and cooling air, which channel is formed between the part and the cover, and communicates with ducts in the support part and an annular enclosure formed in the cover for passing the pressurizing and cooling air.