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

Abstract: The invention relates to a turbomachine blade made of composite material and presenting a root with a bulb-shaped end suitable for engaging in a slot of a rotor disk. In characteristic manner, the end of the root of the blade is provided, beside one of its front faces, with a projecting portion having two symmetrical fins about the axial midplane of the root, each fin having a bearing face suitable for limiting tilting of the blade relative to the rotor disk about the axial direction.

Abstract: A turbine stage in a turbomachine is disclosed. The stage includes a wheel mounted in a ring carried by a turbine casing, and a nozzle situated upstream from the wheel and including an annular fastener rim for fastening to the turbine casing, sealing being provided between the outer rim of the nozzle and the upstream end of the ring by a radial annular sheet bearing axially at its inner and outer peripheries against a downstream face of the outer rim of the nozzle, with its middle annular portion being axially spaced apart from the outer rim of the nozzle and bearing axially against the upstream end of the ring.

Abstract: The invention relates to a device for cooling the slots of a turbomachine rotor disk, the device comprising a rotor disk having a plurality of slots and a flange that extends upstream from a radially upstream face of the disk. The device also comprises a retaining annulus having a flange that is placed around the flange of the disk, co-operating therewith to provide a space forming a cooling air diffusion cavity, said cavity opening out into the bottom of each of the slots of the disk, and a plurality of air admission orifices opening out into the diffusion cavity at the upstream end thereof, the cavity having means at its downstream end for reducing the flow rate of air penetrating into the slots of the disk that are situated radially in register with air admission orifices.

Abstract: The invention relates to a device for cooling slots in a turbomachine rotor disk, comprising a rotor disk having a plurality of slots and a flange. The device also comprises blades, each having its root mounted in a respective slot, a retaining annulus having one end mounted against the upstream radial face of the disk, and a flange disposed around the flange of the disk and co-operating therewith to define a space forming a cooling air diffusion cavity that opens out into the bottom of each of the slots, together with air admission orifices opening out into the diffusion cavity at the upstream end thereof, the end of the retaining annulus that is mounted against the upstream radial face of the disk including a plurality of openings that open out radially into the bottom of each of the slots in the disk, at the upstream ends thereof.

Abstract: A device for mounting a suspension member on the casing of a turbine engine is disclosed. The device includes a yoke with at least one lug, secured to the casing, a pin fixed to the yoke supporting the member via a ring surrounding the pin, and a rotation-prevention device that includes a counter-rotation plate attached to the lug. The plate and the pin include an assembly consisting of a peg and of a cutout or a hole, into which the peg fits in order to prevent the pin from rotating in the yoke.

Abstract: A transition channel between a first turbine section and a second turbine section for a gas turbine engine is disclosed. The channel includes a first radially external annular wall including ring sector elements housed inside an annular ring and orifices for injecting a fluid into the channel in order to re-energize the boundary layer thereof, a second radially internal annular wall, and a fluid supply device arranged between the space outside the ring and the injection orifices.

Abstract: A turbine nozzle for a turbomachine, including inner and outer annular platforms connected together by vanes, the inner platform carrying annular elements of abradable material co-operating with annular wipers of a rotor of the turbomachine to form a labyrinth seal, these elements of abradable material being carried by annular sheet-metal sectors of substantially L-, S-, or C-shaped section that are fastened by brazing or welding at their outer peripheries to the inner platform and at their inner peripheries to the elements of abradable material.

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: 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 invention provides a method of fabricating a turbine stator casing, the method comprising the operations consisting in: between the walls of portions of a mold, forming a cavity of shape corresponding to the shape of the shroud of said casing, securing soluble cores to at least one of said mold portions, said cores being held at a distance from the wall of said mold portion and representing empty spaces that are to be formed inside said shroud; putting soluble inserts into place between the cores to represent flow paths between said empty spaces; filling said cavity with a metal alloy powder; sintering said powder by hot isostatic pressing; eliminating the cores and the inserts by dissolving them; and extracting the shroud as molded in this way. The invention is applicable to fabricating a turbine stator casing for an airplane turbojet.

Abstract: It comprises two bearing supports (19) and (23) mounted on an inter-turbine casing (25), a first and a second bearing (2, 4) mounted on said bearing supports, a low-pressure turbine journal (20) mounted rotating with respect to the inter-turbine casing (25), a fixed ferrule (48) and an oil passage (44) provided in the low-pressure turbine journal (20) making it possible to discharge the oil inside the fixed ferrule (48). The ferrule is preferentially widened from the end at which the oil is discharged.

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 present invention relates to a device for mounting a suspension member on the casing of a turbine engine comprising a yoke with at least one lug, secured to the casing, a pin fixed to said yoke supporting said member via a ring surrounding the pin, said device comprising a rotation-prevention means comprising a counter-rotation plate attached to the lug. The device is one wherein said plate and the pin comprise an assembly consisting of a peg and of a cutout or a hole, into which said peg fits in order to prevent the pin from rotating in the yoke.

Abstract: A turbine stage in a turbomachine, the stage comprising a wheel mounted in a ring carried by a turbine casing, and a nozzle situated upstream from the wheel and including an annular fastener rim for fastening to the turbine casing, sealing being provided between the outer rim of the nozzle and the upstream end of the ring by a radial annular sheet bearing axially at its inner and outer peripheries against a downstream face of the outer rim of the nozzle, with its middle annular portion being axially spaced apart from the outer rim of the nozzle and bearing axially against the upstream end of the ring.

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 cooled blade forming an upstream guide vane element for a turbomachine, wherein the airfoil comprises a longitudinal cavity with a first opening at one end and a second opening at the other end, a tubular sleeve being housed in the cavity with a first end in the first opening and a second end in the second opening, first spacers on the side of the first end and second spacers on the side of the second end of the sleeve making a space between the outer face of the sleeve and the wall of the cavity, the blade being arranged so that the sleeve is inserted into the cavity through the first opening. The blade is characterized in that the first spacers are secured to the sleeve and the second spacers are secured to the wall of the cavity of the airfoil. The invention makes it possible to mount the sleeve despite an accentuated curvature of the profile of the airfoil.

Abstract: Device for limiting turbine overspeed in a turbomachine, the turbine comprising a rotor formed of disks mounted on a turbine shaft and carrying moving blades, stages of fixed blades disposed between the disks of the rotor, and means for shearing the moving blades of the upstream disk of the rotor, these means being carried by a circumferential rim of a stage of fixed blades of the turbine.

Abstract: The invention relates to a device for axially retaining blades mounted on a turbomachine rotor disk, the device comprising a rotor disk having a plurality of slots and a flange extending radially outwards, cooperating with a bearing face of the disk to define a groove that is open radially outwards. The device also comprises a plurality of blades, each having a root mounted in a slot of the disk, each blade root having a respective radial bearing face that corresponds to the bearing face of the disk and that has at least one nib extending radially inwards thereover to define a notch that is open radially inwards, and a retaining ring that is mounted against the bearing faces of the disk and of the blade roots, said retaining ring being housed in the groove of the disk, being held outwardly in the notches of the blade roots, and being constituted by a plurality of angular segments placed end to end.

Abstract: The invention relates to a device for cooling the slots of a turbomachine rotor disk, the device comprising a rotor disk having a plurality of slots and a flange that extends upstream from a radially upstream face of the disk. The device also comprises a retaining annulus having a flange that is placed around the flange of the disk, co-operating therewith to provide a space forming a cooling air diffusion cavity, said cavity opening out into the bottom of each of the slots of the disk, and a plurality of air admission orifices opening out into the diffusion cavity at the upstream end thereof, the cavity having means at its downstream end for reducing the flow rate of air penetrating into the slots of the disk that are situated radially in register with air admission orifices.