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: A turbomachine stator vane having a leading edge, a trailing edge, and pressure side and suction side faces, a first and a second series of a plurality of holes, calibrated emission holes, and a perforated open liner defining an annular cavity between an outside wall of the liner and an inside wall of the vane, an air opening for feeding cooling air to the inside of the liner, and an air exhaust opening for exhausting cooling air from the vane, the liner being secured to the vane at one end and being free at another end to slide along an inside edge of the vane under the effects of relative thermal expansion between the liner and the inside wall of the vane. The holes through the liner in the second series of holes are disposed to avoid any impact of the cooling air against the bridges of the vane.

Abstract: A device for balancing a rotating part, in particular a turbine rotor in a turbomachine such as a turbojet or the like, the device comprising at least one balance weight comprising engagement means for engaging it on an annular flange of the part, and locking means associated with the balance weight and with the annular flange to prevent the balance weight from moving relative to the annular flange and to block itself against moving both in rotation and in axial translation relative to the balance weight.

Abstract: A turbine stator casing comprising a jacket and fastener hooks for fastening a turbine distributor nozzle, the hooks projecting from the inside face of the jacket, said jacket being made of a first alloy by hot isostatic compression using metal powder, said fastener hooks being made out of a second alloy that is more refractory than the first, and being secured to said jacket by diffusion welding during the hot isostatic compression. The casing also comprises inserts passing through the fastener hooks and through said jacket. These inserts, which are likewise secured to the jacket by diffusion welding, serve during manufacture of the casing to fasten the hooks to a mold portion inside which the jacket is formed. The invention is applicable to the turbines of airplane turbojets.

Abstract: The retaining hooks (32) of a flange (22) of straightening sectors (20), bearing fixed blades in a turbomachine, are advantageously placed on an end plate (30) distinct from the casing (21) but assembled on the latter. In this way, these hooks no longer constitute weak points in the casing, as if they were all in one piece with it, assembly of the sectors (20) is facilitated, and the assembly is more rigid.

Abstract: A cooled gas turbine blade includes a foundry part and a longitudinal sleeve obtained by the forming of metal sheet. The foundry part includes a longitudinal body provided with a longitudinal cavity with first and second apertures at its ends. The sleeve is mounted in the cavity being held therein by soldering or brazing to the wall of the first aperture, and an end portion of which is free to slide in the second slide-forming aperture. The end portion and the slide are in sliding contact relatively to surfaces formed by machining. A sealing insert can be positioned between the end portion of the sleeve and the wall of the second aperture. This insert can be integral with the sleeve.

Abstract: In a turbomachine stator vane having a leading edge, a trailing edge, and pressure side and suction side faces, and including a perforated open liner defining an annular cavity between an outside wall of the liner and an inside wall of the vane, an air admission opening for feeding cooling air to the inside of the liner, and an air exhaust opening for exhausting a fraction of this cooling air out from the vane, the liner being secured to the vane at one end and being free at another end to slide along an inside edge of the vane under the effects of relative thermal expansion between the liner and the inside wall of the vane, provision is made for the open liner to comprise a plurality of holes distributed over only two determined zones of said liner, a first series of holes being disposed facing the inside wall of the leading edge and a second series of holes being disposed facing the inside wall of the trailing edge, the holes through the liner in the second series of holes also being disposed in such a mann

Abstract: A turbine disk cooling device fed with cooling air from an orifice through an annular support platform for a fixed vane of a low-pressure turbine is disposed between an upstream flange and a downstream flange of the support platform. The device includes upstream and downstream annular plates longitudinally defining an annular cavity, a sealing device extending longitudinally between the upstream and downstream plates so as to close the cooling air cavity, an element to hold the upstream and downstream plates against upstream and downstream flanges of the support platform, and a plurality of holes for ejecting cooling air towards the turbine disks.

Abstract: An annular platform for the nozzle of a low-pressure turbine in a turbomachine, said nozzle having a longitudinal axis and comprising at least one fixed vane disposed downstream from at least one moving blade of a high-pressure turbine, said platform comprising a downstream portion supporting said fixed vane radially defining an aerodynamic channel which extends longitudinally between a leading edge of said fixed vane and a trailing edge of said moving blade, said platform further comprising an upstream portion extending longitudinally beyond the leading edge of said fixed vane towards the trailing edge of said moving blade so as to lengthen said aerodynamic channel.

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: A turbine stator casing comprising a jacket and fastener hooks for fastening a turbine distributor nozzle, the hooks projecting from the inside face of the jacket, said jacket being made of a first alloy by hot isostatic compression using metal powder, said fastener hooks being made out of a second alloy that is more refractory than the first, and being secured to said jacket by diffusion welding during the hot isostatic compression. The casing also comprises inserts passing through the fastener hooks and through said jacket. These inserts, which are likewise secured to the jacket by diffusion welding, serve during manufacture of the casing to fasten the hooks to a mold portion inside which the jacket is formed. The invention is applicable to the turbines of airplane turbojets.

Abstract: A device for balancing a rotating part, in particular a turbine rotor in a turbomachine such as a turbojet or the like, the device comprising at least one balance weight comprising engagement means for engaging it on an annular flange of the part, and locking means associated with the balance weight and with the annular flange to prevent the balance weight from moving relative to the annular flange and to block itself against moving both in rotation and in axial translation relative to the balance weight.

Abstract: A connection device between a nozzle and a feed enclosure for feeding cooling fluid to at least one injector in a turbomachine, the device comprises at least one bushing having open axial ends engaged in orifices in a wall of the nozzle and in a wall of the feed enclosure, together with retaining means for retaining the bushing axially, the retaining means being formed to project from an outer cylindrical surface of the bushing between the axial ends of the bushing and at a distance from said ends.

Abstract: Distributor sectors (25) on which fixed vanes are placed adjacent to a casing (31) by means of sealing sectors (32) alternating with them in the axial direction and provided with force resistant faces (37; 39) through which forces exerted on the distributor sectors are transmitted to the casing. The inner surface of the casing (31) is smoother and is not fitted with any hooks; consequently, this casing (31) is less complicated to make and is less mechanically stressed to retain the distributor sectors, and the distributor sectors may be installed by a purely axial movement.

Abstract: The present invention concerns a cooled gas turbine blade comprising a foundry part and a longitudinal sleeve obtained by the forming of metal sheet, the foundry part including a longitudinal body provided with a longitudinal cavity with first and second apertures at its ends, the sleeve being mounted in the cavity being held therein by soldering or brazing to the wall of the first aperture, and an end portion of which is free to slide in the second slide-forming aperture. The blade is characterized by the fact that the end portion and the slide are in sliding contact relatively to surfaces formed by machining.

Abstract: An assembly of turbine distributor sectors in a casing. Retaining hooks of a flange of straightening sectors, bearing fixed blades in a turbomachine, are advantageously placed on an end plate distinct from the casing but assembled on the casing. In this way, these hooks no longer constitute weak points in the casing, as if they were all in one piece with it, assembly of the sectors is facilitated, and the assembly is more rigid.

Abstract: An annular platform for the nozzle of a low-pressure turbine in a turbomachine, said nozzle having a longitudinal axis and comprising at least one fixed vane disposed downstream from at least one moving blade of a high-pressure turbine, said platform comprising a downstream portion supporting said fixed vane radially defining an aerodynamic channel which extends longitudinally between a leading edge of said fixed vane and a trailing edge of said moving blade, said platform further comprising an upstream portion extending longitudinally beyond the leading edge of said fixed vane towards the trailing edge of said moving blade so as to lengthen said aerodynamic channel.

Abstract: A cooling device for cooling disks of high-pressure and low-pressure turbines of a turbomachine, said device being fed with cooling air from at least one air orifice formed through a bottom annular platform for supporting at least one fixed vane of said low-pressure turbine and being disposed between an upstream flange and a downstream flange of said bottom platform, the device comprising: an upstream annular plate extending radially from the upstream flange of said bottom platform; a downstream annular plate extending radially from the downstream flange of the bottom platform, said upstream and downstream plates longitudinally defining at least one annular cavity for cooling air; a sealing device extending longitudinally between said upstream and downstream plates so as to close the cooling air cavity in leaktight manner; holding means for holding said upstream and downstream plates against the upstream and downstream flanges of said bottom platform; and a plurality of holes for injecting cooling air towards

Abstract: The pivots (2) of the blades (1) comprise removable portions (16) located at their outer end and adjustable in height using a thread (17) or a similar means in order to adjust the distance between the head (9) of a lever (10) controlling the adjustment of the blade and the casing (4) or the collar (8) of a bearing (5); if the centring bushings (7) of the bearings (5 and 6) are worn, harmful tilting of pivots (2) will be limited by a stop for the head (9).

Abstract: A separate inter-blade platform for a bladed rotor disk of a turbo-machine comprises a first part in the form of a four-sided frame of generally trapezoidal shape and made of a laminated material, the frame having smaller and larger ends for location on the upstream and downstream sides respectively of the rotor disk, and two lateral sides interconnecting said ends for location between successive blades of the rotor, and a second part made of a relatively flexible and self-adhesive material of the polyurethane type attached to the first part, the second part defining a plate capping the frame over the greater part of its two lateral sides and leaving the smaller and larger end portions free, a portion enclosing the two lateral sides of the frame in line with the plate, and a plurality of evenly spaced, transverse reinforcing ribs which are integral with said enclosing portion and the underside of the plate.