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 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: The distributor sectors (25) of a turbomachine are secured adjacent to a casing (31) with sealing sectors (32) alternating with them in the axial direction. The distributor sectors (25) are 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 10 distributor sectors, and the distributor sectors may be installed by a purely axial movement.

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 housing including an outer casing provided with bearer hooks for stator rings and sealing rings. The hooks are discontinuous angularly and joined to a casing by tenon and mortise assemblies. The hooks and the casing may therefore be made in different materials, the hook material having good resistance to heating and the other material lending itself better to machining and forming. Ventilation, clearance piloting and heat protection are facilitated.

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 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: 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: A housing (21) comprises an outer casing (22) provided with bearer hooks (24) for stator rings (26) and sealing rings(27); hooks (24) are discontinuous angularly and joined to casing (22) by tenon and mortise assemblies (28,29). The hooks and the casing may therefore be made in different materials, the hook material having good resistance to heating and the other material lending itself better to machining and forming. Ventilation, clearance piloting and heat protection are facilitated.

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