Snecma Moteurs

Snecma

Philippe Pabion

Jean-Luc Soupizon

Jean-Michel Guimbard

Sebastien Alain Imbourg

Sébastien Imbourg

Claude Marcel Mons

Eric Roger Schwartz

Emmanuel Charrier

Patrick J Girard

Jean-Iuc Soupizon

Sébastien Prestel

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.

Method of fabricating a casing for turbine stator

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.

Stator turbine vane with improved cooling

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.

Device for balancing a rotating part, in particular a turbojet rotor

The distributor sectors () of a turbomachine are secured adjacent to a casing () with sealing sectors () alternating with them in the axial direction. The distributor sectors () are provided with force resistant faces () through which forces exerted on the distributor sectors are transmitted to the casing. The inner surface of the casing () is smoother and is not fitted with any hooks; consequently, this casing () 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.

Arrangement for the attachment of distributor sectors supporting vanes around an arc of a circle

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.

Turbine casing having refractory hooks and obtained by a powder metallurgy method

The 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 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 () is facilitated, and the assembly is more rigid.

Assembly of sectors of a dispensing unit in a gas turbine

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.

Cooled gas turbine blades

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.

Device for cooling turbine disks

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.

Growing community of inventors

Vaux Le Penil, France

Philippe Pabion