Snecma Moteurs

Snecma

Sébastien Imbourg

Philippe Pabion

Jean-Luc Soupizon

Claude Marcel Mons

Jean-Michel Guimbard

Jean-Iuc Soupizon

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

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.

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Yerres, France

Sébastien Imbourg