Snecma Moteurs

Societe Nationale D'etude Et De Construction De Moteurs D'aviation-Snecma

Philippe Christian Pellier

Jean-Claude Christian Taillant

Christophe Bernard Texier

Marc R Marchi

Xavier G Coudray

Mischael F Derrien

Mischa&euml;l Fran&ccedil;ois Louis Derrien

Isabelle Marie Monique Valente

Thierry Henri Tassin

Xavier G&eacute;rard Andr&eacute; Coudray

Thierry Henri Marcel Tassin

jean-Michel Roger Fougeres

Yves Maurice Bailly

The invention provides a turbomachine including a device for supplying pressurized gas, the gas being bled from the compressor of the turbomachine via a bleed orifice and cooled in a cooling cavity disposed within the compressor rotor upstream of the bleed orifice. This arrangement has the effect of cooling the bled gas by heat transfer through the outer wall of the compressor rotor to the gas stream which is being compressed by the compressor upstream of the bleed orifice, and has the result of reducing the drop in the performance of the compressor as a result of the gas being bled off.

Turbomachine including a device for supplying pressurized gas

A turbine vane-system cooling system uses three internal cooling cavities 1, 12, 13) separated by two radial walls (9, 10). The upstream cavity (11) uses a helical ramp (30) and is fed through an intake (22) at the vane root (3). The middle cavity (12) also is fed at the vane root (3) and includes a compartmented, multi-perforated lining (40). The air is exhausted from each compartment through impact orifices and enters the succeeding compartment through slots (42) and then is finally exhausted through a vane-head orifice (21). The vane side walls opposite the downstream cavity (13) have double skins with bridging elements. The air passes through these double skins but circulates centrifugally in the upstream portion (15) of the downstream cavity (13) and enters this cavity's downstream portion (16) to be exhausted through slots (19) in the trailing edge (6). A third wall (14) divides the downstream cavity (13) into two parts (15, 16).

Turbine vane cooling system

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Melun, France

Philippe Christian Pellier