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

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

Societe Dassault Aviation

Xavier G Coudray

Mischael F Derrien

Philippe M Pichon

Jean-Claude Christian Taillant

Christophe Bernard Texier

Mathieu Philippe Bichon

Jean-Francedillaois Georges Lacuisse

Thierry Henri Tassin

Philippe Christian Pellier

Christophe Nicolas Huon De Kermadec

Bruno Andre Rolland

jean-Michel Roger Fougeres

Yves Maurice Bailly

Alex Pierre Deblois

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

A method of manufacturing a hollow machine blade consisting of two skins ining an internal cavity and interconnected by stiffeners comprises:

Method and manufacturing a hollow turbomachine blade

A hollow turbine blade having at least one first row of holes disposed in the leading edge zone of the blade so that each hole communicates with a longitudinal internal cavity of the blade which, in use, is supplied with cooling air, is also provided with at least one second row of holes in the leading edge zone, each hole of the second row intersecting at one end a respective hole of the first row and opening at its other end in the outer surface of the blade.

Cooled turbine blade

A turbo-machine vane having a plurality of internal cavities for the flow of a cooling fluid, and a plurality of openings through the outer wall of the vane for communicating the internal cavities with the outside of the vane. Two rows of openings are provided in the leading edge of the vane, one row on each side of the central line of the leading edge end extending parallel with the central line, and each opening of each row is oriented to direct cooling fluid which flows through it from the interior of the vane away from the central line relative to the rows.

Cooled turbo-machine vane

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Fontainebleau, France

Xavier G Coudray