Air deflector for a cooling circuit for a gas turbine blade

1. A gas turbine blade comprising an internal cooling circuit consisting of at least one cavity extending radially between the base and tip of the blade, at least one air inlet aperture at one radial end of the cavity and at least one air outlet orifice opening into the cavity and emerging onto one of the faces of the blade, at least one of the walls of said cavity of the cooling circuit comprising at least one air deflector whereof the shape and dimensions are adapted to project the air flowing along said wall of the cavity towards an opposite wall of said cavity whilst avoiding re-attachment of the boundary layer immediately downstream of said air deflector, wherein the air deflector has an inclined ramp that has a length (L) of between 2 and 4 times its height (h) so as to project the air flowing along the wall of the cavity towards the opposite wall.

2. The blade as claimed in claim 1 , wherein the inclined ramp of the air deflector has a radius of curvature (R) of between 20 and 30 mm.

3. The blade as claimed in claim 1 , wherein the inclined ramp of the air deflector has a height (h) corresponding to approximately 37.5% of the distance separating the two opposite walls of the cavity of the cooling circuit.

4. The blade as claimed in claim 1 , wherein the wall of the cavity of the cooling circuit comprising the air deflector is disposed on a convex side of the blade and the wall of said cavity onto which the air is projected is disposed on a concave side of the blade.

5. The blade as claimed in claim 1 , wherein the air deflector is disposed on the wall of the cavity of the cooling circuit in the region of an attachment zone of the blade.

6. The blade as claimed in claim 1 , wherein the air deflector is disposed on the wall of the cavity of the cooling circuit in the region of the tip of the blade.

7. The blade as claimed in claim 1 , wherein the internal cooling circuit comprises at least two cavities, the air deflector being positioned in the region of a passage connecting the radial end of one cavity with a neighboring radial end of the other cavity.

8. The blade as claimed in claim 1 , wherein the walls of the cavity of the cooling circuit are provided with a plurality of flow disrupters intended to increase the heat transfers along these walls.

9. A gas turbine comprising a plurality of blades as claimed in claim 1 .

10. A turbine engine comprising a gas turbine having a plurality of blades as claimed in claim 1 .