Gas turbine blade cooling circuit having a cavity with a high aspect ratio
View Patent ↗A blade for a turbomachine gas turbine, the blade having a cooling circuit comprising at least one cooling cavity with a high aspect ratio extending radially between a root and a tip of the blade, and at least one air admission opening at a radially inner end of the cavity to feed it with cooling air, at least one of the walls of the cooling cavity being provided with a plurality of indentations so as to disturb the flow of cooling air in said cavity and increase heat exchange.
1. A blade for a turbomachine gas turbine, the blade including a cooling circuit comprising:
at least one cooling cavity with a high aspect ratio extending radially between a root and a tip of the blade such that said cooling cavity has, in cross-section, a length of camber that is at least three times greater than a width of said cooling cavity, and
at least one air admission opening at a radially inner end of the cooling cavity to feed said cooling cavity with cooling air, wherein
at least one of the walls of the cooling cavity is provided with a plurality of indentations over a first portion of the radial height of the blade so as to disturb a flow of cooling air in said cooling cavity and increase heat exchange, and
said wall is free of said indentations over a second portion of the radial height of the blade different from the first portion.
2. A blade according to claim 1 , wherein the walls of the cooling cavity do not have any flow-disturbing patterns of added material.
3. A blade according to claim 1 , wherein the cooling circuit does not eject any air through the faces of the blade.
4. A blade according to claim 1 , wherein the blade presents a ratio of a thickness of said blade over a radial height of said blade between the root and the tip lying in the range 0.01 to 0.25.
5. A blade according to claim 1 , wherein the blade presents a ratio of a depth of the indentations over the width of the cooling cavity lying in the range 0.15 to 0.65.
6. A blade according to claim 1 , wherein the indentations of the cooling cavity are substantially in alignment parallel with a radial axis of the blade.
7. A blade according to claim 1 , wherein the indentations of the cooling cavity are disposed in a staggered configuration relative to a radial axis of the blade.
8. A blade according to claim 1 , wherein the indentations are formed in the walls of the cooling cavity on the pressure side and on the suction side of the blade.
9. A blade according to claim 1 , wherein the indentations of the cooling cavity are formed in a lower portion of the blade.
10. A blade according to claim 1 , wherein the indentations of the cooling cavity are of substantially spherical shape.
11. A blade according to claim 1 , wherein the indentations of the cooling cavity are of substantially conical shape.
12. A blade according to claim 1 , wherein said indentations are recesses of removed material of said blade formed in said at least one wall of said cooling cavity and said at least one wall of said cooling cavity is free of any added material.
13. A blade according to claim 1 , wherein said width of said cooling cavity is a minimum distance between a pressure side wall of said cooling cavity and a suction side wall of said cooling cavity, wherein said minimum distance is measured between a pressure side wall point located between indentations on said pressure side wall and a suction side wall point located between indentations on said suction side wall.
14. A blade according to claim 13 , wherein said cross-section is within a plane perpendicular to a radial axis of the blade, and said length of camber extends curvilinearly within said plane from a leading edge end of said cooling cavity to a trailing edge end of said cooling cavity.
15. A blade according to claim 4 , wherein said thickness is a maximum distance between a pressure side face of said blade and a suction side face of the blade.
16. A blade according to claim 3 , wherein the cooling cavity is configured such that all of said cooling air fed into said cooling cavity exhausts via the tip of the blade.
17. A blade according to claim 1 , wherein the second portion of the radial height of the blade extends along no less than 70 percent of the height of the blade, measured radially inward from the top of the blade.
18. A blade according to claim 1 , wherein the blade is installed in a low pressure turbine module.
19. A blade according to claim 18 , wherein the blade includes a sealing wiper at a tip of the blade.