Cooled turbine vane
AssigneeSafran
InventorsSylvain PAQUIN, Adrien Bernard Vincent ROLLINGER
Life of this patent
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Abstract
The invention relates to a turbomachine turbine vane comprising a root having a blade (12) comprising a leading edge (16) and a trailing edge (17) and a lower surface wall (14) and an upper surface wall (13), as well as: a manifold for cooling (18) the leading edge (16); a supply line (19) for collecting air from the root and supplying the manifold (18); a side cavity (23) extending along the upper surface wall (13) and supplied with air from the root, to form a heat shield facing the supply line (19); and a circuit forming a trombone comprising a middle portion (24) extending along the supply line (19) and extending laterally to the upper surface wall (13), the middle portion (24) being supplied by the supply line at the tip of the blade (12).
Claims11
1-10. (canceled)
Rotary turbine blade of a turbomachine such as a turboprop or a turbojet, this blade comprising a root supporting an airfoil (12) extending along the length (EV) direction and terminating at a tip (S), this airfoil (12) comprising a leading edge (16) and a trailing edge (17) located downstream from the leading edge (16) following the direction of fluid circulation surrounding the airfoil in service, this airfoil (12) comprising an intrados wall (14) and an extrados wall (13) at a lateral spacing from each other and each connecting the leading edge (16) to the trailing edge (17), this airfoil (12) comprising:
- an upstream cooling manifold (18) for the leading edge (16);
- an upstream feed conduit (19) to collect air at the root and to provide a calibrated supply to the upstream manifold (18);
- a single extrados cavity (23) in a single piece along the extrados wall (13) and supplied with air from the blade root, to form a heat shield facing the upstream conduit (19);
- a trombone type circuit comprising a median portion (24) along the part downstream from the upstream conduit (19) and extending laterally as far as the extrados wall (13), this median portion (24) being supplied by the upstream conduit (19) at the tip (S) of the airfoil.
Dependencies are inferred from the claim text.