Patent ID: 11873732
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 12:
13. The blade according to claim 1, wherein, in a first section taken through the blade, adjacent to the first end portion, in the radial direction of the blade and from the lower surface face to the upper surface face and over a portion of the height of the blade, one of the second portion and the third portion has an increasing thickness in an outward direction of the radial direction, and the other of the second portion and the third portion has a decreasing thickness in said outward direction; and, in a second section taken through the blade, adjacent to the second end portion, in the radial direction of the blade and from the lower surface face to the upper surface face and over a portion of the height of the blade, said one of the second portion and the third portion has a decreasing thickness in an outward direction of the radial direction, and said other of the second portion and the third portion has an increasing thickness in said outward direction.