Patent ID: 11891901
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 4:
5. The vane according to claim 1, wherein said blade comprises a second end portion so that the central portion is disposed vertically between the first end portion and the second end portion, said second end portion having in section a third skeleton line delimited transversely by said leading edge and a second downstream limit, and a third chord connecting said leading edge to said second downstream limit, a total length (L3) of the third chord being between 40% and 80% of the total length (L1) of the first chord, said blade comprising a second junction between said central portion and said second end portion, a skeleton angle (α) at the trailing edge of the central portion in the vicinity of said second junction being substantially equal to the skeleton angle (α) of the second downstream limit of the second end portion in the vicinity of said second junction.