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

Claim 0:
1. A blade comprising:
a reinforced leading edge, a trailing edge, and extending between the leading edge and the trailing edge while being limited by a lower surface face and an upper surface face which are two main aerodynamic faces of the blade, opposite in a direction of the thickness of the blade and each extending from the leading edge to the trailing edge; the blade being formed of a first portion, made in one piece of a first material, made of a first end portion comprising the leading edge, of a second end portion comprising the trailing edge and of a core connecting the first end portion to the second end portion, the first end portion and the second end portion each comprising a strip of each of the main aerodynamic faces; of a second portion, extending between the first end portion and the second end portion and joined to a main face of the core, made of a second material lighter than the first material, and carrying a zone of a first one of the main aerodynamic faces between the strips of said first aerodynamic face belonging to each of the end portions; and of a third portion, joined to a second main face, opposite the first main face, of the core, carrying a zone of a second one of the main aerodynamic faces between the strips of said second aerodynamic face belonging to each of the end portions, and made of a material lighter than the first material; wherein the core has, over at least a portion of the height of the blade, an oblique extension in the direction of thickness, the second portion having a greater thickness adjacent the second end portion than adjacent the first end portion, and the third portion having a greater thickness adjacent the first end portion than adjacent the second end portion.