CPC F01D 5/282 (2013.01) [B29C 70/24 (2013.01); B29C 70/48 (2013.01); F01D 5/147 (2013.01); B29L 2031/082 (2013.01); F05D 2300/6012 (2013.01); F05D 2300/603 (2013.01)] | 20 Claims |
1. A fan or propeller vane for an aircraft turbomachine, the vane being made from composite material and comprising a blade and a root, the root being formed by a longitudinal end of a spar which is formed by a fibrous reinforcement formed of three-dimensionally woven threads and a portion of which extends inside the blade, said blade having an aerodynamic profile defined by a skin formed by woven threads and surrounding said portion of the spar, the spar and the skin being embedded in a polymerized resin, wherein said portion of the spar comprises protruding longitudinal stiffeners which delimit between them spaces for housing longitudinal inserts formed from a cellular material.
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