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AssigneesSafran Aircraft Engines, Safran
InventorsClément Pierre Postec, Vincent Lionel René Maison, Pierre Jean Faivre D'arcier, Mattéo Minervino, François Charleux
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A propeller blade or airfoil for a turboprop engine made from composite material including a matrix-densified fibrous reinforcement, the propeller blade or airfoil including, in the direction of its span, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having three-dimensional weaving with a root preform portion and an aerodynamic profile preform portion. The fibrous preform includes a separation delimiting a recess that forms a cavity extending both into the root and into the aerodynamic profile. A spar is present in the cavity, the spar including an aerodynamic profile shaping portion positioned in a first portion of the cavity and a root shaping portion positioned in a second portion of the cavity. The root has a rotationally symmetric shape.
A method for manufacturing a propeller blade or airfoil for a turboprop engine made from composite material comprising a matrix-densified fibrous reinforcement, the method comprising:
A propeller blade or airfoil for a turboprop engine made from composite material comprising a matrix-densified fibrous reinforcement, the propeller blade or airfoil comprising, in a direction of its span, a root and an aerodynamic profile, the root and the aerodynamic profile extending in a chord direction between a leading edge and a trailing edge, the fibrous reinforcement comprising a fibrous preform having a three-dimensional weave with a root preform portion present in the root and an aerodynamic profile preform portion present in the aerodynamic profile, the preform portions of root and aerodynamic profile being connected to one another by the three-dimensional weave, wherein the fibrous preform comprises a separation delimiting an inner recess opening at the root preform portion, the recess forming a cavity extending both into the root and into the aerodynamic profile, the separation extending in the chord direction between a front edge and a rear edge of the fibrous reinforcement, which correspond to, respectively, the leading-edge and the trailing-edge of the propeller blade or airfoil, and the separation being set back from said front and read edges of the fibrous reinforcement so as to preserve linking portions that are respectively adjacent to the front edge and the rear edge, wherein a spar is present in the cavity, the spar comprising an aerodynamic profile shaping portion positioned in a first portion of the cavity and a root shaping portion positioned in a second portion of the cavity, and wherein the root of the propeller blade or airfoil has a rotationally symmetric shape.
Dependencies are inferred from the claim text.