Composite material turbomachine blade with a reinforced root

Abstract

The invention relates to a turbomachine blade made of composite material including fiber reinforcement, the blade being obtained by three-dimensionally weaving yarns and densifying with a matrix. The blade comprises a single piece constituting both the airfoil and the root of the blade. The blade root has two substantially plane opposite side flanks that are formed in register with the pressure side and suction side surfaces respectively of the airfoil and it is clamped between two metal plates that are fastened against the side flanks of the root.

1 . A turbomachine blade made of composite material, including fiber reinforcement, the blade being obtained by three-dimensionally weaving yarns and densifying with a matrix, and comprising a single piece constituting both the airfoil and the root of the blade, the blade root having two substantially plane opposite side flanks that are formed in register respectively with the pressure side and suction side surfaces of the airfoil, wherein the blade root is clamped between two metal plates that are fastened against the side flanks of the blade root. 
     
     
         2 . A blade according to  claim 1 , wherein one of the metal plates has a rim that is received under the blade root. 
     
     
         3 . A blade according to  claim 1 , wherein at least one of the metal plates has a hook at an axially downstream end thereof, the hook being designed to receive a retaining ring. 
     
     
         4 . A blade according to  claim 1 , wherein at least one of the metal plates includes a notch at an axially downstream end thereof, the notch being designed to co-operate with a tooth of an annular sealing plate. 
     
     
         5 . A blade according to  claim 1 , wherein the metal plates are fastened against the side flanks of the blade root by welding at least one stud that passes through the plates and the blade root in a direction that is substantially perpendicular to its side flanks. 
     
     
         6 . A blade according to  claim 1 , wherein the metal plates are machined to be dovetail-shaped. 
     
     
         7 . A turbomachine rotor disk including a plurality of substantially axial metal slots at its outer periphery, wherein the disk further includes a plurality of blades according to  claim 1 , each blade having its root mounted in a slot of the disk. 
     
     
         8 . A turbomachine including at least one rotor disk according to  claim 7 .