Patent attributes
A gas-turbine engine fan blade made of a textile composite material includes short carbon fiber intermediate layers (8) for forming the blade root arranged between splayed carbon fiber layers (7) in the blade root (2). In a compressive stress-affected zone (11) of the blade root, the fiber layers extend parallel to the flanks (12) of the blade root. The diversion of the carbon fiber layers (7) up to the splayed area is effected in a transition area (13). A glass fiber outer layer (10) arranged on the flanks (12) of the blade root gradually runs out at a transition zone (15) of the transition area (13), this zone being diverted at a certain radius. Between the glass fiber outer layer and the outer carbon fiber layer there is a carbon fiber layer (9) oriented at +/−45°.
