Patent ID: 8100662

Claim:
A gas-turbine engine fan blade made of a textile composite material, which turbine blade comprises an airfoil and a blade root for retention in a recess of a rotor disk, the turbine blade comprising: a plurality of carbon fiber layers extending parallel to an airfoil axis in the airfoil and also forming: a quasi unidirectionally reinforced carbon fiber-plastic carrying structure, an airfoil root tapering in the blade root, a transition area which extends from a start of the airfoil root on both sides, and in which the carbon fiber layers are diverted from a position parallel to the airfoil axis via an outer, load-adequate transition zone to a position splayed in accordance with a geometry of the blade root, and a compressive stress-affected zone, in which the previously diverted carbon fiber layers extend parallel to flanks of the blade root positioned in the recess of the rotor disk, with a plurality of carbon fiber intermediate layers individually arranged between the splayed carbon fiber layers, a glass fiber outer layer positioned on each flank of the blade root; and a further carbon fiber layer, haying a fiber orientation of +/−45° to a fiber orientation of the carbon fiber layers of the carrying structure, positioned between the carrying structure and each glass fiber outer layer.