Braided blades and vanes having dovetail roots

A gas turbine engine composite article comprising:

• a composite article airfoil attached to an article inner root and an article outer root,
• the composite article airfoil including article blade pressure and suction sides extending outwardly in a spanwise direction from an article airfoil base or the article inner root to the article outer root at an article airfoil tip,
• the composite article airfoil extending between chordwise spaced apart article leading and trailing edges,
• at least one of the article inner root or the article outer root including an integral article dovetail,
• a core including a core airfoil integrally formed to a core inner root and a core outer root, at least one of the core inner root or the core outer root including a core dovetail,
• the core airfoil including core pressure and suction sides extending outwardly in the spanwise direction from a core airfoil base or the core inner root to the core outer root at a core tip and located within the composite article airfoil,
• a continuous outer three-dimensional braided layer including braided composite material tows braided on the core, and
• the continuous outer three-dimensional braided layer covering the entire core airfoil, the core inner root, and the core outer root.