A ceramic matrix composite (CMC) turbine blade includes an airfoil, a hub extending from the airfoil, and a shank extending from the hub. The airfoil includes a leading edge, a trailing edge, a pressure side, and a suction side. The shank includes a dovetail root having a dovetail path curved in a radial plane. In some embodiments, a leading shank length of the shank at the leading edge and a trailing shank length of the shank at the trailing edge are greater than an intermediate shank length at an intermediate location between the leading edge and the trailing edge. At least one of the airfoil, the hub, and the shank is formed from a CMC. A method of forming the CMC turbine blade includes forming the dovetail root to have a dovetail path curved in a radial plane.