Turbine blade with heat shield

An airfoil assembly adapted for use in a gas turbine engine, the airfoil assembly comprising

• a root including a root platform and a stem adapted to attach the turbine-blade assembly to the gas turbine engine for rotation about a central axis of the gas turbine engine,
• an airfoil including a spar comprising metallic materials and a heat shield comprising ceramic materials, the spar extending outward from the root platform and formed to include a core body and an airfoil retainer extending outwardly away from the core body, the heat shield shaped to extend around the core body, and the heat shield located in spaced-apart relation to the core body to define cooling passages between the spar and the heat shield, and
• a tip shroud spaced-apart from the root and coupled to the spar to block radial movement of the heat shield relative to the spar.

A method of assembling a turbine-blade assembly adapted for use in a gas turbine engine, the method comprising

• sliding a c-shaped ceramic heatshield over a portion of a metallic spar to form an airfoil, the airfoil arranged to rotate about a central axis of the gas turbine engine, the metallic spar being shaped to define a trailing edge of the airfoil and to block circumferential and axial movement of the heat shield relative to the metallic spar, the heat shield defines a leading edge, a portion of a pressure side, and a portion of a suction side of the airfoil, and
• coupling a tip shroud to the metallic spar, the tip shroud extends circumferentially and axially outward away from the airfoil to block radial movement of the heat shield relative to the metallic spar.