US Patent 10883371 Ceramic matrix composite vane with trailing edge radial cooling

A component adapted for use in a gas turbine engine includes an aerofoil configured to interact with gases flowing through the gas turbine engine along a gas path. The aerofoil is formed to include a first passage that extends radially at least partway into the aerofoil and a second passage that extends radially into the aerofoil at a trailing edge of the aerofoil.