A turbine vane assembly adapted for use with a gas turbine engine , the turbine vane assembly comprising an airfoil comprising ceramic matrix composite materials and adapted to interact with hot gases flowing around the turbine vane assembly during use of the turbine vane assembly , the airfoil having an outer surface and an inner surface located opposite the outer surface to define an airfoil-shaped cavity that extends radially entirely through the airfoil relative to an axis, a spar comprising metallic materials and located in the airfoil-shaped cavity to receive force loads applied to the airfoil by the hot gases during use of the turbine vane assembly , the spar and the inner surface of the airfoil cooperate to define a cooling passage that extends around the spar , and the spar formed to define a feed duct that extends radially into the spar and a feed hole that extends through the spar and fluidly connects the feed duct with the cooling passage to allow cooling gas to flow from the feed duct into the cooling passage to cool the airfoil , a plurality of ribs that extend outward from the spar partway into the cooling passage toward the inner surface of the airfoil and define cooling channels between the plurality of ribs to distribute a flow of the cooling gas and control local heat transfer between the cooling gas and the airfoil , characterized in that turbulators are located in the cooling channels , and the turbulators include discrete fins that extend from the spar partway into the cooling passage , and the plurality of ribs extend away from the spar by a first thickness, the turbulators extend away from the spar by a second thickness, and the first thickness is greater than the second thickness. an airfoil comprising ceramic matrix composite materials and adapted to interact with hot gases flowing around the turbine vane assembly during use of the turbine vane assembly , the airfoil having an outer surface and an inner surface located opposite the outer surface to define an airfoil-shaped cavity that extends radially entirely through the airfoil relative to an axis, a spar comprising metallic materials and located in the airfoil-shaped cavity to receive force loads applied to the airfoil by the hot gases during use of the turbine vane assembly , the spar and the inner surface of the airfoil cooperate to define a cooling passage that extends around the spar , and the spar formed to define a feed duct that extends radially into the spar and a feed hole that extends through the spar and fluidly connects the feed duct with the cooling passage to allow cooling gas to flow from the feed duct into the cooling passage to cool the airfoil , a plurality of ribs that extend outward from the spar partway into the cooling passage toward the inner surface of the airfoil and define cooling channels between the plurality of ribs to distribute a flow of the cooling gas and control local heat transfer between the cooling gas and the airfoil , characterized in that turbulators are located in the cooling channels , and the turbulators include discrete fins that extend from the spar partway into the cooling passage , and the plurality of ribs extend away from the spar by a first thickness, the turbulators extend away from the spar by a second thickness, and the first thickness is greater than the second thickness. <EOS>