US Patent 10337334 Gas turbine engine component with a baffle insert

A component of a gas turbine engine, the component having: an internal cooling cavity extending through an interior of the component; a baffle insert configured to be inserted into the internal cooling cavity; a plurality of trip strips extending upwardly from an exterior surface of the baffle insert; and at least one rib extending upwardly from the exterior surface of the baffle insert, wherein the plurality of trip strips and the at least one rib are spaced from an interior surface of the internal cooling cavity.