US Patent 11873758 Gas turbine engine component with integral heat exchanger

An apparatus is provided for a gas turbine engine. This apparatus includes a vane array and a heat exchanger integrated with the vane array. The vane array includes an inner platform, an outer platform and a plurality of vanes. The inner platform extends circumferentially about a centerline and forms an inner peripheral boundary of a flowpath through the vane array. The outer platform extends circumferentially about the centerline and forms an outer peripheral boundary of the flowpath through the vane array. The vanes extend across the flowpath between the inner platform and the outer platform. The heat exchanger includes a passage following a tortuous trajectory along a first wall of the vane array.