Patent ID: 11686249

Abstract:
An aircraft turbine engine having a primary air flow path with low-pressure and high-pressure compressors, a secondary air flow path which is located around the primary path and runs coaxially thereto, the turbine engine including vanes distributed about a main axis of the turbine engine. A pressurized air circuit draws air between the low-pressure compressor and the high-pressure compressor or in the high-pressure compressor and supplies at least one component located close to a main axis of the turbine engine. The pressurized air circuit includes a heat exchanger between the stream of pressurized air and the stream of air flowing in the secondary path, the heat exchanger being arranged in at least one of the straightening vanes, where a heat exchanger pipe is arranged, the pipe having a pressurized-air inlet and a pressurized-air outlet that are located at the same radial end of the vane.