Recycle cycle aircraft turbine engine

Abstract

The present invention relates to an aircraft turbine engine (10) comprising: - a centrifugal compressor (14); - a combustion chamber (24); - a turbine (30) including a bladed nozzle diaphragm (31) mounted at the outlet of the chamber (24) and a bladed impeller (33) located downstream of the nozzle diaphragm (31), wherein the bladed impeller (33) is surrounded by a sealing ring (35) supported by an annular support (37) connected to a housing (29); - a system (32) for diffusing and rectifying airflow leaving the centrifugal compressor (14) to supply the combustion chamber (24); - a heat exchanger (38) connected to the diffusion and rectification system (32) via a volute (40); and - a loop (50) for drawing out air and circulating the acquired air to a distributor (31) and / or the sealing ring (35) for cooling.

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