In a gas turbine (1) for aeronautic engines, a stator body (5) delimited by an outer lateral surface (6) is cooled by an air cooling device (8) having a plurality of circumferential tubes (11) for distributing air on the outer lateral surface (6); each circumferential tube (11) having a plurality of outlets (12, 30) for guiding respective cooling airflows (13) towards the outer lateral surface (6) and into a respective circumferential channel (16) obtained between two groups of circumferential channels (18) adjacent to each other and lapped by the flow of air leaving the circumferential channel (16).
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