A gas turbine includes a compressor section (2) and a turbine section (5) extending along an axis (A); an outer casing (10) and an inner casing (11), delimiting an annular cavity (13) between one another in the turbine section (5); a cooling circuit (7), configured to direct a cooling fluid flow (F) from the compressor section (2) to the annular cavity (13) of the turbine section (5) through cooling inlets (17) in the outer casing (10); and baffles (20) arranged in the annular cavity (13) between respective cooling inlets (17) and the inner casing (11) and configured to intercept at least partof the cooling fluid flow (F) fed through the respective cooling inlets (17) and to prevent the intercepted cooling fluid flow (F) from directly impinging on the inner casing (11).