Method and device for alleviating, in a transonic gas turbine stage comprising a turbine nozzle with guide vanes (101,201) and a rotor (102,202) with rotor blades (103,203), the impact of shocks from at least one of the guide vanes (101,201) on the rotor blades (103,203). According to this method, an unsteady cooling fluid jet is blown from an outlet at the surface of said guide vane (101,201), at or near its trailing edge. This unsteady jet is synchronised with a rotor blade passing frequency so as to have a flow rate minimum when a rotor blade (103,203) is within an area around a shock originating at said guide vane (101,201).
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