FIELD: machine building.
SUBSTANCE: method of clearance control between tips of turbine rotor blades of the gas turbine aircraft engine at one side and ring-like bandage of turbine casing enclosing the blades from the other side, wherein the method includes a stage when flow speed and/or temperature of air directed to the casing are controlled. The method contains the stage when the period of shutdown (t) of the aircraft engine according to temperature (T495(t)) is determined, the temperature is measured by the temperature transmitter comprising sensor, located in free space of the aircraft engine, and model depending on time of change of the said temperature with time during the aircraft engine shutdown on ground.
EFFECT: increased accuracy of clearance control.
5 cl, 5 dwg
