CPC F01D 11/24 (2013.01) [F05D 2220/323 (2013.01); F05D 2240/55 (2013.01); F05D 2260/201 (2013.01)] | 10 Claims |
1. A method for controlling a clearance between tips of blades of a rotor of a high-pressure turbine of a gas turbine aircraft engine of an aircraft and a turbine ring of a casing surrounding said blades of the high-pressure turbine, the method comprising:
detecting a transient phase of acceleration of the engine based on at least one parameter representative of the engine;
receiving a data relating to an altitude of the aircraft;
determining data representative of a temperature of said rotor of the high-pressure turbine of the engine during the transient acceleration phase subsequent to determining data representative of a temperature of said rotor of the high-pressure turbine of the engine during a steady speed;
calculating a relative temperature deviation between said temperature data of the transient acceleration phase and the temperature data of the steady speed;
estimating the clearance to be controlled;
if said transient acceleration phase is detected and if said relative temperature deviation is greater than a predetermined minimum temperature deviation, defining a level of opening and a time of opening of a valve by a predefined altitude/relative temperature deviation lookup table; and
controlling the opening of the valve at the opening level and during the opening time defined to deliver an air stream directed to the turbine ring based on said estimated clearance.
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