CONTROL METHOD AND UNIT FOR CONTROLLING THE CLEARANCE OF A HIGH-PRESSURE TURBINE TO REDUCE THE EFFECT OF EGT OVERSHOOT
Method for controlling a clearance between the tips of the blades of a rotor of an aircraft engine turbine and a turbine ring, comprising the estimation of the clearance to be controlled and the control of a valve delivering an air stream directed towards the turbine ring based on the thus estimated...
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Main Authors | , , , |
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Format | Patent |
Language | English |
Published |
09.02.2023
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Subjects | |
Online Access | Get full text |
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Summary: | Method for controlling a clearance between the tips of the blades of a rotor of an aircraft engine turbine and a turbine ring, comprising the estimation of the clearance to be controlled and the control of a valve delivering an air stream directed towards the turbine ring based on the thus estimated clearance, this method comprising: the detection of a transient acceleration phase based on at least one parameter representative of the engine; the receipt of a data relating to the altitude of the aircraft; the determination of data representative of the temperature of the rotor during the transient acceleration phase and in steady speed and the calculation of a relative temperature deviation. |
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Bibliography: | Application Number: US202117757981 |