ACTIVE CLEARANCE CONTROL SYSTEM AND METHOD FOR AN AIRCRAFT ENGINE

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ACTIVE CLEARANCE CONTROL SYSTEM AND METHOD FOR AN AIRCRAFT ENGINE

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POISSANT JEFFREY / CRAINIC CRISTINA

There is provided a system and a method for controlling a tip clearance between a turbine casing and turbine blade tips of an aircraft engine. At least one operational parameter of the aircraft engine is obtained. Based on the at least one operational parameter, a current value of the tip clearance and a target value of the tip clearance are determined. A limiting factor to be applied to the target value of the tip clearance is computed. The limiting factor is applied to the target value of the tip clearance to obtain a tip clearance demand for the aircraft engine. A tip clearance control apparatus of the aircraft engine is controlled based on a difference between the current value of the tip clearance and the tip clearance demand.

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Title :

ACTIVE CLEARANCE CONTROL SYSTEM AND METHOD FOR AN AIRCRAFT ENGINE

Additional title:

SYSTEME DE CONTROLE ACTIF DES JEUX ET METHODE POUR UN MOTEUR D'AERONEF

Contributors:

POISSANT JEFFREY (author) / CRAINIC CRISTINA (author)

Publication date :

2023-01-15

Type of media :

Patent

Type of material :

Electronic Resource

Language :

English

Classification :

IPC:

F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT