ACTIVE CLEARANCE CONTROL SYSTEM AND METHOD FOR AN AIRCRAFT ENGINE

There is provided a system and a method (400) 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 (402). Based on the at least one operational parameter, a current value of the ti...

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Bibliographische Detailangaben
Hauptverfasser:	CRAINIC, Cristina, POISSANT, Jeffrey
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	There is provided a system and a method (400) 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 (402). 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 (404). A limiting factor to be applied to the target value of the tip clearance is computed (406). The limiting factor is applied (408) 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 (410) based on a difference between the current value of the tip clearance and the tip clearance demand.