Aircraft gas turbine engine blade tip clearance control

Details Aircraft gas turbine engine blade tip clearance control Aircraft gas turbine engine blade tip clearance control

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 11/14 (2006.01)

Patent

CA 2638250

A method and system adjusts blade tip clearance (CL) between rotating aircraft gas turbine engine blade tips (82) and a surrounding shroud (72) in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance (CL) by expanding or contracting the shroud (72) before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance (CL) may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine (10) and/or on other aircraft.

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