Aircraft gas turbine engine blade tip clearance control

A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud 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 by ex...

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Bibliographische Detailangaben
Hauptverfasser: Hershey, John Erik, Osborn, Brock Estel, Gardner, Donald Lee, Ruiz, Rafael Jose, Herron, William Lee
Format: Patent
Sprache:eng
Online-Zugang:Volltext bestellen
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