Tunable transition duct side seals in a gas turbine engine

A system and method for tuning a gas turbine combustion system having a plurality of seals positioned between the combustion system and the turbine inlet is disclosed. The system and method provide ways of permitting a predetermined amount of compressed air to bypass the combustion system and enter...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser: STUTTAFORD PETER, CREIGHTON SHERMAN CRAIG, ELLIS CHARLES, HENRIQUEZ DAVID JOHN
Format: Patent
Sprache:eng
Schlagworte:
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