Sealing device for a gas turbine combustor

The present invention discloses a novel apparatus and way for sealing a portion of a gas turbine combustor in order to regulate the flow of compressed air into an annular passage adjacent to a combustion liner. A compressible seal is utilized having a first annular portion, a second annular portion,...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	Jorgensen, Stephen W, Keshava-Bhattu, Ramesh, Giel, David, Metternich, Jeremy
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES ENGINE PLANTS IN GENERAL GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS 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:	The present invention discloses a novel apparatus and way for sealing a portion of a gas turbine combustor in order to regulate the flow of compressed air into an annular passage adjacent to a combustion liner. A compressible seal is utilized having a first annular portion, a second annular portion, and a transition portion, the compressible seal regulates airflow passing through the compressible seal via a plurality of openings and/or axially extending slots.