Turbulated combustor aft-end liner assembly and related cooling method

In a combustor for a turbine a cover sleeve (140) is disposed between the aft end portion of the combustor liner (118) and a resilient seal structure (38) to define an air flow passage therebetween. The cover sleeve (140) has at a forward end thereof a plurality of air inlet feed holes (146) for dir...

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Bibliographische Detailangaben
Hauptverfasser:	BERKMAN, MERT, SMITH, ANDRE, FULCHER, STEPHEN KENT, BROWN, JEROME D
Format:	Patent
Sprache:	eng ; fre ; ger
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:	In a combustor for a turbine a cover sleeve (140) is disposed between the aft end portion of the combustor liner (118) and a resilient seal structure (38) to define an air flow passage therebetween. The cover sleeve (140) has at a forward end thereof a plurality of air inlet feed holes (146) for directing cooling air into the air flow passage. A radially outer surface of the combustor liner aft end portion defining the air flow passage includes a plurality of turbulators (52) projecting towards but spaced from the cover sleeve (140) and a plurality of supports (144) extending to and engaging the cover sleeve to space the cover sleeve from the turbulators to define the air flow passage.