Divergent cooling thimbles for combustor liners and related method

A cooling arrangement for a turbine combustor liner includes a combustor liner; a flow sleeve surrounding at least a portion of the combustor liner with a flow annulus therebetween, the flow sleeve having a plurality of rows of cooling holes formed about a circumference thereof for directing cooling...

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Hauptverfasser: RAO GANESH PEJAWAR, KALEESWARAN KARTHICK
Format: Patent
Sprache:eng
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Zusammenfassung:A cooling arrangement for a turbine combustor liner includes a combustor liner; a flow sleeve surrounding at least a portion of the combustor liner with a flow annulus therebetween, the flow sleeve having a plurality of rows of cooling holes formed about a circumference thereof for directing cooling air into the flow annulus and toward the combustor liner. One or more of the cooling holes is fitted with a thimble extending in a radial direction toward the combustor liner, the thimble having a peripheral wall diverging in a direction of flow of the cooling air.