Divergent cooling thimbles for combustor liners and related method
AssigneeGeneral Electric Company
InventorsKarthick Kaleeswaran, Ganesh Pejawar Rao
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Abstract
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.
Claims17
A cooling arrangement for a turbine combustor liner comprising:
- a combustor liner;
- a flow sleeve surrounding at least a portion of said combustor liner with a flow annulus therebetween, said flow sleeve having a plurality of rows of cooling holes formed about a circumference thereof for directing cooling air into said flow annulus and toward said combustor liner;
- wherein at least one thimble is fitted within a respective one or more of said cooling holes, said at least one thimble extending in a radial direction toward said combustor liner, and having a peripheral wall diverging in a direction of flow of the cooling air.
A method of cooling a combustor liner surrounded by a flow sleeve comprising:
- a. forming plural cooling holes in said flow sleeve;
- and
- b. fitting thimbles in at least some of said cooling holes, each of said thimbles having a diverging peripheral wall in the direction of flow of cooling fluid through said thimbles toward said combustor liner.
Dependencies are inferred from the claim text.