COMBUSTOR LINER COOLING ASSEMBLY FOR A GAS TURBINE SYSTEM
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United States of America Patent
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Issued Date -
Dec 19, 2013
app pub date -
Jun 13, 2012
filing date -
Jun 13, 2012
priority date (Note) -
Abandoned
status (Latency Note)
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Abstract
A combustor liner cooling assembly for a gas turbine system includes a combustor liner defining a combustor chamber. Also included is a flow sleeve surrounding at least a portion of the combustor liner, wherein the flow sleeve includes at least one aperture row comprising a plurality of apertures, each of the plurality of apertures impinging a cooling flow jet onto the combustor liner. Further included is a plurality of flow redirecting components disposed proximate an aft end of the flow sleeve, wherein the plurality of flow redirecting components divert an impingement cross-flow flowing relatively perpendicular to the cooling flow jet, thereby providing the cooling flow jet an undisturbed flow path to the combustor liner.
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