System and method for impingement cooling of turbine system components

A gas turbine system, comprising:

• a compressor;
• and
• a combustor downstream from the compressor and including:
• a combustor shell defining an outer liner;
• an inner liner disposed inside the combustor shell and having an inner surface defining a cavity configured to receive hot combustion gases from a combustion chamber of the combustor, and an outer surface, the combustor shell and the inner liner defining an annular flow channel therebetween;
• a segment carrier operatively connected to the inner liner and operative to receive an upper portion of the inner liner, the segment carrier and the inner liner defining a purging cavity therebetween;
• and
• a plurality of impingement jet holes formed in the inner liner and providing a flow passage between the annular flow channel and the purging cavity;
• wherein the compressor is configured to supply compressed air to the annular flow channel;
• wherein a first portion of the compressed air is used by the combustor for combustion, producing the hot combustion gases;
• and
• wherein a second portion of the compressed air is directed through the impingement jet holes to the purging cavity to purge the purging cavity of the hot combustion gases.