Turbine cooling and thermal control

Claim 1

In a gas turbine system having a multi-stage compressor, a turbine having a turbine stator, and a turbine rotor having a bore; a coolant path in contact with said bore including a high pressure plenum, labyrinth seal means for restrictively supplying high temperature air from substantially the compressor outlet to said high pressure plenum, a mixing plenum, labyrinth seal means for restrictively passing air from said high pressure plenum to said mixing plenum, means for conveying air from said mixing plenum in contact with said bore and thereafter discharging the air into the main gas flow; means for passing low temperature air from a low stage of said compressor to said mixing plenum; the improvement comprising: said means for passing low temperature air comprising means for directly conveying low temperature air to said mixing plenum; valve means for stopping and modulating said low temperature airflow; said turbine comprised of a high pressure turbine, and a low pressure turbine having a low pressure turbine bore; said compressor having a bore; an intermediate pressure plenum located to receive air from said mixing plenum after contact with said turbine bore; conveying means for conveying air from said compressor in contact with said compressor bore to said intermediate pressure plenum; labyrinth seals restricting flow from said intermediate pressure plenum to said low pressure turbine bore; and loose seals restricting flow from said intermediate pressure plenum to the main flow path whereby a high flow of said low temperature air will increase air flow through said loose air seal, deterring hot gas ingestion into said intermediate pressure chamber.