FIELD: machine building.
SUBSTANCE: high temperature gas turbine engine comprises a turbine in which the inner cavity of the cooled second stage nozzle blade at the inlet through the flow rate control damper for cooling air is connected to the intermediate stage of a compressor. The working blade of the second turbine stage is made as a cooled one with an inner cavity which at its inlet is connected to the intermediate compressor stage through an additional flow rate control damper for cooling air. Relation of the passage area Fn.takeoff of the flow rate control damper for the cooling air for the second stage nozzle blade in takeoff mode to the passage area Fn.cruise of the flow rate control damper for the cooling air for the second stage nozzle blade in cruise mode falls within the range 1.5-2.5. Relation of the passage area Fw.takeoff of the flow rate control damper for the cooling air for the second stage working blade in takeoff mode to the passage area Fw.cruise of the flow rate control damper for the cooling air for the second stage working blade in cruise mode falls within the range 2-4.
EFFECT: improved reliability and cost efficiency of a high temperature gas turbine engine by the decrease of air flow for cooling of the working blade of the second turbine stage in cruise mode of the gas turbine engine as compared to that in takeoff mode.
1 dwg
