Cooling air system for gas turbine

A cooling air system for reducing thermal loading on components in a turbine high-pressure region of a gas turbine, which includes at least one first compressor, a combustion chamber and a turbine, comprising:

• a plurality of blades/vanes through which cooling air flows and including a plurality of separate flow chambers within a blade/vane aerofoil for different airflows, each blade/vane having a first flow chamber in a region of its leading edge, at least one second flow chamber in a central region of its profile and a third flow chamber in a region of its trailing edge;
• and
• a cooling air guidance arrangement surrounding a high-temperature zone of the combustion chamber, the cooling air guidance arrangement configured to guide cooling air from one of the high-pressure region and an outlet region of the first compressor into a blading of the high-pressure region of the turbine, the cooling air guidance arrangement including at least one heat exchanger configured to reduce a temperature of a partial flow of the cooling air from the first compressor and at least one flow connection from an outlet of the heat exchanger to the first flow chamber and the third flow chamber of each blade/vane, the cooling air guidance arrangement extending directly to the at least one second flow chamber and bypassing the heat exchanger.