| 摘要 |
Cooling air system for reducing the thermal load on components in the turbine high-pressure region of gas turbines, having blades/vanes which respectively have a plurality of separate flow chambers for different airflows, and having cooling air guidance from the high-pressure region of the compressor into the blading of the high-pressure region of the turbine. Each of the highly loaded blades/vanes has a front flow chamber, at least one central flow chamber and a rear flow chamber. The cooling guidance includes at least one heat exchanger for a part of the cooling air and a flow connection from the heat exchanger to the front and to the rear flow chambers of each blade/vane, with the cooling air guidance to the central flow chamber of each blade/vane bypassing the heat exchanger.
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