Cooling system for HP turbine of aviation jet engine has low pressure chamber for receiving of LP compressed air for additional cooling of guide vane segments and means for dilution-free cross-over of HP and LP compressed air flows

摘要

The cooling system for the high pressure turbine of an aviation jet engine to supply the guide vane segments (2) and connected components of the HP turbine with high pressure cooling air is characterized by a low pressure chamber (12) for the receiving of LP compressed air for the additional cooling of the guide vane segments and means for the dilution-free cross-over of the supplied HP and LP compressed air flows.