Gas turbine layout cooling system bleeds portion of film cooling air through turbine blade via inlet or outlet edge borings for direct blade wall service.

摘要

A small portion of the cooling air is fed into the turbine flow through film cooling borings (33,34) in designed leakage mode. Thermally loaded parts include the combustion chamber walls (12) and/or housing parts of the turbine (13) and/or turbine rotor parts and/or blades (23). The blades are cooled via borings (33,34) at blade inlet edges (52) and/or blade outlet edges (53), the turbine having a series of blade lines to be cooled in sequence. The cooling air is compressed after cooling operations by means of the turbines own compressor (11) or an outside compressor which in turn brings the air up to compressor end air to which it is added. On removal from the compressor (11) the air should be cooled down (19,22) or by direct water spray.