A control method for cooling a turbine stage (20) of a gas turbine (1), whereby cooling air is bled from combustion air flowing in a compressor (2) of the gas turbine (1), and is fed to a cooling circuit (55) staring from a stator (22) of the turbine stage...

The gas turbine (10) has a compressor (12), a combustion chamber (14) for producing one hot gas, a turbine (16) with multiple turbine blade rings and an air system (24). A regulating unit (V21) is provided in a coolant passage (S1), by which a cooling air ...

A system for cooling components of a turbine (16, 64) includes: at least one input in fluid communication with a source of carbon dioxide gas, the carbon dioxide gas removed from synthesis gas produced by a gasification unit (32) from hydrocarbon fuel; and...

A combustor for a turbine includes a combustor liner (12); a first flow sleeve (28) surrounding the liner, the flow sleeve having a plurality of rows of cooling holes (34) formed about a circumference of flow sleeve; and a transition piece connected to the...