Asea Brown Boveri Ag

Burkhard Schulte-Werning

Robert Marmilic

In a gas turbine having sequential combustion and two combustion chambers and in each case associated turbines, a secondary guide row (6a-c) formed in an annular transition duct (1) is arranged on the downstream side of the first turbine before entry into the second combustion chamber. A number of blades of this secondary guide row effect an irrotational flow with regard to the mixing elements, which are located in the second combustion chamber and in the flow plane of the blades, which in each case are combined to form an assembly. Due to the irrotational incident flow in the second combustion chamber, the mixing elements produce a uniform separate swirl flow which optimizes the subsequent combustion, designed for self-ignition, with regard to efficiency and pollutant emissions.

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Munich, Germany

Burkhard Schulte-Werning