Patent ID: 6679061
Filing Date: 2004-01-20
Classification: F23C,F23R

Abstract:
Premix burner arrangement comprising a pilot fuel feeding means for operating a combustion chamber of a gas turbine arrangement, a double cone premix burner wherein at least one fuel addition unit as well as supply air openings have been provided in such a way that gaseous and/or liquid fuel can be mixed with combustion supply air inside the premix burner and form a fuel/air mixture, which exits from the premix burner downstream in the direction towards the combustion chamber positioned after the premix burner and which can be ignited inside the combustion chamber in the form of a spatially largely stationary flame,wherein outside of the premix burner, a catalyzer unit is provided, through which the pilot fuel is injected from the side and feeding is performed in such a way that a pilot fuel/air mixture flows through the catalyzer unit and can be converted at least in part catalytically in the catalyzer unit, and flows as a mass flow that stabilizes the flame into the combustion chamber, the pilot fuel feeding means being immediately adjacent the double cone premix burner, and wherein a rich pilot fuel/air mixture passes through the catalyzer unit and forms a H2/CO mixture, thereby stabilizing the flame front chemically.