Patent ID: 7621130

Claim:
A combustion system for a gas turbine comprising: a premixing chamber for air which is mixed with fuel injected from a series of holes creating a main central flame which is formed in a flame tube, said premixing chamber is convergent towards a connection end with a combustion chamber comprising the flame tube; the flame tube being connected to the premixing chamber through a tapered portion, the tapered portion having a series of holes positioned along a circumference of the tapered portion coaxial with a longitudinal axis of the flame tube; a series of pilot devices distributed in the series of holes of the tapered portion and configured to premix fuel gas prior to injecting the fuel gas into the combustion chamber and create a series of corresponding pilot flames configured to stabilize the main central flame, at the same time reducing the polluting emissions; and each of the series of pilot devices includes a sub-pilot device configured to inject pilot fuel gas into the respective pilot device prior to mixing the pilot fuel gas and produce diffusion flames for stabilizing the pilot flame.