Abstract: The invention concerns a gas turbine combustion system, including a gas turbine. The gas turbine includes at least one compressor, at least one combustion chamber for generating working gas, wherein the combustion chamber connected to receive compressed air from the compressor, at least one turbine connected to receive working gas from the combustion chamber. The combustion chamber consists of an individual can-combustor or comprising a number of can-combustors arranged in an annular can-architecture, wherein the can-combustor having at least one premixed burner. The ignition of the mixture starts at the premixed burner outlet and the flame is stabilized in the region of the premixed burner outlet by means of a backflow zone. The can-combustor comprising a number of premixed burners arranged uniformly or divided at least in two groups within the can-combustor.

Abstract: A method is provided for determining the approach of the lean blow off (LBO) of a gas turbine engine having at least one combustion chamber into which a fuel is supplied and burnt generating a flame. The method includes determining a value indicative of the gas temperature in recirculation areas adjacent to the flame, and identifying the lean blow off (LBO) approach on the basis of this value. A device for determining the approach of the lean blow off (LBO) is also disclosed.