Patent ID: 6840049

Claim:
A gas turbine, comprising: a compressor for generating a compressed combustion air flow which flows along a flow direction; a hot-gas region, including a combustion chamber and a turbine part with a hot gas flow duct; and a cooling air supply system for branching off a cooling air flow from the combustion air flow at a branch position and supplying it to a thermally stressed hot gas component of the hot gas region; wherein a fuel supply device is provided for the supply of fuel to the combustion air flow at a fuel supply position; wherein the fuel supply position is arranged, viewed in the flow direction, before the branch position; wherein the fuel and the cooling air flow are branched directly adjacent a pilot burner into at least two cooling passages inclusive of a first cooling passage and a second cooling passage, the first cooling passage delivering fuel and cooling air flow to the hot gas component; and wherein the cooling air supply system directs at least a portion of the cooling air flow mixed with fuel from the fuel supply device along an inner lining of the combustion chamber via the second cooling passage, through openings in the inner lining, and into the combustion chamber in which the cooling air flow mixed with fuel self-ignites.