Patent ID: 8316645

Claim:
A triple swirl gas turbine combustor comprising: a case to which an igniter is attached; a combustor liner where ignition is performed by the igniter and having a compressed air inlet, formed at a side of the case, through which compressed air is introduced from a gas turbine compressor and a plurality of cooling air inlets; and a burner having an air feeding swirler including first, second, and third swirlers with fuel jetting swirl vanes which are concentrically disposed inside a burner head positioned at the upper side of the combustor liner to generate a vortex in the compressed air, wherein the first swirler, the second swirler, and the third swirler are concentrically disposed in that order from a central shaft of the air feeding swirler, wherein the third swirler is located axially upstream of the first and second swirlers from a flame in the combustor liner, wherein each of the fuel jetting swirl vanes of the first, second, and third swirlers includes a fuel injecting hole formed at a side of a vane blade and fuel jetting holes formed in the longitudinal direction to jet fuel introduced through the fuel injecting hole, and wherein distances between fuel passages positioned at lower sides of the first, second and third swirlers increase as the fuel passages are located more outwardly from a center, such that a space between fuel passages of the second swirler is larger than a space between fuel passages of the first swirler and smaller than a space between fuel passages of the third swirler.