Patent ID: 6568188
Filing Date: 2003-05-27
Classification: F23C,F23R

Abstract:
A combustor for a gas turbine, comprising:a combustor body; a casing enclosing said combustor body and defining an annular passageway therebetween for carrying compressor discharge air into said combustor body at one end thereof; a reaction zone within said combustor body for main combustion of fuel and air; a first annular manifold surrounding said casing and arranged to extract a predetermined amount of compressor discharge air from said annular passageway; a second annular manifold surrounding said casing manifold and arranged to receive the extracted air, said second manifold located downstream of said first manifold in a combustion flow direction; a conduit for supplying the extracted air from said first manifold to said second manifold; and a plurality of injection tubes in communication with said second manifold for injecting the extracted air into said combustor body downstream of said reaction zone in the combustion flow direction to quench combustion, said injection tubes and said second manifold being disposed in a substantially common radial plane.