Patent ID: 7313919
Filing Date: 2008-01-01
Classification: F23R

Abstract:
1. A gas turbine combustor comprising: a combustion chamber supplied with fuel and air; a first fuel supply system and a second fuel supply system; a first group of fuel nozzles for jetting fuel from said first fuel supply system thereby to provide fuel jet flow; a second group of fuel nozzles for jetting fuel from said second fuel supply system thereby to provide fuel jet flow; and a disc member, provided forwardly of said first and second groups of fuel nozzles in a fuel jetting direction, and having air holes corresponding to said fuel nozzles of said first and second groups of fuel nozzles, respectively, wherein said first and second groups of fuel nozzles and said disc member are arranged so that annular air flows are formed around said fuel jet flows in flow paths of said air holes.