Gas turbine combustor
View Patent ↗A gas turbine combustor has a combustion chamber into which fuel and air are supplied, wherein the fuel and the air are supplied into said combustion chamber as a plurality of coaxial jets.
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.
2. A gas turbine combustor according to claim 1 , wherein said first fuel supply system and said second fuel supply system each are provided with an individually controllable control valve for controlling fuel flow rate.
3. A gas turbine combustor according to claim 1 , wherein said first group of fuel nozzles are arranged around a central axis of said disc member and said second group of fuel nozzles are arranged around an outer periphery of said first group of fuel nozzles.