Patent ID: 7343745
Filing Date: 2008-03-18
Classification: F02C,F23R

Abstract:
1. A gas turbine combustor having a combustion chamber supplied with fuel and air, comprising: a plurality of fuel nozzles for jelling gaseous fuel into said combustion chamber; a plurality of air holes for jetting air into said combustion chamber, said plurality of fuel nozzles and said plurality of air holes being arranged so that coaxial flows, each of which is formed with a fuel jet flow and an air flow flowing on an outer peripheral side of said fuel jet flow, are formed; a disc member having said plurality of air holes formed therein and arranged on a wall surface of said combustor so that gaseous fuel and air of said coaxial jet flows are jetted into said combustion chamber; wherein a flow passage area of each of said air holes is larger than a flow passage area of each fuel hole of said plurality of fuel nozzles; ends of said plurality of fuel nozzles are arranged around inlets of said air holes and at an upstream side of said wall surface of said combustion chamber so that the air from the upstream side of said disc member and gaseous fuel from said plurality of fuel nozzles are rapidly mixed in said combustion chamber after the air and the gaseous fuel are premixed in premixing flow passages of said air holes, and the gaseous fuel is jetted from said fuel nozzles to said air holes, said plurality of fuel nozzles and said plurality of air holes are formed as a single module, and axes of only a part of said plurality of air holes provided in said module are inclined against fuel jet flow axes of said fuel nozzles.