GAS TURBINE COMBUSTOR

摘要

An annular gas turbine combustor (1) having fuel injection valves (10) arranged on a circle is provided with: pilot injection valves (12) which spray fuel for diffusion combustion into a combustion chamber (8) from outer peripheral pilot nozzles (34); main injection valves (14) which are each provided so as to surround each of the pilot injection valves (12) and which spray fuel for premixed combustion; and flow guides (27) which are mounted downstream of the fuel injection valves (10) and which are configured in such a manner that the cross-sectional area of paths for air and mixture gas extending from the fuel injection valves (10) is gradually increased toward the downstream side.