Gas turbine with combustor

摘要

The present invention relates to a gas turbine combustor for homogeneous air to flow in by eliminating the turbulences from the air thereby to reduce the combustion instability. In a combustor 3, there are arranged at the center a pilot nozzle 8 and eight main nozzles 7 around the pilot nozzle 8. The air flows in around the individual nozzles 7 and 8 to the leading end of the combustor 3 so that it is used for the combustion. An annular flow ring 20 having a semicircular section is disposed at the upstream end portion of a combustion cylinder 10, and a punching metal (or porous plate) 50 and a surrounding punching metal rib 51 are disposed downstream of the flow ring 20. The air inflow is smoothly turned at first by the flow ring 20 and is then straightened by the punching metal 50 so that the air flows without any disturbance around the individual nozzles 7 and 8 to the leading end thereby to reduce the combustion instability.