GAS TURBINE AND GAS TURBINE COMBUSTOR

摘要

A gas turbine combustor capable of eliminating a disturbance of air flow flowing therein so as to allow air to flow in uniformly in order to reduce the instability of combustion, wherein a pilot nozzle (8) is disposed at the center of the combustor (3) and eight main nozzles (7) are disposed therearound, air flows from therearound through around the nozzles (7) and (8) to the tip thereof for use in combustion, a donut-shaped flooring (20) in semi-circular cross-section is provided at the upstream side end part of a combustion cylinder (10) and a punch metal (porous plate) (50) and a punch metal rib (51) are installed on the downstream side thereof and therearound, respectively, whereby a flow-in air is first directed smoothly by the flooring (20), and then straightened by the punch metal (50), and flows from around the nozzles (7) and (8) to the tip end thereof without causing any disturbance so as to reduce the instability of combustion.