| 摘要 |
A gas turbine combustor and a gas turbine are configured in such a manner that a combustor inner tube (42) is provided with: an air path (54) which supplies high-pressure air for combustion; a pilot nozzle (44), a main fuel nozzle (45), and a top hat nozzle (47) which supply fuel; and an opening (64) which supplies film air (cooling air). Flow restriction members (71, 72, 73) are provided to the inner wall surface of the combustor inner tube (42) so as to extend in the circumferential direction of the inner wall surface and to be provided at positions located downstream in the flow direction of a combustion gas. The flow restriction members (71, 72, 73) are provided in predetermined regions in the circumferential direction excluding the regions of through sections (74, 75, 76) which do not disturb the flow of the film air, and as a result, the generation of carbon monoxide can be suppressed and the occurrence of unstable combustion is suppressed. |
