| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine combustor more improved in reduction of NO<SB>X</SB>and flashback durability in comparison with a current multi-nozzle type pre-mixing combustor. SOLUTION: A plurality of turning blades 10 possible to turn the air for combustion along the inner surface of a combustor inside cylinder 1 are arranged with the predetermined space in the circumferential direction in the periphery of a straight cylinder part 4a of a cone 4 arranged at a central part of a cross section of the combustor inside cylinder 1 to form the diffusion flame with a reaction of the pilot fuel from a pilot fuel nozzle and the air for combustion from a pilot swirler. The air for combustion and the main fuel gas are supplied into the turning blades 10 through an air supply pipe 11a and a gas supply pipe 11b, and the pre-mixed gas formed in the turning blade is injected like the film air from multiple nozzle holes 12, for example a shower head, formed in a blade surface of the turning blades 10. COPYRIGHT: (C)2004,JPO
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