| 摘要 |
PROBLEM TO BE SOLVED: To enable a gas turbine to maintain the fuel-air ratios of combustor cans in a prescribed stable combustible range by providing a means which reduces the flow rate of a fluid in the clearance between a flame propagating pipe connecting a plurality of can-type combustors to each other and an outer cylinder covering the outer periphery of the propagating pipe. SOLUTION: Each can type combustor 1a constituting a gas turbine is provided with a diffusion burner 7 having a fuel nozzle 3 which jets fuel 10 for diffusion combustion into the inner pipe 19 of a combustion chamber 2 and a premixing burner 8 having a fuel nozzle 5 which jets fuel 11 for premixing combustion into a premixer 4. Combustion air 12 is supplied to the combustor 1a from a compressor through a flow passage 32 formed between the inner pipe 19 of the chamber 2 and an outer cylinder 21 covering the outer periphery of the pipe 19. In the burner 7, the combustion air 12 and fuel 10 from the nozzle 3 form a circulating vortex of a combustion gas and becomes a stable diffusion flame. The air 12 flowing in the premixer 4 is mixed with the fuel 11 jetted from the nozzle 5 by means of a turning device 9 and jetted into the chamber 2 for combustion. A flow rate reducing means 30 is arranged in the flow passage 22 between a flame propagating pipe 20 and its outer cylinder 21.
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