| 摘要 |
PURPOSE:To prevent the temperature of the titled burner from rising locally by a method wherein when compressed air is supplied into an air supply passage between inner and outer cylinders forming the burner, it is flowed into the passage as it is given a swirling velocity component. CONSTITUTION:The reverse flow annular type burner 11 is constituted by the annular outer and inner cylinder 13 and 14 which are arranged concentrically with the axis 12 of the gas turbine and the air supply passage formed between both of the cylinders 13 and 14. The compressed air A from a compressor 15 is flowed into the air supply passage 17 form the exhaust side 14a of the inner cylinder 14 toward a fuel injection nozzle 19. In this case, a part of the compressed air is supplied into a combustion chamber 21 through a combustion air inlet hole 2 of the inner cylinder 14 so that it is mixed with the fuel from the nozzle 19 and burned while the remaining part of the compressed air is supplied into the combustion chamber through a diluting air inlet hole 22 to thereby lower the temperature of a combustion gas B. The above mentioned compressor 15 is so constructed that the configuration of its stationary vane 25 is determined such that the compressed air A has a swirling velocity component when it flows through an outlet 24a of a diffuser 24 of the compressor. |
