| 摘要 |
PURPOSE:To improve a cooling characteristic at a tail cylinder of a combustion unit by a method wherein a double cylinder structure is composed of a tail cylinder, an outer circumference of the tail cylinder and an inner cylinder of the tail cylinder and the annular part is formed to have a cooling passage communicated with combustion air passage. CONSTITUTION:A gas turbine combustion unit 10 is constructed such that a combustion air passage 17 is formed between an outer cylinder 15 of a linear and an inner cylinder 16, and then a combustion chamber 18 is defined within the inner cylinder 16 of the liner. The tail cylinder 20 is fixed to the rear end part of the inner cylinder. Hot combustion gas is guided into the inner cylinder of the tail cylinder 21 to show a hot gas temperature. However, a double cylinder structure is constructed by the outer cylinder 22 and the inner cylinder 21 for the tail cylinder 20, cooling passage 23 is formed within it and it is accelerated when the cooling air is guided from an injecting chamber into the cooling passage 23. As a result, an efficiency of radiation at the surface of the inner cylinder of the tail cylinder is improved, a rate of thermal conduction at the surface of the inner cylinder of the tail cylinder is made superior and the inner cylinder 21 of the tail cylinder is positively cooled. Therefore, it is possible to decrease the temperature in the tail cylinder 20 less than an allowable temperature.
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