| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine and its stationary blade having a refrigerant recovering type cooling system, capable of cooling in response to the high temperature of a working medium, and capable of optimizing a refrigerant flow rate and a pressure loss. SOLUTION: A part of delivery air of a compressor is extracted, and this air is cooled and boosted. An outer peripheral side flow passage wall 35 of the stationary blade, a blade part 34 and an inner peripheral side flow passage wall 36 are cooled in series by its low temperature-boosted cooling air, and the air is recovered to a combustor. An inside cooling flow passage of the blade part 34 is divided into three cooling flow paths. A blade front edge side first path is formed as a serpentine-shaped flow passage constitution by three flow passage parts 42a to 42c. First and third flow passage parts are formed as an impingement cooling flow passage, and a second cooling flow passage is formed as a convection flow passage. A blade central part is formed as a serpentine-shaped flow passage constitution of convection cooling by three flow passage parts 42d to 42f. The blade rear edge is formed as a through-flow type by an independent one cooling flow passage 42g. COPYRIGHT: (C)2007,JPO&INPIT
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