| 摘要 |
PROBLEM TO BE SOLVED: To provide a technique effectively preventing burning of a portion of a gap between a tail pipe of a combustor and a stator vane shroud, caused by non-uniform combustion gas pressure in a circumferential direction of a stator vane row. SOLUTION: A gas turbine includes: the combustor 3 blowing combustion gas 3a from the tail pipe 4; and a turbine to which the combustion gas 3a is supplied from the tail pipe 4. The turbine includes stator vanes 5 and the stator vane shrouds 6 positioned downstream of the tail pipe 4 to support the stator vanes 5. An opening 4c is formed at a downstream end part 4a of the tail pipe 4 to blow cooling air 13 to upstream end parts 6a of the stator vane shrouds 6. The cooling air 13 is blown from the downstream end part 4a of the tail pipe 4 to the upstream end parts 6a of the stator vane shrouds 6, so as to effectively prevent the combustion gas 3a from entering into the gap between the tail pipe 4 and the stator vane shroud 6. COPYRIGHT: (C)2011,JPO&INPIT
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