| 摘要 |
PROBLEM TO BE SOLVED: To improve durability and reliability by preventing cracks from being easily generated through the process of reducing thermal stress of a component member, in a gas turbine engine. SOLUTION: In a turbine stationary blade structural body 1, a contiguous blade body 2, arranged downstream of a combustion chamber of a gas turbine engine and having a plurality of stationary blades 3, is jointed annularly, the contiguous blade body 2 is constituted of an inner band 4 for forming the inner peripheral part, an outer band 5 for forming the outer peripheral part, and a plurality of stationary blades 3 fixed between them, an air inlet chamber 10 into which cooling air 12 for cooling the stationary blades 3 is to be introduced is formed outside the outer band 5, and a flange part 6 for shutting off air in the air inlet chamber 10 in combination with a sealing member 7 is provided on the rear end of the outer band 5. The flange part 6 is covered with a heat transfer shutting member 8.
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