| 摘要 |
PROBLEM TO BE SOLVED: To provide a seal part structure of a gas turbine capable of preventing combustion gas from flowing into the inside of an inner circumferential casing, improving durability and reducing material cost. SOLUTION: A plurality of projection parts 16 are formed on the inner circumferential casing of the downstream side of a stationary blades, projecting ridge- shaped in the radial direction toward the outer side from the surface of the inner circumferential casing, and extending along the direction of the flow of the combustion gas from near the trailing edge 2a of the stationary blades to near the space between the stationary blades and rotor blades.
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