| 摘要 |
PROBLEM TO BE SOLVED: To enhance sealing performance of a seal plate interposed between inside and outside shrouds adjacent to each other on the circumference in a sealing structure for a gas turbine stator blade shroud. SOLUTION: Grooves 12a, 12b are formed at axial side faces opposite to each other in outside shrouds 11a, 11b adjacent to each other in a circumferential direction. Bending portions 1a, 1b of a thin seal plate 1 are inserted into the grooves 12a, 12b, respectively. As shown in figures (b) and (c), each of the bending portions 1a, 1b is provided with a resilient tip having a dimension slightly larger than a dimension (t) of the groove. The tips are contracted to be inserted into the grooves 12a, 12b, and then, are fixed inside the grooves 12a, 12b by their resilient effect. The seal plate 1 is adapted to partition an adjacent space from a gas passage 40 and to form an air passage for cooling a blade on a vehicular chamber side of the outside shrouds 11a, 11b. Consequently, it is possible to enhance sealing performance without any generation of a gap between the seal plate 1 and the shrouds due to deformation of the grooves caused by thermal deformation of the shrouds.
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