| 摘要 |
The invention pertains to a seal element (1) for sealing a gas-path leakage-gap (5) between spaced apart first and second components (2,3) of a turbo machinery (22), which first and second components (2,3) having opposing inner and outer surfaces (9, 10) situated outside the leakage-gap (5). The seal element (1) comprises a generally gas impervious sealing member (4) and a layer (6) comprising ceramic fibers. The layer (6) covers at least partially said sealing element (1) and defines a sealing surface (21) for contacting outside the gap (5) the outer surfaces (10) of the first and second components (2,3) of the turbo machinery (22). The inventions further pertains to a combustion turbine (22), which comprises plurality of components (2,3) disposed in axial and circumferential direction, said components including guide-blade plates (12) of guide blades (16) and wall components (13), which are spaced apart in the circumferential direction or the axial direction by a leakage-gap (5) sealed off by a seal element (1).
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