| 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 fibres. 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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