| 摘要 |
The invention relates to a structure of a seal ring separating surface for a gas turbine, which sets a shape of an end portion in the separation surface to a perpendicular cutting surface and reduces a leaking amount of a sealing air. A seal ring holding ring (1) within a stationary blade fixes brush seals (3, 4) to an upstream side by bolts (5, 6) respectively, so as to form a seal with respect to a rotor disc (69). Further, it fixes and supports a seal ring (2) to a downstream side by a bolt (7) so as to constitute a seal with respect to a seal portion (8) in a disc (69) side. The brush seals (3, 4) and the seal ring (2) are structured such as to have a circular ring shape and a separation construction, and each of the separation pieces has a gap, so that a sealing air leaks to a downward side from an upward side through the gap, however, since the separation piece end portion is formed in a perpendicular cutting surface and a shape of the gap is formed in a bypass passage, a resistance of an air flow passage is increased and a leaking air amount is reduced.
|
