| 摘要 |
<p>A seal assembly (215) for a gas turbine engine (100) including a first disk (202) and a second disk (204) is provided. The seal assembly (215) includes a seal member (201), and an interstage seal ring (205) including an axially forward member (201) coupled to a first radially inward surface (230) of the first disk and an axially aft member coupled to a second radially inward surface (231) of the second disk, the seal ring configured to move in an axial direction while the upstream and downstream arms are coupled to the first and second disks respectively.</p> |
