| 摘要 |
A seal assembly (52, 54) for a gas turbine engine (10). The seal assembly (52, 54) includes a first seal member (40) including an abradable structure having at least first and second seal portions (58, 64) radially spaced from each other, and a second seal member (44) including first and second seal surfaces (56, 62) located in facing relationship to the first and second seal portions (58, 64), respectively. The first seal member (40) is formed of a honeycomb structure, and the first seal portion (58) of the first seal member (40) is a thin fin-like structure having a width in the axial direction of the turbine engine (10) that is less than the width of the second seal portion (64) in the axial direction.
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