| 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.
|
