| 摘要 |
<p>A gas turbine engine (10) includes an axial brush seal (84) extending substantially axially between a vane support (48) and a plurality of blade outer air seals (62) to minimize leakage of cooler air into an air path (22) of working fluid. The axial seal (84) includes a first and a second rings (86, 88) extending axially with a plurality of bristles (92) sandwiched therebetween. Each of the plurality of bristles (92) includes a fore bristle end (98) and an aft bristle end (100) that come into contact with a vane support sealing surface (53) and a blade outer air seal sealing surface (76), respectively, with the bristles (92) being compressed against the sealing surfaces. The axial seal (84) is movable with respect to the vane support (48) and the blade outer air seals (62) to compensate for expansion and contraction of the vane support (48) and the plurality of blade outer air seals (62) as well as for lack of uniformity in the plurality of blade outer air seals. <IMAGE></p> |
