Axial brush seal for gas turbine engines

摘要

A gas turbine engine includes an axial brush seal extending substantially axially between a vane support and a plurality of blade outer air seals to minimize leakage of cooler air into an air path of working fluid. The axial seal includes a first and a second rings extending axially with a plurality of bristles sandwiched therebetween. Each of the plurality of bristles includes a fore bristle end and an aft bristle end that come into contact with a vane support sealing surface and a blade outer air seal sealing surface, respectively, with the bristles being compressed against the sealing surfaces. The axial seal is movable with respect to the vane support and the blade outer air seals to compensate for expansion and contraction of the vane support and the plurality of blade outer air seals as well as for lack of uniformity in the plurality of blade outer air seals.