Patent ID: 11873721
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 8:
9. A gas turbine engine comprising:
a section including an array of blades rotatable about a longitudinal axis, an array of vanes adjacent to the array of blades, and an array of blade outer air seals arranged circumferentially about the array of blades relative to the longitudinal axis;
a seal assembly dimensioned to span between the array of vanes and the array of blade outer air seals, the seal assembly comprising:
a first side plate, a second side plate and a backing plate that extend circumferentially about the longitudinal axis;
a first brush seal between the first side plate and the backing plate;
a second brush seal between the second side plate and the backing plate;
wherein the first and second brush seals are spaced apart from each other by the backing plate;
wherein the first brush seal is dimensioned to establish a first sealing relationship with the array of vanes, the second brush seal is dimensioned to establish a second sealing relationship with the array of blade outer air seals;
wherein each of the vanes includes an airfoil section extending from a platform section that bounds a gas path, the platform section is arranged to establish the first sealing relationship with the first brush seal, and the platform section comprises a ceramic material; and
wherein each of the vanes includes a metallic spar member secured to a fairing, the fairing comprises a ceramic matrix composite material that establishes the airfoil section and the platform section, and the seal assembly is trapped between one or more of the spar members and one or more of the blade outer air seals.