Patent ID: 8734089

Claim:
A vane assembly for a gas turbine engine, comprising: an outer band; an inner band, wherein said inner band is subdivided into a plurality of circumferential segments; a plurality of airfoils spaced apart circumferentially and extending between said outer band and said inner band, wherein each airfoil has a tip end and a root end; and wherein each airfoil is coupled to said outer band at said tip end and coupled to a respective segment of said inner band at said root end; and a damper seal, including: a friction damper portion extending along said inner band in a circumferential direction, wherein said friction damper portion is in contact with at least two circumferential segments of said plurality of circumferential segments and is structured to provide friction damping of said at least two circumferential segments based on said contact; and an integral air seal portion extending from said friction damper portion and having a compressible end face seal structured to extend outward of and away from said at least two circumferential segments in an axial direction substantially perpendicular to the circumferential direction toward an engine component that is spaced apart from said vane assembly in the axial direction, said air seal portion being structured as a face seal to seal against an axial face of the engine component that is spaced apart from said vane assembly in the axial direction.