Patent ID: 7950900

Claim:
A stage for a gas turbine engine comprising: a plurality of circumferentially spaced apart radially extending aerofoils, and a plurality of annulus fillers that bridge the spaces between adjacent aerofoils to define an inner wall of a flow annulus through the stage, each annulus filler having opposite side faces which are spaced circumferentially from the adjacent aerofoils and which correspond in profile therewith, and resilient seal strips each including a stiffener mounted adjacent the opposite side faces of the annulus fillers, wherein: the stiffener has a three-dimensional curvature, each annulus filler bridges a space between a suction surface of one aerofoil and a pressure surface of an adjacent aerofoil, and the seal strip adjacent the suction surface is stiffer than the seal strip adjacent the pressure surface, or the seal strip adjacent the pressure surface is stiffer than the seal strip adjacent the suction surface.