| 摘要 |
A stage for a gas turbine engine, having a plurality of circumferentially spaced apart radially extending aerofoils, includes a plurality of annulus fillers (12) to bridge the spaces between adjacent aerofoils to define an inner wall of a flow annulus through the stage. Each annulus filler (12) has opposing side faces (22,24) which are spaced circumferentially from the adjacent blades and which correspond in profile therewith, and resilient seal strips (26,28) each including a stiffener (36) are mounted adjacent the opposing side faces of the annulus fillers to seal the gaps between the annulus fillers (12) and the aerofoils. The stiffeners have three-dimensional curvature. |
