Rolls-royce Corporation

Neil A Shipley

Mark J Hicklin

Daniel J Swan

A rotatable arrangement for a gas turbine engine comprises a plurality of blades having an aerofoil profile with a suction side, a pressure side, a leading edge and a trailing edge. A plurality of annulus fillers are provided between adjacent blades. A pressure side seal extends between a blade and an annulus filler on the pressure side of the blade, and a suction side seal extends between the blade and an annulus filler on the suction side of the blade. The suction side seal comprises a blocking member provided at an end of the suction side seal proximal to the trailing edge of the blade, the blocking member being configured to restrict recirculation of flow along the suction side of the blade.

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Derby, United Kingdom

Neil A Shipley