Rolls-royce Corporation

Benjamin A Leishman

Crispin David Bolgar

Czeslaw Paluszkiewicz

Gary P Austin

Nicholas A Cumpsty

A seal arrangementpresents a barrier in the form of a combined seal and anti-fret lineracross a shroud ring cavityin order to inhibit air leakage in the platform gap between platforms. It will be understood that these gaps are provided for thermal expansion and vibration of vane assemblies but create a leakage path between passageand cavitywhich can increase aerodynamic losses and therefore reduce engine compressor efficiency. By provision of a combined seal and anti-fret linersuch air losses are reduced whilst combining the function of an air leakage seal and an anti-fret liner to prevent abrasive degradation of the mountingsand platform sectionensures that there is a reduced component count as well as cost, weight and assembly time.

Seal arrangement

A vane () for a rotor arrangement () of a gas turbine engine () comprises an aerofoil member () and a mounting member () from which the aerofoil member () extends. The mounting member () includes a sloped region () to guide gas flowing over the mounting member () into a bleed arrangement (). A vane assembly () and a rotor arrangement () comprising such vanes () are also disclosed.

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Derby, United Kingdom

Benjamin A Leishman