Rolls-royce Corporation

Rodney D Conrad

Eric William Engebretsen

Matthew J Kappes

Patrick E Bailey

Samuel J Lacombe

A fan assembly for use in a gas turbine engine of an aircraft includes a fan disk having a number of fan blades and a windage shield coupled to the fan disk to move therewith. The fan assembly supplies air for use in the engine. The windage shield rotates with the fan disk during operation of the gas turbine engine and directs air supplied by the fan blade.

Attachment of piloting feature

Within gas turbine enginesit is necessary to provide fixed vanes which comprise an aerofoil in the gas flow through the gas turbine engine. These vanes are subject to significant stressing. Therefore it is generally necessary to secure the vane at one endthrough an appropriate bond such as brazing while at another end a friction damping response is achieved. By providing an anti-bonding layer it is possible to prevent a mechanical bond being formed at the friction damping end. Furthermore, a tight fit can be emphasized by residual bonding material remaining after an attempted bonding process upon the anti-bonding layer.

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Zionsville, IN, United States of America

Rodney D Conrad