Tip treatment bars for gas turbine engines
AssigneeROLLS-ROYCE plc
InventorsAndrew Motherwell, Brynley Clark
Life of this patent
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Abstract
A tip treatment bar (16) for a gas turbine engine has a damping coating (24) applied to one or more sides. The coating (24) may be a hard ceramic, for example Magnesia Alumina Spinel, and this may be plasma sprayed directly on to the bar (16) or applied to a substrate (26) which may then be applied to the bar (16).
Claims19
A tip treatment bar for a gas turbine engine, the bar having a coating applied over at least part of at least one face of the bar.
A tip treatment ring comprising oppositely disposed end supports and a plurality of tip treatment bars disposed in an annular array and supported at their ends by end supports, each tip treatment bar having a coating applied over at least part of at least one face of the bar.
Dependencies are inferred from the claim text.