Seal apparatus
OwnerAlec G. Dodd, Colin J. Burfordinventors
Life of this patent
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Abstract
A seal for a gas turbine engine comprises an internal abradable lining and two interconnecting flanges. The flanges form a U-shaped channel therebetween for the insertion of radially inwardly directed features on the inner ends of a plurality of stator vanes. One or both flanges support the abradable lining via a land.
Claims8
Support means for a seal for a gas turbine engine, one component of which comprises an annular land having an internal abradable lining and at least two radially, separately formed, outwardly extending members defining first and second flanges, at least one of said members being adapted to support said internal abradable lining, the flanges being adapted and shaped to cooperate with one another so as to form a channel therebetween and said channel being shaped so as to receive one or more connecting members extending radially inwardly from the inner ends of a plurality of stator vanes.
Dependencies are inferred from the claim text.