CMC turbine engine component

1. A component of a gas turbine engine, the component being formed from a continuous fibre reinforced ceramic matrix composite (CMC);

wherein the component has a sealing portion which, in use, makes sealing contact with an adjacent component of the engine, the sealing portion comprising a recess formed in the CMC and filled with a finer grade ceramic relative to the surrounding CMC, a metal or an intermetallic wherein sealing contact between the component and the adjacent component is effected by a flexible sealing member which conforms to a surface of the sealing portion.

2. The component according to claim 1 , wherein the finer grade ceramic is a monolithic ceramic.

3. The component according to claim 1 , wherein the finer grade ceramic has substantially the same composition as the ceramic matrix of the CMC.

4. The component according to claim 1 which is a seal segment for a shroud ring of a rotor of the engine, the seal segment being positioned, in use, radially adjacent the rotor.

5. A seal segment according to claim 4 , wherein the recess is a channel formed in a face of the segment.

6. The seal segment according to claim 5 , wherein the channel extends around the periphery of the face.

7. The seal segment according to claim 5 , wherein the face is a back face distal from the rotor.

8. The seal segment according to claim 4 , wherein the adjacent component is a casing of the rotor.

9. The component according to claim 1 which is a nozzle guide vane.

10. A nozzle guide vane according to claim 9 , wherein the vane has an aerofoil body which extends between inner and outer endwall platforms, the recess being formed in one of the platforms.

11. A gas turbine engine fitted with the component of claim 1 .