CMC TURBINE ENGINE COMPONENT

• US 20140255170A1
• Filed: 03/04/2014
• Published: 09/11/2014
• Est. Priority Date: 03/06/2013
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Hillier, Steven
• Granted Patent: US 9,476,316 B2
• Time in Patent Office: Days
• US Class Current: 415/174.2
• CPC Class Codes: F01D 11/005 Sealing means between non relatively rotating elements
• CPC Class Codes: F01D 11/08 for sealing space between rotor blade tips and stator specially-shaped blade tips therefor F01D5/20
• CPC Class Codes: F01D 11/12 using a rubstrip, e.g. erodible. deformable or resiliently-biased part
• CPC Class Codes: F01D 5/282 Selecting composite materials, e.g. blades with reinforcing filaments
• CPC Class Codes: F01D 5/284 Selection of ceramic materials
• CPC Class Codes: F01D 9/04 forming ring or sector
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F05D 2230/00 Manufacture
• CPC Class Codes: F05D 2240/11 Shroud seal segments
• CPC Class Codes: F05D 2240/80 Platforms for stationary or moving blades
• CPC Class Codes: F05D 2250/62 smooth or fine
• CPC Class Codes: F05D 2300/6033 Ceramic matrix composites [CMC]

Abstract

A component of a gas turbine engine is formed from a continuous fibre reinforced ceramic matrix composite (CMC). The component has a sealing portion which, in use, makes sealing contact with an adjacent component of the engine. The sealing portion comprises a recess formed in the CMC and filled with a finer grade ceramic relative to the surrounding CMC, a metal or an intermetallic.

Claims

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 (35) formed in the CMC and filled with a finer grade ceramic (36) 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 (37) which conforms to the surface of the sealing portion.

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

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

4. A component according to claim 1 which is a seal segment (30) 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. A seal segment according to claim 5, wherein the channel extends around the periphery of the face.

7. A seal segment according to claim 5, wherein the face is a back face (34) distal from the rotor.

8. A seal segment according to claim 4, wherein the adjacent component is a casing (38) of rotor.

9. A 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.