Sacrificial inner shroud liners for gas turbine engines
A split shroud system for a gas turbine engine having a pair of annular-shaped shrouds that each have an inner pocket; to form a pair of inner pockets. Each of the pair of pockets having liner parts that form a circle. Liner parts of one of the pair of pockets facing liner parts of the other of the pair of pockets to form liner part pairs. One of each of said of pair of liner parts has a mutual abutting surface that forms a plurality of slots for accepting a plurality of vane inner trunnions.
1. A split shroud system for a gas turbine engine comprising:
a pair of annular-shaped shrouds that each contain an inner pocket to form a pair of facing pockets; and
a pair of liners, one of said pair of liners, contained within one of said pair of pockets and the other of said pair of liners contained in the other of said pair of pockets,
wherein each of said pair of liners has a mutually contacting surface that forms a plurality of slots.
2. The split engine shroud system of claim 1 , wherein each of said pair of liners comprises a plurality of segments and each of said pair of shrouds comprises a plurality of segments, wherein each segment of each of said pair of liners forms a plurality of slots at the mutually contacting surface.
3. The split engine shroud system of claim 1 , wherein each of said plurality of slots has a circular cross-section.
4. The split engine shroud system of claim 2 , wherein each of said plurality of slots is dimensioned to receive an inner diameter trunnion of a turbofan vane.
5. The split engine shroud system of claim 1 , wherein said each of said pair of liners is made from a graphitic carbon material.
6. The split engine shroud system of claim 1 , wherein said pair of annular-shaped shrouds are made from a hardened steel material.
7. The split engine shroud system of claim 1 , wherein each of said pair of annular-shaped shrouds is made from a titanium material.
8. The split engine shroud system of claim 1 , wherein each of said pair of liners is press-fit into one of the pockets of the shroud.
9. The split engine shroud system of claim 2 , wherein each of said plurality of liner parts can be removed and re-inserted into the other of said pair of pockets.
10. The split engine shroud system of claim 1 , wherein each of said liners is annular-shaped.
11. A split shroud system for a gas turbine engine comprising:
a pair of annular-shaped shrouds; each of said pair of shrouds having an inner pocket to form a pair of inner pockets; and
each of said pair of pockets having liner parts that form a circle; said liner parts of one of said pair of pockets facing liner parts the other of said pair of pockets to form liner pairs, one of each of said of pair of liner parts has a mutual abutting surface that forms a plurality of slots to receive vane trunnions,
wherein said liner parts and said plurality of slots accept wear caused by said trunnions during operational flight conditions of the engine.
12. The split engine shroud system of claim 11 , wherein each of said plurality of slots has a circular cross-section.
13. The split engine shroud system of claim 11 , wherein each of said plurality of slots is dimensioned to receive an inner diameter trunnion of a turbofan vane.
14. The split engine shroud system of claim 11 , wherein said each of said pair of liners is made from a graphic carbon material.
15. The split engine shroud system of claim 11 , wherein said pair of annular-shaped shrouds are made from a hardened steel material.
16. The split engine shroud system of claim 11 , wherein said pair of annular-shaped shrouds are made from a titanium material.
17. The split engine shroud system of claim 11 , wherein each of said pair of liner parts is press-fit into one of the pockets of the shroud.
18. The split engine shroud system of claim 11 , wherein each of said plurality of liner parts can be removed and re-inserted into the other of said pair of pockets.
19. The split engine shroud system of claim 11 , wherein each of said inner pockets is annular-shaped.