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US 7,510,369 B2Granted
Sacrificial inner shroud liners for gas turbine engines
AssigneeUnited Technologies Corporation
InventorWilliam C Lytle
Life of this patent
Estimating the term…
Abstract
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.
Claims19
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.
1 more element
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.
3 more elements
Dependencies are inferred from the claim text.