Cooling ends of a gas turbine engine liner

摘要

A gas turbine engine has a turbine liner structure comprising a plurality of segments 22 disposed end-to end to form a ring surrounding a turbine (2, fig 1). A gap 42 defined between end faces 28 of each two adjacent liner segments 22 is inclined to a plane 30 which passes trough the gap 42 and contains the engine axis. The swirl component 36 of gas flow through the turbine draws air 48 through the gap 42 past a sealing strip 32. This air flow 48 may be enhanced by a cooling air feed 44. The air flow 48 enhances venting of the gap 42 and protects the upstream edge of each liner segment 22 from direct impingement of the hot gas flow, so reducing damage due to overheating of an alloy substrate 24 of each liner segment 22 and of any ceramic coating 26 provided on the substrate 24.