| 摘要 |
An attrition liner machining tool (30), configured to machine the surface of an attrition liner (26) provided radially outward of a set of a plurality of fan blades in a gas turbine engine (10). The tool (30) comprises at least one rotating machine tool (31,32) having a connector (34) at a first end and a cutter (35) at a second end. The connector (34) is configured to rigidly connect to a rotating fan blade mount (33) of the gas turbine engine (10) that, in use of the gas turbine engine, supports the fan blades. The cutter (35) is configured to machine the attrition liner (26). The at least one rotating machine tool (31,32) is configured such that, when it is connected to said rotating fan blade mount (33) of a gas turbine engine (10), the cutter (35) is passed across the surface of the attrition liner (26) when said rotating fan blade mount (33) is rotated. |
