GAS TURBINE ENGINE

摘要

A fan casing for fitment around an array of radially extending fan blades of a gas turbine engine. The fan casing includes an annular casing element; and an annular fan track liner positioned radially inward of the annular casing element. The fan track liner includes an abradable layer and an abrasive layer, the abrasive layer being positioned radially inward of the abradable layer and proximal, in use, to the fan blades.

主权项

1. A method of manufacturing a gas turbine engine, the method comprising:
providing a series of fan blades about a hub, arranging an annular fan casing having an annular fan track liner circumferentially around the fan blades, wherein the fan track liner comprises an abradable layer and an abrasive layer on a radially inner surface of the abradable layer; and rotating the fan blades such that the abrasive layer removes a section from a tip of one or more of the fan blades.