An aerofoil structure and a method of manufacturing an aerofoil structure for a gas turbine engine

摘要

The present disclosure relates to a method of manufacturing an aerofoil structure for a gas turbine engine, wherein the aerofoil structure comprises a root (202) configured to be received in a rotor disc (240) of the gas turbine engine, wherein the method comprises: providing a pre-formed insert (210a); adding the insert into a mould (220) for forming the aerofoil structure; adding a composite constituent (230) into the mould; and heating the composite constituent (230) in the mould (220) to bond the insert (210a, 210b) to the composite constituent, the insert being provided at a flank of the aerofoil structure root that faces a shoulder of the rotor disc; wherein the melting temperature of the insert (210a) is higher than the melting temperature of the resin. An aerofoil structure (200) for a gas turbine engine (10) comprises a root (202) configured to be received in a rotor disc (240) of the gas turbine engine. The aerofoil structure is formed from a composite constituent (230) and an insert (210a) moulded together, the insert being provided at a flank of the aerofoil structure root that faces a shoulder of the rotor disc.