Method of manufacturing an annular bladed member having an integral shroud
AssigneeROLLS-ROYCE plc
InventorJames P. Angus
Life of this patent
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Abstract
A gas turbine engine disc having integral, radially extending aerofoil blades and an integral shroud interconnecting the radially outer extents of the blades is described. In the manufacture thereof continuous fibres are wound around an annular array of inserts provided in a dividable disc. The inserts define the spaces between adjacent blades on the disc. A mixture of chopped carbon fibre and an epoxy resin matrix material is then injected into the central portion of the die interior. Any part of the wound fibres which has not been impregnated by the chopped fibre/resin matrix material is subsequently impregnated by a matrix material whereupon the die is opened to release the thus produced bladed disc.
Claims9
A method of manufacturing an integral bladed member comprising:
- winding a substantially continuous fibre around radially outer extents of an annular array of inserts provided on a dividable die defining the form of said integral bladed member, said inserts being so configured as to define spaces between adjacent blades on said member, so that said fibre constitutes the reinforcing fibre of an integral shroud interconnecting the radially outer extends of said blades,
- closing said die and injecting a mixture of short fibres in a matrix material into the central portion of said die interior so that said mixture fills said central portion and flows between said inserts so that the majority of said short fibres between said inserts are generally radially aligned to partially inpregnate said wound fibre,
- injecting a matrix material into said wound fibre so as to impregnate any part thereof which has not been impregnated by said mixture of a matrix material and short fibres so as to define said integral shroud, and
- subsequently opening said die to release the thus produced integral bladed member.
A method of manufacturing an integral bladed member comprising:
- locating a ring-shaped shroud member comprising substantially continuous circumferentially extending reinforcing fibre enclosed in a matrix material around radially outer extents of an annular array of inserts provided in a dividable die defining the form of an integral bladed member, said inserts being so configured as to define spaces between adjacent aerofoil blades ,
- closing said die, and
- injecting a mixture of short fibres dispersed in a matrix material into the central portion of said die interior so that said mixture fills said central portion and flows between said inserts to reach and abut said ring shaped shroud member so that inter-linking between said short fibres and said reinforcing fibre of said ring-shaped shroud member occurs and said short fibres, at least between said inserts, are generally radially aligned.
Dependencies are inferred from the claim text.