Composite structure formed by CMC-on-insulation process
View Patent ↗A method of manufacturing a composite structure uses a layer of an insulating material ( 22 ) as a mold for forming a substrate of a ceramic matrix composite (CMC) material ( 24 ). The insulating material may be formed in the shape of a cylinder ( 10 ) with the CMC material wound on an outer surface ( 14 ) of the cylinder to form a gas turbine combustor liner ( 20 ). Alternatively, the insulating material may be formed in the shape of an airfoil section ( 32 ) with the CMC material formed on an inside surface ( 36 ) of the insulating material. The airfoil section may be formed of a plurality of halves ( 42, 44 ) to facilitate the lay-up of the CMC material onto an easily accessible surface, with the halves then joined together to form the complete composite airfoil. In another embodiment, a box structure ( 102 ) defining a hot gas flow passage ( 98 ) is manufactured by forming insulating material in the shape of opposed airfoil halves ( 104 ) joined at respective opposed ends by platform members ( 109 ). A layer of CMC material ( 107 ) is then formed on an outside surface of the insulating material. A number of such composite material box structures are then joined together to form a vane ring ( 100 ) for a gas turbine engine.
1. A method of manufacturing a composite structure, the method comprising;
forming a layer of porous thermally insulating material;
using the layer of porous thermally insulating material as a mold for receiving ceramic fibers and a matrix material in a wet state to form a layer of wet ceramic matrix composite material, and further comprising;
allowing the matrix material of the layer of wet ceramic matrix composite material to penetrate pores of the porous layer of thermally insulating material to form a continuous matrix across an interface between the respective layers; and
curing the matrix material to form an integral composite structure.
2. The method of claim 1 , further comprising only partially curing the layer of thermally insulating material prior to the step of using the layer of thermally insulating material as a mold to form the layer of ceramic matrix composite material.
3. The method of claim 1 , further comprising curing the layer of thermally insulating material and the layer of ceramic matrix composite material simultaneously to form a bond there between.
4. The method of claim 1 , further comprising:
partially curing the layer of thermally insulating material prior to the step of using the layer of thermally insulating material as a mold to form the layer of ceramic matrix composite material; and
curing the layer of thermally insulating material and the layer of ceramic matrix composite material to a fully stabilized state simultaneously to form a bond there between.
5. The method of claim 1 , further comprising:
forming the layer of thermally insulating material in the shape of a cylinder; and
forming the layer of ceramic matrix composite material on an outside surface of the cylinder.
6. The method of claim 5 , further comprising only partially curing the layer of thermally insulating material prior to the step of forming the layer of ceramic matrix composite material.
7. The method of claim 1 , further comprising:
forming the layer of porous thermally insulating material in the shape of a cylinder; and
wet filament winding reinforcing fibers of the layer of ceramic matrix composite material on an outside surface of the cylinder.
8. The method of claim 1 , further comprising:
forming the layer of thermally insulating material to have an outside surface defining an airfoil shape and to have an inside surface; and
forming the layer of ceramic matrix composite material on the inside surface.
9. The method of claim 1 , further comprising:
forming the layer of thermally insulating material as a plurality of split airfoil shell portions, each shell portion comprising an accessible inside surface;
forming a respective layer of wet ceramic matrix composite material on the accessible inside surface of each of the split airfoil shell portions; and
joining the split airfoil shell portions together to define a composite airfoil having the thermally insulating material as its outside layer and the ceramic matrix composite material as its inside layer.
10. The method of claim 9 , further comprising curing the layer of thermally insulating material of each respective airfoil shell portion together with its respective layer of ceramic matrix composite material to form a bond there between.
11. The method of claim 9 , further comprising:
forming mating locking members in the respective layers of ceramic matrix composite material; and
joining the respective mating locking members together during the step of joining the airfoil shell portions together.
12. The method of claim 11 , further comprising:
forming a generally U-shaped locking member of ceramic matrix composite material; and
joining the respective mating locking members together with the generally U-shaped locking member.
13. The method of claim 9 , wherein the step of joining the shell portions together further comprises:
attaching each shell portion and its respective layer of ceramic matrix composite material to a respective metal core member; and
joining the respective metal core members together.
14. The method of claim 1 , further comprising:
forming the layer of thermally insulating material to the shape of a box structure comprising a pair of opposed split airfoil portions joined at respective ends by an opposed pair of platform members and defining a hot combustion gas passage there between; and
forming the layer of ceramic matrix composite material on an outside surface of the box structure.
15. A method of manufacturing a composite structure, the method comprising:
forming a layer of porous ceramic thermally insulating material;
applying a layer of wet ceramic matrix composite material to a surface of the layer of porous ceramic thermally insulating material so that the wet matrix material penetrates the pores of the insulating material to form a continuous matrix across an interface between the respective layers; and
curing the matrix material to form to form an integral composite structure;
wherein an extent of matrix material penetration into the pores of the insulating material is controlled with a surface treatment of the insulating material.