Composite structure and related method to obtain it
A method of making a composite structure ( 1 ) that comprises a curved body ( 5 ) and an integral rim ( 3 ) extending from an end of the curved body. The method comprises the steps of: forming a diaphragm pack ( 19 ) comprising a flat stack ( 13 ) of composite plies between two diaphragms ( 15 A, 15 B), wherein each ply (L 1 , L 2 , L 3 ) of the flat stack ( 13 ) is made up of a plurality of composite tiles ( 9 ). Each tile ( 9 ) includes at least a first portion ( 9 A) and a second portion ( 9 B) that have side edges of the first portion ( 9 A) configured to abut against side edges of adjacent tiles and side edges of the second portion ( 9 B) configured to overlap side edges of adjacent tiles. Air is evacuated from within the diaphragm pack ( 19 ) either before or after placing the diaphragm pack ( 19 ) within a double diaphragm forming apparatus comprising a hollow forming tool ( 23 ), wherein the first portion ( 9 A) of the composite tiles ( 9 ) is supported on an upper surface ( 23 A) of the tool ( 23 ). Heat ( 25 ) is applied to the diaphragm pack ( 19 ); when the stack reaches the forming temperature a vacuum (Pv) is applied between the lower diaphragm ( 15 B) and the hollow forming tool ( 23 ) such the second portion ( 9 B) of the composite tiles ( 9 ) are drawn downwards into contact with the internal wall ( 23 B) of the forming tool ( 23 ) to move the edges of the second portion ( 9 B) of adjacent tiles to abut against side edges of adjacent tiles ( 9 ). The first portion ( 9 A) of each tile ( 9 ) forms part of the rim ( 3 ) and the second portion ( 9 B) of each tile forms art of the curved body ( 5 ).
1. A method of making a composite structure comprising a curved body and an integral rim extending from an end of the curved body, the method comprises the steps:
forming a diaphragm pack comprising a flat stack of composite plies between two diaphragms wherein each ply of the flat stack is made up of a plurality of composite tiles, each tile having at least a first portion and a second portion, with side edges of the first portion being configured to abut against side edges of adjacent tiles and side edges of the second portion being configured to overlap side edges of adjacent tiles;
placing the diaphragm pack in a double diaphragm forming apparatus comprising a hollow forming tool including evacuating air from within the diaphragm pack, wherein the first portion of the composite tiles is supported on an upper surface of the tool;
applying heat to the diaphragm pack; and
applying a vacuum between the lower diaphragm and the hollow forming tool such that: an unsupported region corresponding to the second portion of the composite tiles is drawn into contact with an internal wall of the forming tool; the edges of the second portion of adjacent tiles move to abut against side edges of adjacent tiles; the first portion of each tile forms part of the rim; and the second portion of each tile forms part of the curved body.
2. A method according to claim 1 , wherein the side edges of the second portion of each tile is configured with substantially parallel edges.
3. A method according to claim 1 , wherein each of the tiles laid is of substantially the same shape and size.
4. A method according to claim 1 , wherein the side edges of the first portion of each tile are substantially radial.
5. A method according to claim 4 , wherein the tiles are laid in a circular pattern.
6. A method according to claim 4 , wherein the edges of adjacent tiles in each ply are offset from the edges of adjacent tiles in adjacent plies.
7. A method according to claim 1 , wherein each tile comprises one ply of composite material.
8. A method according to claim 7 , wherein the tiles include unidirectional pre-impregnated composite material.
9. A method according to claim 7 , wherein the tiles include woven pre-impregnated material.
10. A method according to claim 7 , wherein the tiles include dry fabric.
11. A method according to claim 10 , wherein the dry fabric is woven fabric or a unidirectional stitched non-crimped fabric including binder or tackifier.
12. A method according to claim 10 , wherein each ply of dry fabric when laid to form a composite stack is interleaved with resin film.
13. A method according to claims 7 , wherein the composite material includes carbon fibres and/or aramid fibres and/or glass fibres.
14. A composite structure comprising a hollow duct and integral rim on an end thereof, wherein the duct and rim are formed from a plurality of composite tiles that include at least a first portion and a second portion, where the first portion of each tile forms part of the rim and the second portion of each tile forms part of the hollow duct and wherein edges of adjacent tiles abut one another, the composite structure being made by a method comprising the steps of:
forming a diaphragm pack comprising a flat stack of composite plies between two diaphragms wherein each ply of the flat stack is made up of a plurality of composite tiles, each tile having at least a first portion and a second portion, with side edges of the first portion being configured to abut against side edges of adjacent tiles and side edges of the second portion being configured to overlap side edges of adjacent tiles;
placing the diaphragm pack in a double diaphragm forming apparatus comprising a hollow forming tool including evacuating air from within the diaphragm pack, wherein the first portion of the composite tiles is supported on an upper surface of the tool;
applying heat to the diaphragm pack; and
applying a vacuum between the lower diaphragm and the hollow forming tool such that: an unsupported region corresponding to the second portion of the composite tiles is drawn into contact with an internal wall of the forming tool; the edges of the second portion of adjacent tiles move to abut against side edges of adjacent tiles; the first portion of each tile forms part of the rim; and the second portion of each tile forms part of the hollow duct.
15. A composite structure according to claim 14 , wherein each tile is substantially mushroom-shaped, where the first portion is the head of the mushroom and the second portion forms the stalk of the mushroom shape.
16. A composite structure according to claim 14 , wherein the duct and rim have a circular cross-section or oval cross section.
17. A composite structure according to claim 14 , wherein the duct is an engine duct for an aircraft.
18. An aircraft engine comprising a composite structure or duct as claimed in claim 1 .
19. A composite structure comprising a hollow duct and integral rim on an end thereof, wherein the duct and rim are formed from a plurality of composite tiles that include at least a first portion and a second portion, where the first portion of each tile forms part of the rim and the second portion of each tile forms part of the hollow duct and wherein edges of adjacent tiles abut one another.
20. A duct for an engine for an aircraft comprising a hollow duct and integral rim on an end thereof, wherein the duct and rim are formed from a plurality of composite tiles that include at least a first portion and a second portion, where the first portion of each tile forms part of the rim and the second portion of each tile forms part of the hollow duct and wherein edges of adjacent tiles abut one another.
21. A duct as claimed in claim 20 manufactured according to a method comprising the steps of:
forming a diaphragm pack comprising a flat stack of composite plies between two diaphragms wherein each ply of the flat stack is made up of a plurality of composite tiles, each tile having at least a first portion and a second portion, with side edges of the first portion being configured to abut against side edges of adjacent tiles and side edges of the second portion being configured to overlap side edges of adjacent tiles;
placing the diaphragm pack in a double diaphragm forming apparatus comprising a hollow forming tool including evacuating air from within the diaphragm pack, wherein the first portion of the composite tiles is supported on an upper surface of the tool;
applying heat to the diaphragm pack; and
applying a vacuum between the lower diaphragm and the hollow forming tool such that: an unsupported region corresponding to the second portion of the composite tiles is drawn into contact with an internal wall of the forming tool; the edges of the second portion of adjacent tiles move to abut against side edges of adjacent tiles; the first portion of each tile forms part of the rim; and the second portion of each tile forms part of the curved body.