Aircraft rotor blade and relative forming method
An aircraft rotor blade having a root portion having a through seat and designed for connection to the rotor; and a main portion extending from the root portion. The blade is produced by polymerizing an assembly having a main structure of composite material, and a composite material covering defining the outer surface of the blade. At the root portion, the main structure has a contoured block; and a lamina member extending about at least part of the block, and having a first part adhering to a first peripheral portion of the block, and a second part spaced apart from and facing a second peripheral portion of the block to form the seat; the lamina member having a pre-preg of continuous unidirectional fibers.
1. An aircraft rotor blade ( 1 ) comprising;
a root portion ( 2 ) having a through seat ( 3 ) and designed for connection to the rotor; and
a main portion ( 4 ) extending from said root portion ( 2 );
said blade ( 1 ) being produced by polymerizing an assembly comprising a main structure ( 5 ) of composite material, and a composite material covering ( 6 ) defining the outer surface ( 7 ) of the blade ( 1 );
wherein, at said root portion ( 2 ), said main structure ( 5 ) comprises:
a contoured block ( 8 ); and
a lamina member ( 16 ) extending about at least part of said block ( 8 ), and having a first part ( 17 ) adhering to a first peripheral portion ( 12 ) of said block ( 8 ), and a second part ( 18 ) spaced apart from and facing a second peripheral portion ( 13 ) of the block ( 8 ) to form said seat ( 3 );
said lamina member ( 16 ) comprising a pre-preg of continuous unidirectional fibres; and
wherein said lamina member ( 16 ) has an annular shape.
2. A blade as claimed in claim 1 , wherein said block ( 8 ) is made of pre-preg layers superimposed with an interposition of adhesive and polymerized.
3. A blade as claimed in claim 2 , wherein said pre-preg layers of said block ( 8 ) are continuous-fibre types.
4. A blade as claimed in claim 2 , wherein said first part ( 17 ) of said lamina member ( 16 ) is fixed by adhesive to said first peripheral portion ( 12 ) of said block ( 8 ).
5. A blade as claimed in claim 1 , wherein said main structure ( 5 ) comprises a first and second hoop ( 35 , 36 ) made of composite material and applied to opposite sides of said block ( 8 ) and said lamina member ( 16 ).
6. A blade as claimed in claim 5 , wherein said first and second hoop ( 35 , 36 ) comprise pre-pregs of continuous fibres.
7. A blade as claimed in claim 6 , wherein said fibres of said first and second hoop ( 35 , 36 ) are fibres comprising carbon, or graphite fibres.
8. A blade as claimed in claim 5 , wherein said lamina member ( 16 ) is sandwiched between said first and second hoop ( 35 , 36 ).
9. A blade as claimed in claim 5 , wherein said first and second hoop ( 35 , 36 ) each have a through opening ( 39 ) with an edge aligned with said lamina member ( 16 ) to define said seat ( 3 ).
10. A blade as claimed in claim 1 , wherein said main structure ( 5 ) comprises a longitudinal member ( 32 ), one end ( 33 ) of which is fixed, with the interposition of short-fibre composite material ( 34 ), to said first part ( 17 ) of said lamina member ( 16 ), on the opposite side to said block ( 8 ).
11. A blade as claimed in claim 1 , wherein said fibres of said block ( 8 ) and/or said lamina member ( 16 ) are fibres comprising carbon, or graphite fibres.
12. A method of forming an aircraft rotor blade ( 1 ); said blade ( 1 ) comprising a root portion ( 2 ) having a through seat ( 3 ) and designed for connection to the rotor, and a main portion ( 4 ) extending from said root portion ( 2 ); said method comprising a step of polymerizing an assembly comprising a main structure ( 5 ) of composite material, and a composite material covering ( 6 ) defining the outer surface ( 7 ) of the blade ( 1 );
wherein, at said root portion ( 2 ), said main structure ( 5 ) is formed by:
forming a contoured block ( 8 );
enclosing at least part of said block ( 8 ) in a lamina member ( 16 ), so that a first part ( 17 ) of said lamina member ( 16 ) adheres to a first peripheral portion ( 12 ) of said block ( 8 ), and a second part ( 18 ) of the lamina member ( 16 ) is spaced apart from and faces a second peripheral portion ( 13 ) of said block ( 8 ) to form said seat ( 3 );
said lamina member comprising a pre-preg of continuous unidirectional fibres;
wherein said lamina member ( 16 ) is annular in shape and is wrapped about the whole of said block ( 8 ).
13. A blade as claimed in claim 1 , wherein said lamina member is defined by a first continuous curved end and an opposing second continuous curved end, said first continuous curved end being adhered to the first peripheral portion of the block and the second continuous curved end partially defining the seat.
14. A method as claimed in claim 12 , wherein said block ( 8 ) is produced by forming successive pre-preg layers superimposed with an interposition of adhesive, and by polymerizing the whole.
15. A method as claimed in claim 14 , wherein said pre-preg layers of said block ( 8 ) are continuous-fibre types.
16. A method as claimed in claim 14 , wherein said first part ( 17 ) of said lamina member ( 16 ) is fixed by adhesive to said first peripheral portion ( 12 ) of said block ( 8 ).
17. A method as claimed in claim 12 , wherein the whole formed by said block ( 8 ) and said lamina member ( 16 ) is polymerized.
18. A method as claimed in claim 12 , wherein forming said main structure ( 5 ) comprises the further step of applying a first and second hoop ( 35 , 36 ) of composite material to opposite sides of said block ( 8 ) and said lamina member ( 16 ).
19. A method as claimed in claim 18 , wherein said first and second hoop ( 35 , 36 ) are made of pre-pregs of continuous fibres.
20. A method as claimed in claim 19 , wherein said fibres of said first and second hoop ( 35 , 36 ) are fibres comprising carbon, or graphite fibres.
21. A method as claimed in claim 18 , wherein said lamina member ( 16 ) is sandwiched between said first and second hoop ( 35 , 36 ).
22. A method as claimed in claim 12 , wherein forming said main structure ( 5 ) comprises the further step of fixing one end ( 33 ) of a longitudinal member ( 32 ), with the interposition of short-fibre composite material ( 34 ), to said first part ( 17 ) of said lamina member ( 16 ), on the opposite side to said block ( 8 ).
23. A method as claimed in claim 12 , wherein said fibres of said block ( 8 ) and/or said lamina member ( 16 ) are fibres comprising carbon, or graphite fibres.
24. A method as claimed in claim 12 , wherein said lamina member is defined by a first continuous curved end and an opposing second continuous curved end, said first continuous curved end being adhered to the first peripheral portion of the block and the second continuous curved end partially defining the seat.