技术功效语段：
[0014]This provides a stronger laminate layer in a final composite structure than conventional laminate layers that are manufactured via two or more non-spliced fibre mats prior to the infusion process. Further, it is possible to reduce the number of wrinkles in the laminate, thus decreasing mechanical weaknesses in the final composite structure even further. This is particularly achieved since the splicing joint ensures that the two mats do not move during a layup procedure, e.g. when additional fibre layers are arranged on top of the assembled fibre layers, or when the fibre reinforcement material is later vacuum bagged and infused.
[0042]Thus, it is seen that the method relates to a normal layout procedure, where advantageously continuous layers are arranged in the mould, and only layers comprising spliced fibre mats are used in order to reduce the amount of waste products.
权利要求：
1. A method of producing a single assembled longitudinally extending fibre layer for use in a later resin infusion process for manufacturing a fibre-reinforced composite structure, the method comprising the following steps: a) providing a first fibre mat comprising unidirectional reinforcement fibres oriented in a longitudinal direction of the first fibre mat between two ends, b) providing a second fibre mat comprising unidirectional reinforcement fibres oriented in a longitudinal direction of the second fibre mat between two ends, c) arranging the first fibre mat and the second fibre mat so that unidirectional fibres of one end of the first fibre mat adjoin one end of the second fibre mat in a single plane at a common boundary, and d) splicing unidirectional fibres of the first fibre mat at said one end of the first fibre mat to unidirectional fibres of the second fibre mat at said one end of the second fibre mat in order to form a splicing joint.
2. A method according to claim 1, wherein said one end of the first fibre layer and said one end of the second fibre layer are cut taperingly, and wherein said fibre layers in step c) are arranged so that the common boundary forms a tapering transition between unidirectional fibres of the first fibre mat and unidirectional fibres of the second fibre mat in the longitudinal direction of the single continuous, longitudinally extending fibre layer.
3. A method according to claim 2, wherein the tapering transition has a thickness-to-length ratio being between 1:50 and 1:5, e.g. around 1:30.
4. A method according to any of the preceding claim, wherein step d) comprises the use of an adhesive for providing said splicing.
5. A method according to claim 4, wherein the adhesive is powder based.
6. A method according to any of the preceding claims, wherein the splicing joint is heated, e.g. through ironing.
7. A method according to any of the preceding claims, wherein step d) comprises the step of stitching the first fibre mat and the second fibre mat together for providing said splicing.
8. A method according to any of the preceding claims, wherein further unidirectional fibres of the first fibre mat are pressed against unidirectional fibres of the second fibre mat in order to form a frictional connection between said unidirectional fibres.
9. A method according to any of the preceding claims, wherein step d) comprises the use of rollers for pressing the unidirectional fibres of the first mat and the second fibre mat against each other.
10. A method according to any of the preceding claims, wherein unidirectional fibres at said one ends of the first fibre mat and the second fibre mat are unstitched at a longitudinal zone at said one ends prior to step d).
11. A method according to any of the preceding claims, wherein unidirectional fibres at said one ends of the first fibre mat and the second fibre mat are aligned in the longitudinal direction via alignment means, such as a comb.
12. A method of manufacturing a wind turbine blade part, such as a blade shell part, wherein the manufacturing method includes layup of fibre layers in a mould, wherein at least one of the fibre layers are produced according to any of the methods according to claims 1-11, and wherein a resin is later supplied to said fibre layers and subsequently cured or hardened in order to form a composite structure.
13. A method of manufacturing a wind turbine blade part according to claim 12, wherein the layup involves stacking of a plurality of fibre layers, and wherein said at least one fibre layer is sandwiched between two fibre layers which do not have a splicing joint at the splicing joint of said at least one fibre layer.
14. A method of manufacturing a wind turbine blade part according to claim 12 or 13, wherein the wind turbine blade part is a load carrying structure, such as a main laminate or a spar cap.
15. An assembled longitudinally extending fibre reinforcement layer for use in a later resin infusion process for manufacturing a fibre-reinforced composite structure, the fibre reinforcement layer comprising: - a first fibre mat comprising unidirectional reinforcement fibres oriented in a longitudinal direction of the first fibre mat between two ends, - a second fibre mat comprising unidirectional reinforcement fibres oriented in a longitudinal direction of the second fibre mat between two ends, wherein - the first fibre mat and the second fibre mat are arranged so that unidirectional fibres of one end of the first fibre mat adjoin one end of the second fibre mat in a single plane at a common boundary, and wherein - the unidirectional fibres of the first fibre mat at said one end of the first fibre mat are spliced to unidirectional fibres of the second fibre mat at said one end of the second fibre mat and forming a splicing joint.