Method for solving blade defects

Abstract

The invention discloses a method for solving blade defects. The method comprises the steps of blade pneumatic design, structure laying layer design, shell laying layer laying and vacuum auxiliary material laying. In the step of blade pneumatic design, the blunt trailing edge angle of the blade is designed to be of an obtuse arc structure, and a blade mold is prepared and formed; in the step of structural laying layer design, a connecting glass fiber laying layer is arranged between a blunt trailing edge core material and a non-blunt trailing edge area core material of the blade; in the step of laying the shell laying layers, the first glass fiber laying layer is laid on the inner surface of the blade mold and bonded to the blunt trailing edge corner of the blade mold, the first one-way breathable layer is laid in the non-blunt trailing edge corner area of the blade mold, and the structural laying layer and the auxiliary laying layer are laid on the first glass fiber laying layer till the whole laying layer is laid; in the step of laying the vacuum auxiliary material, the laying area of the vacuum auxiliary material is larger than that of the whole laying layer. The problem that the blunt trailing edge of a large blade is rich in resin is solved.

Description

Technical Field

[0001] The present application relates to the technical field of blade manufacturing, and more specifically, to a method for solving blade defects. Background Art

[0002] The blade shell pouring process in the production process of wind turbine blades is one of the most critical processes. Its biggest feature is that the pouring process is irreversible and cannot be stopped, and pouring defects directly affect the molding quality and total molding cycle of the blades.

[0003] During the infusion process of large blades, resin-rich defects usually appear at the blunt trailing edge of the blade. Defects at this location are more difficult to repair in the subsequent process and the repair cycle is longer, which directly affects the overall molding cycle of the blade.

[0004] Therefore, how to solve the resin-rich defect of the blunt trailing edge of large blades has become a technical problem that needs to be solved urgently by those skilled in the art. Summary of the invention

[0005] In view of this, an object of the present application is to provide a method for solving blade defects, so as to solve the resin-rich defect of the blunt trailing edge of a large blade.

[0006] To achieve the above objectives, this application provides the following technical solutions:

[0007] A method for resolving blade defects, comprising the steps of:

[0008] The blade is aerodynamically designed, the blunt trailing edge of the blade is designed to be an obtuse angle, and the blunt trailing edge of the blade is an arc-shaped structure, and a blade mold is prepared;

[0009] Structural ply design, providing a connecting glass fiber ply between the blunt trailing edge core material and the non-blunt trailing edge core material of the blade;

[0010] Laying the shell ply, laying the first layer of glass fiber ply on the inner surface of the blade mold, and fixing it at the blunt trailing edge corner of the blade mold by means of adhesive material, laying the first unidirectional air permeable layer at the non-blunt trailing edge corner area of ​​the blade mold, and laying the structural ply and auxiliary ply on top of the first layer of glass fiber ply until the overall ply laying is completed;

[0011] Laying the vacuum auxiliary material, laying the vacuum auxiliary material on the top of the overall paving layer, and the laying area of ​​the vacuum auxiliary material is larger than the laying area of ​​the overall paving layer.

[0012] Optionally, in the above method for solving blade defects, the following steps are further included:

[0013] Vacuuming, vacuuming the bottom of the vacuum auxiliary material through the conveying pipeline until the pressure maintenance is completed;

[0014] Injection and curing: injecting resin glue into the lower part of the vacuum auxiliary material through the conveying pipeline and curing it.

[0015] Optionally, in the above method for solving blade defects, the vacuuming step further includes compacting the laying area of ​​the vacuum auxiliary material.

[0016] Optionally, in the above method for resolving blade defects, in the steps of infusion and curing, the resin glue is cured by heating or pressurizing.

[0017] Optionally, in the above method for resolving blade defects, in the mold lamination step, a second unidirectional air-permeable layer is laid on top of the overall lamination.

[0018] Optionally, in the above method for solving blade defects, the first one-way air-permeable layer is one of a one-way air-permeable film, a continuous mat and a chopped strand mat; and / or,

[0019] The second one-way air-permeable layer is one of a one-way air-permeable film, a continuous mat and a chopped strand mat.

[0020] Optionally, in the above method for solving blade defects, in the step of structural ply design, the connecting glass fiber ply is multi-layered, and each layer of the connecting glass fiber ply is prefabricated into an integrated structure.

[0021] Optionally, in the above method for solving blade defects, in the step of aerodynamic design of the blade, the blunt trailing edge angle of the blade is not less than 120°.

[0022] Optionally, in the above method for resolving blade defects, in the step of laying the mold layer, the adhesive material is glass fiber tape or double-sided tape.

[0023] Optionally, in the above method for solving blade defects, in the step of laying the vacuum auxiliary material, the laying area increment of the vacuum auxiliary material is not less than 1% of the laying area of ​​the overall layer.

[0024] The method for solving blade defects provided by the present application is to design the blunt trailing edge angle of the blade to be an obtuse angle at the initial stage of the blade aerodynamic design, and the blunt trailing edge of the blade is an arc-shaped structure, avoiding the aerodynamic design of the blunt trailing edge with a straight edge, so that the prepared blade mold lays a hardware foundation for solving the subsequent optimization of the blunt trailing edge rich resin. At the same time, in the structural ply design stage, the blunt trailing edge core material of the blade and the non-blunt trailing edge area core material are designed separately, and a connecting glass fiber ply is arranged between the two, thereby eliminating the problem that the structural ply cannot be completely fitted. In the step of laying the shell ply, the first layer of glass fiber ply is laid on the inner surface of the blade mold, and at the same time, it is fixed to the blunt trailing edge corner of the blade mold with an adhesive material, and the first unidirectional air permeable layer is laid in the non-blunt trailing edge corner area of ​​the blade mold to prevent impurities and gas from entering, and the structural ply and auxiliary ply are laid on top of the first layer of glass fiber ply until the overall ply is laid. When laying the vacuum auxiliary material, the vacuum auxiliary material is laid on top of the overall layer, and the laying area of ​​the vacuum auxiliary material is larger than the laying area of ​​the overall layer, so as to ensure that there is a margin when laying the vacuum auxiliary material, which can prevent overhead operation, thereby solving the resin-rich defect of the blunt trailing edge of the blade. From the above examples, it can be seen that the method for solving blade defects provided by the present application solves the problem of resin-rich defects on the blunt trailing edge of large blades by comprehensively considering the aerodynamic design of the blade, the structural layer design, the laying of the shell layer and the laying of the vacuum auxiliary material.

[0025] The technical features mentioned above, the technical features to be mentioned below, and the technical features shown separately in the drawings can be combined with each other arbitrarily, as long as the combined technical features are not contradictory. All feasible feature combinations are technical contents clearly recorded in this article. Any of the multiple sub-features contained in the same sentence can be applied independently, and does not have to be applied together with other sub-features. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are merely embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on the provided drawings without paying any creative work.

[0027] Figure 1 Schematic diagram of the method flow for solving blade defects provided in the embodiment of the present application Figure 1 ;

[0028] Figure 2 Schematic diagram of the method flow for solving blade defects provided in the embodiment of the present application Figure 2 . DETAILED DESCRIPTION

[0029] The core of the present application is to provide a method for solving blade defects, so as to solve the resin-rich defect of the blunt trailing edge of a large blade.

[0030] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0031] During the infusion process of large blades, resin-rich defects usually appear at the blunt trailing edge of the blade. Defects at this location are more difficult to repair in the subsequent process and the repair cycle is longer, which directly affects the overall molding cycle of the blade.

[0032] For this reason, Figure 1 As shown, the embodiment of the present application discloses a method for solving blade defects, including step S100 blade aerodynamic design, step S101 structural layer design, step S102 laying mold layers, and step S103 laying vacuum auxiliary materials. Through comprehensive consideration of step S100 blade aerodynamic design, step S101 structural layer design, step S102 laying mold layers, and step S103 laying vacuum auxiliary materials, the problem of resin-rich defects on the blunt trailing edge of large blades is solved.

[0033] The following will be combined Figure 1 and Figure 2 The method for solving blade defects disclosed in the embodiment of the present application is specifically explained and illustrated.

[0034] Step S100, blade aerodynamic design;

[0035] By designing the blunt trailing edge angle of the blade to be an obtuse angle, and the blunt trailing edge of the blade adopts an arc structure to avoid the aerodynamic design of the blunt trailing edge with a straight edge, the prepared blade mold can lay a hardware foundation for solving the subsequent optimization of the blunt trailing edge rich in resin. Optionally, the blunt trailing edge angle of the blade can adopt an arc structure of not less than 120°, so that the prepared blade mold can lay a hardware foundation for solving the subsequent optimization of the blunt trailing edge rich in resin.

[0036] Step S101, structural ply design;

[0037] A connecting glass fiber ply is provided between the blunt trailing edge core material and the non-blunt trailing edge core material of the blade. Specifically, in the structural ply design stage, the blunt trailing edge core material and the non-blunt trailing edge core material of the blade are designed separately, and a connecting glass fiber ply is provided between the two, thereby eliminating the problem that the structural ply cannot be completely fitted. Among them, the connecting glass fiber ply can be multi-layered, and each connecting glass fiber ply can be stacked one by one on site, or can be prefabricated as an integrated structure and then assembled on site. It should be noted that the non-blunt trailing edge area refers to the area of ​​the blade other than the blunt trailing edge.

[0038] Step S102, laying the shell layer;

[0039] The first layer of glass fiber ply is laid on the inner surface of the blade mold and fixed to the blunt tail edge corner of the blade mold by adhesive material. The first unidirectional air-permeable layer is laid in the non-blunt tail edge corner area of ​​the blade mold, and the structural ply and auxiliary ply are laid above the first layer of glass fiber ply until the overall ply is laid. At the same time, a second unidirectional air-permeable layer can be laid above the overall ply, so that the residual glue treatment and auxiliary air extraction can be carried out during the infusion process through the first unidirectional air-permeable layer and the second unidirectional air-permeable layer, thereby improving the infusion quality and solving the resin-rich defect of the blunt tail edge of the blade. Optionally, the adhesive material can be glass fiber tape or double-sided tape, so that the first layer of glass fiber ply is bonded and fixed to the blunt tail edge corner of the blade mold by glass fiber tape or double-sided tape. In addition, the first unidirectional air-permeable layer and the second unidirectional air-permeable layer can use unidirectional air-permeable membranes to prevent impurities and gas from entering. Of course, the first unidirectional air-permeable layer and the second unidirectional air-permeable layer can also use continuous mats or chopped strand mats, which are not limited in this article. It should be noted that the structural ply refers to the main structure of the blade and the part that bears the main load, and the auxiliary ply refers to the ply that assists in realizing other functions of the blade or improves local performance, which can be used to improve the performance and function of the structural ply.

[0040] Step S103, laying vacuum auxiliary materials;

[0041] The vacuum auxiliary material is laid on the top of the overall paving layer, and the laying area of ​​the vacuum auxiliary material is larger than the laying area of ​​the overall paving layer, so as to ensure that there is a margin when laying the vacuum auxiliary material, which can prevent overhead operation. Optionally, the laying area increment of the vacuum auxiliary material is not less than 1% of the laying area of ​​the overall paving layer, so as to effectively prevent overhead operation and effectively solve the problem of resin-rich defects on the blunt trailing edge of the blade.

[0042] The method for solving blade defects disclosed in the embodiment of the present application is to design the blunt trailing edge angle of the blade to be an obtuse angle at the initial stage of the blade aerodynamic design, and the blunt trailing edge of the blade is an arc-shaped structure, avoiding the aerodynamic design of the blunt trailing edge with a straight edge, so that the prepared blade mold lays a hardware foundation for solving the subsequent optimization of the blunt trailing edge rich in resin. At the same time, in the structural ply design stage, the blunt trailing edge core material of the blade is designed separately from the core material of the non-blunt trailing edge area, and a connecting glass fiber ply is arranged between the two, thereby eliminating the problem that the structural ply cannot be completely fitted. In the step of laying the shell ply, the first layer of glass fiber ply is laid on the inner surface of the blade mold, and is fixed to the blunt trailing edge corner of the blade mold with an adhesive material, and the first unidirectional air permeable layer is laid in the non-blunt trailing edge corner area of ​​the blade mold to prevent impurities and gas from entering, and the structural ply and auxiliary ply are laid on top of the first layer of glass fiber ply until the overall ply is laid. When laying vacuum auxiliary materials, lay them above the overall paving layer, and the laying area of ​​the vacuum auxiliary materials is larger than the laying area of ​​the overall paving layer to ensure that there is a margin when laying the vacuum auxiliary materials, which can prevent overhead operation.

[0043] The method for solving blade defects disclosed in the embodiment of the present application solves the problem of resin-rich defects on the blunt trailing edge of large blades by comprehensively considering the blade aerodynamic design, structural layup design, shell layup and vacuum auxiliary material laying processes.

[0044] like Figure 2 As shown, the method for solving blade defects also includes step S104 of vacuuming and step S105 of pouring and curing.

[0045] Step S104, vacuuming;

[0046] The vacuum auxiliary material is evacuated under the conveying pipeline until the pressure maintenance is completed. Specifically, during the vacuum evacuation process, the laying area of ​​the vacuum auxiliary material can be compacted to further achieve the anti-overhead operation until the pressure maintenance is completed.

[0047] Step S105, pouring and curing;

[0048] By connecting the air extraction delivery pipeline to the glue injection equipment, the resin glue can be poured into the bottom of the vacuum auxiliary material through the delivery pipeline, and can be cured by heating or pressurizing to ensure the strength of the blade shell. It should be noted that during the pouring and curing process, the flow of the resin glue in the pouring area and the working state of the one-way air permeable layer need to be checked, and abnormal conditions in the process should be handled in time to ensure the pouring quality of the blade shell.

[0049] The terms "first" and "second" and the like in the specification and claims of this application and the above drawings are used to distinguish different objects, rather than to describe a specific order. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions. For example, a process, method, system, product or device that includes a series of steps or units is not limited to the listed steps or units, but may include steps or units that are not listed.

[0050] The above description of the disclosed embodiments enables those skilled in the art to implement or use the present application. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present application. Therefore, the present application will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A method for solving blade defects, characterized in that: Includes steps: The blade is aerodynamically designed, the blunt trailing edge of the blade is designed to be an obtuse angle, and the blunt trailing edge of the blade is an arc-shaped structure, and a blade mold is prepared; Structural ply design, providing a connecting glass fiber ply between the blunt trailing edge core material and the non-blunt trailing edge core material of the blade; Laying the shell ply, laying the first layer of glass fiber ply on the inner surface of the blade mold, and fixing it at the blunt trailing edge corner of the blade mold by means of adhesive material, laying the first unidirectional air permeable layer at the non-blunt trailing edge corner area of ​​the blade mold, and laying the structural ply and auxiliary ply on top of the first layer of glass fiber ply until the overall ply laying is completed; Laying the vacuum auxiliary material, laying the vacuum auxiliary material on the top of the overall paving layer, and the laying area of ​​the vacuum auxiliary material is larger than the laying area of ​​the overall paving layer.

2. The method for solving blade defects according to claim 1, characterized in that: Also includes the steps: Vacuuming, vacuuming the bottom of the vacuum auxiliary material through the conveying pipeline until the pressure maintenance is completed; Injection and curing: injecting resin glue into the lower part of the vacuum auxiliary material through the conveying pipeline and curing it.

3. The method for solving blade defects according to claim 2, characterized in that: The vacuuming step further includes compacting the laying area of ​​the vacuum auxiliary material.

4. The method for solving blade defects according to claim 2, characterized in that: In the steps of pouring and curing, the resin glue is cured by heating or pressurizing.

5. The method for solving blade defects according to claim 1, characterized in that: In the mold lamination step, a second one-way air-permeable layer is laid on top of the overall lamination.

6. The method for solving blade defects according to claim 5, characterized in that: The first one-way air-permeable layer is one of a one-way air-permeable film, a continuous mat and a chopped strand mat; and / or, The second one-way air-permeable layer is one of a one-way air-permeable film, a continuous mat and a chopped strand mat.

7. The method for solving blade defects according to claim 1, characterized in that: In the step of structural ply design, the connecting glass fiber ply is multi-layered, and each layer of the connecting glass fiber ply is prefabricated into an integrated structure.

8. The method for solving blade defects according to claim 1, characterized in that: In the step of aerodynamic design of the blade, the blunt trailing edge angle of the blade is not less than 120°.

9. The method for solving blade defects according to claim 1, characterized in that: In the step of laying the mold layer, the adhesive material is glass fiber tape or double-sided tape.

10. The method for solving blade defects according to claim 1, characterized in that: In the step of laying the vacuum auxiliary material, the increase in the laying area of ​​the vacuum auxiliary material is not less than 1% of the laying area of ​​the entire paving layer.

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