Modular wind turbine blade and associated method of manufacture

Patent metadata

Field	Value
Publication number	US-11396154-B2
Application number	US-201816955348-A
Country	US
Kind code	B2
Filing date	Dec 18, 2018
Priority date	Dec 21, 2017
Publication date	Jul 26, 2022
Grant date	Jul 26, 2022

Abstract

A method of making a modular wind turbine blade is described. The modular blade comprises first and second blade modules connected together by a scarf joint between tapered spar caps of the respective blade modules. According to the method, first and second blade modules are laid up in the same mould assembly. A separating layer is arranged between the layups of the first and second module in a joint region of the mould. The separating layer has a thickness corresponding to a required bond thickness in the scarf joint when the modules are bonded together.

First claim

The invention claimed is:

1. A method of making first and second blade modules of a modular wind turbine blade, the first and second blade modules each having a spar cap section with a tapered end, and the modules being configured for connection end-to-end by an adhesively bonded scarf joint between the tapered end portions of respective spar cap sections of the blade modules, and the method comprising:
providing a blade mould having a first region, a second region and a joint region between the first and second regions;
arranging a first outer skin layer of fibrous material in the first region of the mould and in the joint region of the mould to form an outer skin of the first blade module;
arranging a first spar cap section having a tapered end portion on top of the first outer skin layer such that the tapered end portion is in the joint region of the mould and a remainder of the first spar cap section extends into the first region of the mould;
arranging a first separating layer on top of the tapered end portion of the first spar cap section in the joint region of the mould;
arranging a second outer skin layer of fibrous material in the second region of the mould to form an outer skin of the second blade module;
arranging a second spar cap section having a tapered end portion in the mould such that its tapered end portion overlaps the tapered end portion of the first spar cap section in the joint region of the mould with the first separating layer sandwiched there between, and such that a remainder of the second spar cap section extends into the second region of the mould and is on top of the second outer skin layer;
integrating the first outer skin layer with the first spar cap section to form a shell portion of the first blade module;
integrating the second outer skin layer with the second spar cap section to form a shell portion of the second blade module;
separating the shell portions of the first and second blade modules; and
selecting a thickness of the first separating layer to correspond to a required bond thickness of the scarf joint between the tapered end portions of the first and second spar cap sections when the first and second modules are connected together to form the modular blade.

2. The method of claim 1 , further comprising arranging part of the second outer skin layer around the tapered end portion of the first spar cap section in the joint region of the mould.

3. The method of claim 1 , further comprising arranging a second separating layer such that it overlaps an edge portion of the first outer skin layer in the joint region of the mould, and wherein the second outer skin layer extends up to or overlaps the second separating layer.

4. The method of claim 3 , wherein the first separating layer is elongate and extends in a spanwise direction of the mould and the second separating layer is elongate and extends in a chordwise direction of the mould.

5. The method of claim 3 , wherein the second separating layer is integral with the first separating layer.

6. The method of claim 3 , further comprising arranging peel ply in the mould in areas directly above and/or below the second separating layer.

7. The method of claim 3 , wherein the second separating layer comprises perforations.

8. The method of claim 1 , further comprising arranging first core material in the mould on top of the first outer skin layer and arranging a third separating layer in the joint region of the mould such that it covers an end face of the first core material.

9. The method of claim 8 , further comprising arranging a second separating layer such that it overlaps an edge portion of the first outer skin layer in the joint region of the mould, wherein the second outer skin layer extends up to or overlaps the second separating layer, and wherein the third separating layer is integral with the second separating layer and forms a step with the second separating layer.

10. The method of claim 9 , wherein the second separating layer is integral with the first separating layer.

11. The method of claim 8 , wherein the method comprises arranging second core material in the mould on top of the second outer skin layer and wherein end faces of the second core material abut the third separating layer.

12. The method of claim 8 , further comprising arranging peel ply in the mould in areas directly above and/or below the third separating layer.

13. The method of claim 8 , wherein the third separating layer comprises perforations.

14. The method of claim 1 , further comprising arranging a first inner skin layer of fibrous material on top of the first spar cap section to form an inner skin of the first blade module, and arranging a fourth separating layer in the mould such that it overlaps an edge portion of the first inner skin layer.

15. The method of claim 14 , further comprising arranging a second inner skin layer of fibrous material on top of the second spar cap section to form an inner skin of the second blade module, and wherein the second inner skin layer extends up to or overlaps the fourth separating layer.

16. The method of claim 14 , wherein the fourth separating layer is integral with the first separating layer.

17. The method of claim 1 , further comprising arranging peel ply in the mould in areas directly above and/or below the first separating layer.

18. The method of claim 1 , wherein the first separating layer comprises perforations.

19. The method of claim 1 , wherein the first separating layer is made from a non-stick material.

20. The method of claim 1 , wherein the first and/or second spar cap sections comprise at least two parallel spaced-apart beams.

Assignees

• Vestas Wind Sys As

Inventors

• Barton Leon
• Hunter Robert
• Owens Christopher

Classifications

• B29C66/543

  joining more than two hollow-preforms to form said hollow articles · CPC title

• B29C65/54

  between pre-assembled parts · CPC title

• B29C65/7826

  said distance pieces being non-integral with the parts to be joined, e.g. particles · CPC title

• B29D99/0028 Primary

  hollow blades · CPC title

• F05B2240/302

  Segmented or sectional blades · CPC title