Wind turbine rotor blade assembly having an access window and related methods
A rotor blade assembly having an access window and methods for assembling a rotor blade are disclosed. The rotor blade assembly may generally include a first shell component and a second shell component. The first shell component may be secured to the second shell component. Additionally, an access region may be defined in the first shell component and/or the second shell component. The access region may generally be configured such that an access window is defined in the rotor blade assembly. The access window may be configured to provide access to the interior of a portion of the rotor blade assembly.
1. A rotor blade assembly for a wind turbine, the rotor blade assembly comprising:
a root segment comprising a root shell and an internal root component;
a tip segment configured to be secured to the root segment, the tip segment comprising a tip shell and an internal tip component; and,
an access region defined in at least one of the root shell and the tip shell, the access region being configured such that an access window is defined at an interface between the root shell and the tip shell;
wherein the access window is configured to provide access to the interior of a portion of the rotor blade assembly.
2. The rotor blade assembly of claim 1 , further comprising a shell segment configured to cover the access window.
3. The rotor blade assembly of claim 2 , wherein the access region is formed on a pressure side of at least one of the root shell and the tip shell such that the shell segment is configured as a pressure side skin component.
4. The rotor blade assembly of claim 2 , wherein the access region is formed on a suction side of at least one of the root shell and the tip shell such that the shell segment is configured as a suction side skin component.
5. The rotor assembly blade of claim 2 , wherein the access region is formed at a leading edge of at least one of the root shell and the tip shell such that the shell segment is configured as a leading edge component.
6. The rotor blade assembly of claim 2 , wherein the access region is formed at a trailing edge of at least one of the root shell and the tip shell such that the shell segment is configured as a trailing edge component.
7. The rotor blade assembly of claim 2 , wherein the shell segment is secured to the root shell and the tip shell such that a substantially continuous aerodynamic profile is defined by the rotor blade assembly.
8. The rotor blade assembly of claim 7 , wherein an overlaminate is disposed around the perimeter of the shell segment so as to define a smooth aerodynamic transition between the shell segment and the tip and root shells.
9. The rotor blade assembly of claim 1 , wherein an overlaminate is disposed at an interface of the tip shell and root shell so as to define a smooth aerodynamic transition between the tip segment and the root segment.
10. The rotor blade assembly of claim 1 , wherein the internal root component and the internal tip component each comprise a pair of spar caps and at least one shear web extending between the spar caps.
11. The rotor blade assembly of claim 1 , wherein the access window is configured to provide access to an interface of the internal root component and the internal tip component.
12. The rotor blade assembly of claim 11 , wherein the access window is configured to provide physical access to the interface of the internal root component and the internal tip component.
13. A method for assembling a rotor blade having a root segment including a root shell and an internal root component and a tip segment including a tip shell and an internal tip component, the method comprising:
aligning the root segment and the tip segment such that an access window is defined at an interface between the tip shell and the root shell;
securing the internal tip component to the internal root component; and,
securing a shell segment over the access window.
14. The method of claim 13 , further comprising securing the tip shell to the root shell.
15. The method of claim 14 , further comprising applying an overlaminate at the interface of the tip shell and the root shell.
16. The method of claim 13 , further comprising applying an overlaminate around the perimeter of the shell segment.
17. The method of claim 13 , wherein the internal root component and the internal tip component each comprise a pair of spar caps and at least one shear web extending between the spar caps.
18. A rotor blade assembly for a wind turbine, the rotor blade assembly comprising:
a first shell component;
a second shell component configured to be secured to the first shell component;
an access region defined in at least one of the first shell component and the second shell component, the access region being configured such that an access window is defined at an interface between the first shell component and the second shell component; and,
a shell segment configured to cover the access window,
wherein the access window is configured to provide access to the interior of a portion of the rotor blade assembly.
19. The rotor blade assembly of claim 18 , wherein the first shell component comprises a pressure side shell component and the second shell component comprises a suction side shell component.
20. The rotor blade assembly of claim 18 , wherein the first shell component comprises a tip shell and the second shell component comprises a root shell.