Blade insert for a wind turbine rotor blade and related methods

Abstract

A blade insert for coupling a first blade segment to a second blade segment is disclosed. The blade insert may include an aerodynamic body extending between a first end configured to be coupled to the first blade segment and a second end configured to be coupled to the second blade segment. The aerodynamic body may include a pressure side and a suction side extending between a leading edge and a trailing edge. In addition, the aerodynamic body may define a chord, wherein the chord at the first end is substantially equal to the chord at the second end.

What is claimed is: 
     
         1 . A rotor blade assembly, comprising:
 a first blade segment having a first joint end;   a second blade segment having a second joint end; and,   a blade insert having a first end coupled to the first joint end such that a first interface is defined between the blade insert and the first blade segment and a second end coupled to the second joint end such that a second interface is defined between the blade insert and the second blade segment, the blade insert defining a chord, the chord at the first interface being substantially equal to the chord at the second interface.   
     
     
         2 . The rotor blade assembly of  claim 1 , wherein the chord of the blade insert is substantially constant between the first and second interfaces. 
     
     
         3 . The rotor blade assembly of  claim 1 , wherein the blade insert defines an airfoil-shaped cross-section, the airfoil shaped cross-section at the first interface being substantially the same as the airfoil-shaped cross-section at the second interface. 
     
     
         4 . The blade insert of  claim 3 , wherein the airfoil-shaped cross-section of the blade insert is substantially constant between the first and second interfaces. 
     
     
         5 . The rotor blade assembly of  claim 1 , wherein the blade insert defines a length between the first and second ends ranging from about 1 meter to about 20 meters. 
     
     
         6 . The rotor blade assembly of  claim 1 , wherein the first blade segment defines a first length and the second blade segment defines a second length, the first and second lengths together defining a total segment span, wherein the first length ranges from about 40% to about 95% of the total segment span. 
     
     
         7 . The rotor blade assembly of  claim 1 , wherein the first blade segment defines a maximum chord location for the rotor blade assembly. 
     
     
         8 . The rotor blade assembly of  claim 1 , wherein a center of gravity of the rotor blade assembly is positioned within the first blade segment. 
     
     
         9 . The rotor blade assembly of  claim 1 , wherein the blade insert defines a longitudinal axis between the first and second ends, at least a portion of the blade insert being twisted about the longitudinal axis. 
     
     
         10 . The rotor blade assembly of  claim 1 , wherein the blade insert defines a longitudinal axis between the first and second ends, at least a portion of the blade insert being curved relative to the longitudinal axis. 
     
     
         11 . The rotor blade assembly of  claim 1 , wherein at least a portion of the blade insert is formed from a material having a greater stiffness than a material used to form the first and second blade segments. 
     
     
         12 . The rotor blade assembly of  claim 1 , wherein the blade insert has a constant stiffness between the first and second interfaces. 
     
     
         13 . The rotor blade assembly of  claim 1 , wherein the first blade segment comprises a root segment and the second blade segment comprises a tip segment. 
     
     
         14 . A blade insert for coupling a first blade segment to a second blade segment, the blade insert comprising:
 an aerodynamic body extending between a first end configured to be coupled to the first blade segment and a second end configured to be coupled to the second blade segment, the aerodynamic body including a pressure side and a suction side extending between a leading edge and a trailing edge, the aerodynamic body defining a chord, the chord at the first end being substantially equal to the chord at the second end.   
     
     
         15 . The blade insert of  claim 14 , wherein the chord is substantially constant between the first and second ends. 
     
     
         16 . The blade insert of  claim 14 , wherein the aerodynamic body defines an airfoil-shaped cross-section, the airfoil shaped cross-section at the first end being substantially the same as to the airfoil-shaped cross-section at the second end. 
     
     
         17 . The blade insert of  claim 14 , wherein the aerodynamic body defines a length between the first and second ends ranging from about 1 meter to about 20 meters. 
     
     
         18 . The blade insert of  claim 14 , wherein the aerodynamic body defines a longitudinal axis between the first and second ends, at least a portion of the aerodynamic body being twisted about the longitudinal axis. 
     
     
         19 . The blade insert of  claim 14 , wherein the aerodynamic body defines a longitudinal axis between the first and second ends, at least a portion of the aerodynamic body being curved relative to the longitudinal axis. 
     
     
         20 . A rotor blade assembly, comprising:
 a first blade segment having a first joint end;   a second blade segment having a second joint end; and,   a blade insert having a first end coupled to the first joint end such that a first interface is defined between the blade insert and the first blade segment and a second end coupled to the second joint end such that a second interface is defined between the blade insert and the second blade segment,   wherein a stiffness of the blade insert is greater than a stiffness of at least one of the first blade segment at the first joint end or the second blade segment at the second joint end.   
     
     
         21 . A rotor blade assembly, comprising:
 a first blade segment having a first joint end;   a second blade segment having a second joint end; and,   a blade insert having a first end coupled to the first joint end such that a first interface is defined between the blade insert and the first blade segment and a second end coupled to the second joint end such that a second interface is defined between the blade insert and the second blade segment,   wherein the blade insert transitions between a constant cross-section and a varying cross-section between the first and second interfaces.   
     
     
         22 . The rotor blade assembly of  claim 21 , wherein the blade insert transitions between a constant cross-section and a varying cross-section at more than one location between the first and second interfaces.