Abstract: Provided is a rotor blade that may include a first layer having first plurality of fibers oriented at first angle of about 20 to 30 degrees relative to a long axis of the rotor blade, a second plurality of fibers oriented at a second angle of about 60 to 75 degrees relative to the first plurality of fibers, and a third plurality of fibers oriented at a third angle of about ?60 to about ?75 degrees relative to the second plurality of fibers.

Abstract: Provided is a rotor blade that may include a first layer having first plurality of fibers oriented at first angle of about 20 to 30 degrees relative to a long axis of the rotor blade, a second plurality of fibers oriented at a second angle of about 60 to 75 degrees relative to the first plurality of fibers, and a third plurality of fibers oriented at a third angle of about ?60 to about ?75 degrees relative to the second plurality of fibers.

Abstract: Provided is a rotor blade that may include a first layer having first plurality of fibers oriented at first angle of about 10 to 30 degrees relative to a long axis of the rotor blade, a second plurality of fibers oriented at a second angle of about 60 to 75 degrees relative to the first plurality of fibers, and a third plurality of fibers oriented at a third angle of about -60 to about -75 degrees relative to the second plurality of fibers.

Abstract: Provided is a rotor blade that may include a first layer having first plurality of fibers oriented at first angle of about 10 to 30 degrees relative to a long axis of the rotor blade, a second plurality of fibers oriented at a second angle of about 60 to 75 degrees relative to the first plurality of fibers, and a third plurality of fibers oriented at a third angle of about ?60 to about ?75 degrees relative to the second plurality of fibers.

Abstract: Provided is a rotor blade that may include a first layer having a first plurality of non-woven fibers oriented at first angle of about 10 to 30 degrees relative to a long axis of the rotor blade, a second plurality of non-woven fibers oriented at a second angle of about 60 to 75 degrees relative to the first plurality of fibers, and a third plurality of non-woven fibers oriented at a third angle of about ?60 to about ?75 degrees relative to the second plurality of fibers.

Abstract: Example embodiments relate to an insert and a method for attaching the insert to a structure. In example embodiments the structure may be comprised of a composite material, a metal, and a ceramic.

Abstract: Disclosed is an engineered structure which includes pultrusions usable for resisting a bending load.

Abstract: Disclosed is a structure that may include a first flange, a second flange, and a web connecting the first flange to the second flange. In example embodiments, the web may include at least one end with at least two angled members attaching to one of the first flange and the second flange and another end connecting to the other of the first flange and the second flange. Disclosed also is a wind turbine blade that includes the structure.

Abstract: Provided is a rotor blade that may include a first layer having first plurality of fibers oriented at first angle of about 10 to 30 degrees relative to a long axis of the rotor blade, a second plurality of fibers oriented at a second angle of about 60 to 75 degrees relative to the first plurality of fibers, and a third plurality of fibers oriented at a third angle of about ?60 to about ?75 degrees relative to the second plurality of fibers.

Abstract: A balancing of aerodynamic optimization and structural optimization provides a wind turbine airfoil having substantially improved performance characteristics. Mathematic modeling yields maximum aerodynamic criteria that are coupled with a structural analysis to modify the optimum aerodynamic design into a balanced, substantially optimized airfoil configuration. The resulting airfoils have substantial performance impact on GAEP. The airfoil is based on the theoretical optimum aerodynamic structure modified as required to maximize structural integrity. The method for maximizing airfoil performance permits the design of airfoils of predictable performance while achieving necessary structural integrity. A family of airfoils having operational and structural characteristics with substantially enhanced performance capability includes thickness-to-chord ratios ranging from 14% to 45%.