Abstract: An aerodynamic vane insert configured to reproduce at least an aerodynamic vane of a finished centrifugal impeller and a method for building a centrifugal impeller for a turbomachine.

Abstract: A centrifugal impeller for a turbomachine is provided. The centrifugal impeller comprises a plurality of aerodynamic vanes, each of the aerodynamic vanes having internal walls on which is associated a fabric element.

Abstract: A mold for a centrifugal impeller for a turbomachine is provided. The mold comprises at least one annular insert, wherein the annular insert comprises a plurality of aerodynamic vane inserts configured to reproduce an annular assembly of aerodynamic vanes of a finished centrifugal impeller.

Abstract: A centrifugal impeller for a turbomachine is provided. The centrifugal impeller comprises a plurality of aerodynamic vanes, each of the aerodynamic vanes having internal walls on which is associated a fabric element.

Abstract: A mold for a centrifugal impeller for a turbomachine is provided. The mold comprises at least one annular insert, wherein the annular insert comprises a plurality of aerodynamic vane inserts configured to reproduce an annular assembly of aerodynamic vanes of a finished centrifugal impeller.

Abstract: In one aspect, a method for assembling an outlet guide vane is provided. The method includes providing an outlet guide vane frame having a first side and a second side. The outlet guide vane includes a radially inward flange coupled to a radially outward flange by a leading edge. A trailing edge is coupled to the radially inward flange and the radially outward flange aft of the leading edge. A cavity is defined between the radially inward flange, the radially outward flange, the leading edge, and the trailing edge. A first and a second mating surface circumscribe the cavity on the first and second sides respectively. The method further includes coupling a filler portion within the cavity wherein the filler portion includes a third side and a fourth side, coupling a first skin to the third side and the first mating surface, and coupling a second skin to the fourth side and the second mating surface, wherein at least one of the first skin and the second skin are fabricated from a composite material.

Abstract: In one aspect, a method for assembling an outlet guide vane is provided. The method includes providing an outlet guide vane frame having a first side and a second side. The outlet guide vane includes a radially inward flange coupled to a radially outward flange by a leading edge. A trailing edge is coupled to the radially inward flange and the radially outward flange aft of the leading edge. A cavity is defined between the radially inward flange, the radially outward flange, the leading edge, and the trailing edge. A first and a second mating surface circumscribe the cavity on the first and second sides respectively. The method further includes coupling a filler portion within the cavity wherein the filler portion includes a third side and a fourth side, coupling a first skin to the third side and the first mating surface, and coupling a second skin to the fourth side and the second mating surface, wherein at least one of the first skin and the second skin are fabricated from a composite material.

Abstract: A method for constructing a wind turbine blade for installation at a wind farm location is described herein. In accordance with the present method, primary components of the wind turbine blade, such as, for example, the root and the spar caps, are manufactured in a first manufacturing facility. Secondary components such as, for example, the skin, are manufactured at a second manufacturing facility, which is closer to the wind farm location than the first manufacturing facility. The manufactured primary and secondary components may be assembled in an assembly location near the wind farm.

Abstract: In accordance with certain embodiments, a wind turbine blade includes an outer skin and an internal support structure. The skin has a closed airfoil shape and includes an outer surface, an inner surface, and opposite sides along a length of the blade. The internal support structure is disposed within the closed airfoil shape. The internal support structure includes at least one shear load bearing member disposed across the opposite sides and oriented lengthwise along the length of the blade. The internal support structure further includes a plurality of bending load bearing members disposed along the inner surface in a lengthwise direction along the length of the blade. The internal support structure is configured to position a shear center and a center of aerodynamic pressure loading of the blade at different locations relative to one another.

Abstract: A fan blade including a plurality of fiber composite layers and at least one high elongation fiber composite strip joining one of the fiber composite layers at a joint. A method of making a fan blade includes joining a plurality of fiber composite layers and joining at least one high elongation fiber composite strip to one of the plurality of fiber composite layers. An end of the high elongation fiber composite strip meets an end of the fiber composite layer at a joint.