Abstract: A blade insert for coupling a first blade segment to a second blade segment is disclosed. The blade insert may generally include an aerodynamic body extending between a forward end configured to be coupled to the first blade segment and an aft end configured to be coupled to the second blade segment. The aerodynamic body may include a top side extending between a forward edge and an aft edge. The top side may define a top scarfed section at its forward edge. The aerodynamic body may further include a bottom side extending between a forward edge and an aft edge. The bottom side may define a bottom scarfed section at its forward edge. Additionally, at least a portion of the forward edge of the top side may be configured to be offset relative to the forward edge of the bottom side.

Abstract: A system for installing a blade insert between a root portion and a tip portion of a rotor blade of a wind turbine is disclosed. The system may include a root cradle assembly configured to support the root portion of the rotor blade and a tip cradle assembly configured to support the tip portion of the rotor blade. At least one of the tip cradle assembly or the root cradle assembly may be movable relative to the other of the tip cradle assembly or the root cradle assembly to allow the tip portion to be spaced apart from the root portion after the rotor blade has been divided between the root and tip portions. In addition, the system may include an insert cradle assembly configured to support a blade insert for the rotor blade. The insert cradle assembly may be configured to be positioned between the root cradle assembly and the tip cradle assembly so as to position the blade insert between the root portion and the tip portion.

Abstract: A rotor blade assembly for a wind turbine has a rotor blade. A strip-member blade accessory is mounted to one of the rotor blade surfaces that stretches under normal operating conditions of the wind turbine. The blade accessory has a base portion. An attachment layer connects the base portion to the rotor blade surface and has a lower shear modulus than the base portion to allow for shear slippage between the base portion and the underlying rotor blade surface.

Abstract: A wind turbine rotor blade assembly and associated method include a rotor blade having a pressure side, a suction side, a leading edge, and a trailing edge extending in a generally span-wise direction between a tip and a root. An edge extension panel is attached along either of the leading edge or trailing edge (or along both edges) in a generally span-wise direction from adjacent the root towards the tip. The edge extension panels include a cured and hardened viscous material continuous core formed onto the leading or trailing edge with a contoured generally aerodynamic outer surface.

Abstract: A method for determining pitch angles for at least one rotor blade of a wind turbine during peak shaving is disclosed. The method may generally include receiving a signal with a controller associated with a peak shaving parameter of the wind turbine and determining a target pitch angle for the at least one rotor blade based on a mathematical relationship between the target pitch angle and the peak shaving parameter, wherein the mathematical relationship is modeled as a non-linear function.

Abstract: A joint for connecting a first blade segment and a second blade segment of a wind turbine rotor blade is disclosed. The joint includes a body, the body including an outer surface and an inner surface. The outer surface has an aerodynamic contour that generally corresponds to an aerodynamic contour of the first blade segment and the second blade segment. The body includes a pressure side and a suction side extending between a leading edge and a trailing edge. In some embodiments, the joint further includes a channel defined in the outer surface of the body. The channel includes a generally continuous base wall extending between opposing sidewalls. The inner surface includes the base wall. In other embodiments, the joint further includes a channel defined in the body, and a shell extending from the body in a generally span-wise direction.

Abstract: A spar cap assembly for a rotor blade of a wind turbine is disclosed. In general, the spar cap assembly may include a tensile spar cap formed from a composite material and configured to engage an inner surface of the rotor blade. The tensile spar cap may generally have a first thickness and a first cross-sectional area. Additionally, the spar cap assembly may include a compressive spar cap formed from the same composite material and configured to engage an opposing inner surface of the rotor blade. The compressive spar cap may generally have a second thickness and a second cross-sectional area that is greater than the first cross-sectional area. Additionally, the composite material is generally selected so that at least one of a strength and a modulus of elasticity of the composite material differs depending on whether the material is in tension or in compression.

Abstract: A turbine rotor blade includes a hollow airfoil joined to a platform and dovetail. A main flow channel extends longitudinally in span through the blade and is bound chordally by opposite partitions transversely bridging opposite sidewalls of the airfoil. A damper rib and transversely opposite damper pad are arranged together in a plurality of pairs spaced longitudinally apart in the airfoil and chordally positioned intermediate to the partitions to provide unobstructed forward and aft portions of the flow channel for channeling a coolant therethrough. The damper ribs and pads are configured to receive a wire damper through the channel to locally dampen vibration while minimizing obstruction of the coolant flow therethrough.

Abstract: A turbine rotor blade includes a hollow airfoil joined to a platform and dovetail. A main flow channel extends longitudinally in span through the blade and is bound chordally by opposite partitions transversely bridging opposite sidewalls of the airfoil. A damper rib and transversely opposite damper pad are arranged together in a plurality of pairs spaced longitudinally apart in the airfoil and chordally positioned intermediate to the partitions to provide unobstructed forward and aft portions of the flow channel for channeling a coolant therethrough. The damper ribs and pads are configured to receive a wire damper through the channel to locally dampen vibration while minimizing obstruction of the coolant flow therethrough.

Abstract: A turbine blade includes an airfoil, platform, and dovetail. The airfoil includes a plurality of flow channels being separated by partitions. A primary partition includes an inner saddle. And, a bipedal damper includes a pair of legs extending into the flow channels, and integrally joined together at a seat bridging the saddle.

Abstract: A fiber reinforced composite article is made by providing a plurality of layers of first, substantially dry, unimpregnated reinforcing fibers, sometimes called in-plane fibers. Such layers are stacked into a preform of a stack of layers. While in the dry, unimpregnated condition, a plurality of spaced apart second reinforcing members are inserted into the preform at an angle, for example transversely, to the stack of layers. In this condition, the preform is impregnated with a matrix about the first reinforcing fibers and the second reinforcing members. The article product comprises the plurality of stacked layers of the first reinforcing fibers and the plurality of the spaced apart second reinforcing members disposed beside or adjacent the first reinforcing fibers, with a substantially solid matrix disposed about the reinforcing fibers and members.

Abstract: A counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row axially spaced from the first fan blade row and connected to a second drive shaft. The counterrotatable booster compressor assembly includes a first compressor blade row connected to the first drive shaft, a plurality of fan shaft extensions connected to the second drive shaft for driving the second fan blade row, and at least one compressor blade integral with each fan shaft extension so as to form a second compressor blade row interdigitated with the first compressor blade row.

Abstract: A counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row axially spaced from the first fan blade row and connected to a second drive shaft. The counterrotatable booster compressor assembly includes a first compressor blade row connected to the first drive shaft, a plurality of fan shaft extensions connected to the second drive shaft for driving the second fan blade row, and at least one compressor blade integral with each fan shaft extension so as to form a second compressor blade row interdigitated with the first compressor blade row.

Abstract: A composite article, for example a blading member of a gas turbine engine, comprising a plurality of stacked layers of reinforcing fibers bonded together with a matrix resin is provided with enhanced resistance to impact cracking, material loss and/or delamination though use of a matrix resin including properties comprising a tensile strain property of at least 5% and a K1c toughness of at least about 850 psi·inch1/2. A method for making such a composite article with such resin comprises providing the layers of reinforcing fibers in a substantially dry, unimpregnated condition. The dry layers are stacked as a preform in a mold cavity and impregnated with the resin to wet and impregnate the dry layers of the preform. Then the resin is cured as a matrix about the fibers and the stacked layers.

Abstract: A fiber reinforced composite article is made by providing a plurality of layers of first, substantially dry, unimpregnated reinforcing fibers, sometimes called in-plane fibers. Such layers are stacked into a preform of a stack of layers. While in the dry, unimpregnated condition, a plurality of spaced apart second reinforcing members are inserted into the preform at an angle, for example transversely, to the stack of layers. In this condition, the preform is impregnated with a matrix about the first reinforcing fibers and the second reinforcing members. The article product comprises the plurality of stacked layers of the first reinforcing fibers and the plurality of the spaced apart second reinforcing members disposed beside or adjacent the first reinforcing fibers, with a substantially solid matrix disposed about the reinforcing fibers and members.

Abstract: A fiber reinforced composite article is made by providing a plurality of layers of first, substantially dry, unimpregnated reinforcing fibers, sometimes called in-plane fibers. Such layers are stacked into a preform of a stack of layers. While in the dry, unimpregnated condition, a plurality of spaced apart second reinforcing members are inserted into the preform at an angle, for example transversely, to the stack of layers. In this condition, the preform is impregnated with a matrix about the first reinforcing fibers and the second reinforcing members. The article product comprises the plurality of stacked layers of the first reinforcing fibers and the plurality of the spaced apart second reinforcing members disposed beside or adjacent the first reinforcing fibers, with a substantially solid matrix disposed about the reinforcing fibers and members.