Provided is a helical strake set to reduce vortex induced vibrations of a tower, intended to be transported unassembled in a container, including a plurality of identical attachable segments, wherein each segment includes a main body of hollow pyramidal configuration including a wide polygonal end a narrow polygonal end and a narrow polygonal portion firmly attached to the narrow polygonal end, and each segment further including a cap including a wide polygonal portion able to fit in the wide polygonal end by a fastening element, wherein all main bodies and caps are able to be piled in one into another in a container yielding a significant reduction in seaborn transport volume and later assembled on site to reduce vortex induced vibrations of a tower.

A seal system for a gas turbine engine includes a ceramic matrix composite (CMC) seal arc segment and a carrier supporting the CMC seal arc segment. The CMC seal arc segment defines radially inner and outer sides and has an abradable layer disposed on the radially outer side. There is a cooling cavity radially between the carrier and the abradable layer. The carrier includes a ridge that projects into a groove in the abradable layer and provides a labyrinth seal that partitions the cooling cavity into sub-cavities.

A wind turbine blade includes a first blade section and a second blade section configured to be coupled together at a joint interface. The blade further includes a connection joint for coupling the first and second blade sections together. The connection joint includes a plurality of connecting elements integrated into the first and second blade sections at the first and second blade interfaces. The connection joint further includes cross pins and fasteners for making the connection. A method of making a wind turbine blade section and a wind turbine blade made from such sections are also disclosed.

A diffuser component for a gas turbine is provided, where a fluid flow in the direction of a combustion chamber of the gas turbine can be slowed down by the diffuser component, and a flow cross-section of the diffuser component, which is defined by a diffuser wall is widened to do so. The diffuser wall is at least locally braced, in that at least one stiffening element with a lattice-type structure is provided on the diffuser wall.

A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform has a gas path side that supports the radially outer end of the at least one airfoil and a non-gas path side. A hook is supported by the platform and has an anti-rotation surface that faces in a circumferential direction. A conical surface is spaced axially forward of a base portion of the hook. A triangular base surface intersects the anti-rotation surface and is spaced radially outward from the conical surface.

A system for capturing fluid energy has a blade shaft coupled to a gear assembly and a blade assembly. The blade assembly has a rod arm and a blade having a front surface and a blade plane, the blade fixedly coupled substantially normal to the rod arm. A limiter coupling has a limiter coupling axis and is coupled to the blade such that the limiter coupling axis is substantially parallel to the front surface and perpendicular to the rod arm. A horizontal limiter restricts the limiter coupling to a range of motion substantially along a first movement axis perpendicular to the limiter coupling axis and substantially perpendicular to the blade shaft. The blade assembly interacts with a fluid flow to transmit fluid energy from the fluid flow to the blade shaft to impart rotational energy to the gear assembly.

A rotor blade assembly for a wind turbine. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a blade tip and a blade root. The rotor blade assembly also includes at least one noise reducer secured at the trailing edge. The noise reducer(s) includes at least one serration having a base portion and at least one side edge feature extending from the base portion. Further, the base portion extends along a first plane. The side edge feature(s) extends out of the first plane so as to reduce vortices generated by the serration(s).

A method for assembling a shear web assembly of a wind turbine includes providing at least one spar cap. The method also includes forming a spar connecting member of a thermoplastic material via additive manufacturing. Further, the method includes securing the spar connecting member to the spar cap. Moreover, the method includes providing a shear web, forming a web connecting member of a thermoplastic material via additive manufacturing, and securing the web connecting member at a first end of the shear web. In addition, the method includes interconnecting the web connecting member and the spar connecting member at a joint. Thus, the method further includes heating the joint to secure the web connecting member and the spar connecting member together.

A mountable wing tip device (102) for mounting on a rotor blade of a wind turbine is disclosed which comprises a forward extremity (106) and at least two rearward extremities (108A, 108B, 112), wherein the forward extremity (106) and the at least two rearward extremities (108A, 108B, 112) are triangularly arranged, a leading edge region extending between the forward extremity (106) and the at least two rearward extremities (108A, 108B, 112), and a trailing edge region extending between the rearward extremities (108A, 108B, 112), a root region (113) at which the wing tip device (102) is mountable on an end of the rotor blade, wherein the root region (113) is positioned between the leading edge region and the trailing edge region.

A method includes providing a ceramic matrix composite (CMC) seal arc segment that has radially inner and outer sides, attaching an abradable layer on the radially outer side of the CMC seal arc segment, providing a carrier to support the CMC seal arc segment, the carrier including a ridge, and sliding the CMC seal arc segment relative to the carrier such that during the sliding the ridge cuts a groove into the abradable layer, the ridge remaining disposed in the groove to thereby provide a labyrinth seal that partitions the cooling cavity between the carrier and the CMC seal arc segment into sub-cavities.