The present disclosure is directed to a root assembly for a rotor blade of a wind turbine and methods of manufacturing same. The root assembly includes a blade root section having an inner sidewall surface and an outer sidewall surface separated by a radial gap, a plurality of root inserts spaced circumferentially within the radial gap, and a plurality of spacers configured between one or more of the root inserts. Further, each of the root inserts includes at least one bushing surrounded by a pre-cured or pre-consolidated composite material. In addition, the spacers are constructed of a pre-cured or pre-consolidated composite material.

A fan slider for use in a fan assembly to push a fan blade radially outward of a rotating axis of the gas turbine engine. The fan slider may include a fan slider body coated with a nanocrystalline metallic coating and a slider spring.

A flow straightening vane made of composite materials includes a core made up of three-dimensional woven textile rods which core is surrounded by a textile covering, this core and this covering being consolidated using a thermoset resin.

A blocker door assembly for use in a gas turbine engine includes a facesheet including a plurality of openings to facilitate noise attenuation and a body portion coupled to the facesheet. The body portion includes a backsheet integrally formed with a honeycomb core, wherein the body portion is molded from a thermoplastic material.

An impeller for use with centrifugal compressors or pumps is provided and described along with methods for making such multi-component polymeric articles such as open or closed impellers and other assembled molded articles, which may optionally include openings therein. The impeller includes a composite comprising a matrix material selected from at least one thermoplastic polymer or at least one thermosetting polymer; and at least one continuous reinforcing fiber. The impeller includes at least one first flange comprising the composite, the first flange having an exterior surface and an interior surface, the first flange defining a first opening extending longitudinally therethrough; and at least one rib having a first end and a second end, the at least one rib positioned such that its first end engages the at least one first flange. Ring members and additional, second flanges, and optionally outer banding rings may be provided in various designs. The multi-component polymeric composite articles are formed of composite parts that are first molded, then assembled, positioned in a mold and remolded, optionally using removable cores for retaining openings within the remolded structures.

The present disclosure is directed to a root assembly for a rotor blade of a wind turbine and methods of manufacturing same. The root assembly includes a blade root section having an inner sidewall surface and an outer sidewall surface separated by a radial gap, a plurality of root inserts spaced circumferentially within the radial gap, and a plurality of spacers configured between one or more of the root inserts. Further, each of the root inserts includes at least one bore hole surrounded by a pre-cured or pre-consolidated composite material. In addition, the pultruded spacers are constructed of a pre-cured or pre-consolidated composite material.

The present disclosure is directed to a root assembly for a rotor blade of a wind turbine and methods of manufacturing same. The root assembly includes a blade root section having an inner sidewall surface and an outer sidewall surface separated by a radial gap, a plurality of root inserts spaced circumferentially within the radial gap, and a plurality of spacers configured between one or more of the root inserts. Further, each of the root inserts includes at least one bushing surrounded by a pre-cured or pre-consolidated composite material. In addition, the spacers are constructed of a pre-cured or pre-consolidated composite material.

A gas turbine engine includes a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement, and defining an engine centerline extending between a forward direction and an aft direction. A disk includes a slot for mounting a composite airfoil to the disk. An axial retainer couples to the disk and secures the composite airfoil to the disk. A compliant portion positioned at the composite airfoil abuts the composite airfoil during operation of the gas turbine engine to secure the composite airfoil to the disk.