A modular repair kit for repairing damaged pallet rack frames and a method of installation thereof which incudes modular elements that can be customized by mechanical process such as cutting, drilling and connecting, for example, by bolts, that avoids major modifications, such as welding, at the installation site. The modular repair kit utilizes a standard replacement post assembly that can be cut to fit into nearly any size gap that is created when the damaged portion of the pallet rack frame is removed. The remaining elements of the repair kit can then be customized to accommodate any size of the standard replacement post assembly.

A modular repair kit for repairing damaged pallet rack frames and a method of installation thereof which incudes modular elements that can be customized by mechanical process such as cutting, drilling and connecting, for example, by bolts, that avoids major modifications, such as welding, at the installation site. The modular repair kit utilizes a standard replacement post assembly that can be cut to fit into nearly any size gap that is created when the damaged portion of the pallet rack frame is removed. The remaining elements of the repair kit can then be customized to accommodate any size of the standard replacement post assembly.

A replacement tip section for a rotor blade, from which a legacy tip section was removed, includes a blade tip portion configured to be attached to an intermediate section of the rotor blade after removal of the legacy section. The intermediate section has a connection feature at an end of the intermediate section to which the blade tip portion is attachable. The replacement tip section includes a transition region configured to be attached to a forward end of the connection feature. The transition region is configured to form a leading edge of the rotor blade and extends from the blade tip portion to form an opening into which the intermediate section is attached. The transition region includes a first end having a first airfoil that conforms to the intermediate section airfoil at the connection feature, and a second end having a second airfoil that conforms to the blade tip portion.

Method of lining a tubular structure with a plastics liner pipe comprising the steps of: temporarily reducing an outside diameter of the liner pipe by passing the liner pipe through a roller system; cooling the liner pipe once its outside diameter has been reduced and applying a thermal restraint; transporting the liner pipe to an installation site remote from the roller system; removing said thermal restraint; and installing the liner pipe in said tubular structure at said installation site.

A method of repairing a damaged spar cap of a wind turbine blade of a wind turbine, the damaged spar cap including carbon fiber-reinforced plastic and the method having the steps of: removing a damaged carbon fiber-reinforced plastic part from the damaged spar cap to obtain a corresponding recess in the damaged spar cap, applying an adhesive to the recess, and fitting at least one patch including carbon fiber-reinforced plastic into the recess, is provided.

A repair axial bearing system includes an arcuate rail coupled to a support, one or more bolts protruding upward from a raised portion coupled to a supported member, and a lever plate including at least one low friction bearing pad mounted in the lever plate. A first new bearing surface is formed on the arcuate rail. A second new bearing surface is formed on the at least one low friction bearing pad. The one or more bolts are tensioned with bolt tensioners to press the lever plate against the raised portion. The axial bearing system can include a hydraulic cylinder to slide the second bearing surface over the first bearing surface. The repair axial bearing system can be used to supplant a damaged axial bearing positioned between an FPSO and a turret.

An acoustic panel (200) for an aircraft nacelle (100) may comprise a perforated first skin (220), a second skin (230), and a core (210) sandwiched between them. A damaged portion of the perforated first skin may be removed. A fiberglass ply (510) may be coupled to the acoustic panel. A pressure differential may cause the fiberglass ply to form dimples (515) within the perforations (325) of the first skin. The fiberglass ply may be used as a template to drill holes in a replacement patch (400).

Methods for repairing composite cylindrical components are provided. One exemplary method for repairing a cylindrical component defining an axial direction, a radial direction, and a circumferential direction includes removing a damaged region of the cylindrical component. A flange extending from a cylindrical body of the cylindrical component is included in the damaged region. One or more arc segments that extend along the circumferential direction are connected with the existing cylindrical component. At least one of the arc segments includes a prefabricated flange. One or more plies are laid up to connect the arc segments with the existing cylindrical component to repair the damaged region of the cylindrical body and the prefabricated flange formed integrally with one of the arc segments replaces the damaged portion of the flange. Repaired cylindrical components are also provided.

An acoustic panel (200) for an aircraft nacelle (100) may comprise a perforated first skin (220), a second skin (230), and a core (210) sandwiched between them. A damaged portion of the perforated first skin may be removed. A fiberglass ply (510) may be coupled to the acoustic panel. A pressure differential may cause the fiberglass ply to form dimples (515) within the perforations (325) of the first skin. The fiberglass ply may be used as a template to drill holes in a replacement patch (400).

An apparatus and method for servicing a combustion liner in a combustion case of a turbine is provided. The apparatus includes an elongated bar having a handle at one end and a force applying member at an opposing end of the elongated bar. An attachment member is configured for attachment to a flange of the combustion case. The attachment member is also configured for pivotal attachment to the elongated bar. The apparatus is configured to apply a radially outward force on a downstream portion of the combustion liner when a radially inward force is applied to the handle.