A process for manufacturing a blade made of composite material for a turbomachine is provided. The blade includes an airfoil having a pressure side and a suction side which extend from a leading edge to a trailing edge of the airfoil. The blade further includes a metal sheath that extends along the leading edge of the airfoil. The process includes the steps of: a) placing a preform, made by three-dimensionally weaving fibers, in a mold, a polymerizable adhesive being inserted between the sheath and the edge of the preform; and b) injecting polymerizable resin into the mold to impregnate the preform so as to form the airfoil after solidifying, wherein the resin is injected within a time interval during which the adhesive reaches a freezing point.

Additive manufacturing techniques are used to achieve customized preforms for repair or manufacture of turbomachinery. A method of modifying a section of a product includes forming, a preform set to fit the section. A base material is selected with properties desired for the modification of the section. A binder is selected that vaporizes at a temperature below a melting point of the base material. The preform set is built by the selective application of the binder to the base material to achieve design dimensions of the section when the preform is joined to the section. The section is prepared for effecting the extent of modification and the preform is positioned on the section. The section and the preform are heated to substantially eliminate the binder from the preform and then thermally processed to harden the preform and to bond the preform to the section.

A system for use in servicing a machine. The system includes a tubular body including a longitudinal axis, a tip end, a dispensing nozzle defined at the tip end, and an interior channel in flow communication with the dispensing nozzle. The tubular body is configured to be flexible. An actuator is configured to selectively modify an orientation of the tubular body, and a reservoir is in flow communication with the interior channel. The reservoir is configured to supply a maintenance fluid to the tubular body for discharge from the dispensing nozzle.

A process of repairing a component includes identifying a void in a component; determining at least one approximate physical configuration of the void; inserting borescope into the component in order to view the void; providing a repair rod approximately equivalent to at least one of the least one approximate physical configuration of the void; inserting the repair rod into component; confirming insertion of the repair rod in the void; separating the repair rod to leave a repair plug in the void; and depositing braze paste over the repair plug in the void.

A movable carriage system for an aircraft element, such as an aeroplane engine, has a first movable module (10) and a second movable module (20). Each movable module has a frame (12, 22) equipped with at least three wheels, a lifting device adapted to be able to move said aircraft element at least in a vertical direction, and at least one link arm (16, 17) adapted to be able to secure together the frame of said first module and the frame of said second module and to allow data to be transferred between them. The movable modules are adapted to be able to be controlled in a mutually coordinated manner.

Embodiments of the present disclosure generally relate to protective coatings on various substrates including aerospace components and methods for depositing the protective coatings. In one or more embodiments, a method of forming a protective coating on an aerospace component includes forming an aluminum oxide layer on a surface of the aerospace component and depositing a boron nitride layer on or over the aluminum oxide layer during a vapor deposition process. In some examples, the method includes depositing a metal-containing catalytic layer on the aluminum oxide layer before depositing the boron nitride layer. The boron nitride layer can include hexagonal boron nitride (hBN).

A method of retrofitting a wind turbine having a tower and a first energy generating unit with a second energy generating unit. The method includes analyzing a first natural frequency of the tower relative to first rated operation frequencies of the tower having the second energy generating unit; when the first natural frequency lies within the first rated operation frequencies, modifying one or both the tower and the second energy generating unit so that the modified one or both the tower and the second energy generating unit have a second natural frequency and second rated operation frequencies that do not overlap; and replacing the first energy generating unit with the second energy generating unit.

A pump features a trimmed impeller having a trimmed impeller diameter that is less than a standard full-sized diameter of a standard full-sized impeller for a standard full-sized casing, and having a circumferential outer edge; and a modified standard full-sized casing having dimensions corresponding to the standard full-sized casing and configured to house the trimmed impeller for pumping a fluid, having an outer peripheral wall, and having an inner annular volute portion between the circumferential outer edge of the trimmed impeller and the outer peripheral wall configured with a volume of material deposited using an additive manufacturing process so as to fill in vacant space otherwise caused by the trimmed impeller diameter being less than the standard full-sized impeller diameter. The additive manufacturing process is a directed energy deposition.

A method of repairing a compressor outlet housing includes the steps of obtaining a damaged compressor outlet housing having a radially outer volute, a radially inwardly extending finger extending to an axially extending ledge, a radially inwardly extending web extending radially inwardly from the ledge, and a radially inner bearing support defining a bore. The method identifies a damaged section within at least one of the bearing support, the web, and the ledge, and removes at least the bearing support and the web to leave a remaining part. The method then inserts an insert having at least a replacement bearing support and a replacement web into the remaining part after the removal step. The method then welds the insert to the remaining part to provide a repaired compressor housing. A method of replacing a compressor outlet housing and a replacement compressor outlet housing are also disclosed.

A method for repairing a turbomachine air intake lip including a damaged area whose shape differs from the initial shape of the lip, includes identifying the damage; depositing a filler material on the damaged area so as to give it a shape identical to the initial shape; inspecting the shape of the lip; and inspecting the performed repair.