A method for manufacturing a blade structure includes providing the blade structure comprising an outer surface having an aerodynamic profile. The method also includes applying one or more shape memory alloys to the outer surface of the blade structure so as to form an outer protection layer on at least a portion of the blade structure. Moreover, the method includes securing the one or more shape memory alloys to the blade structure.

A rotor wind turbine blades with attached mantle peridotite panel available to capture CO.sub.2 in air while the blades are rotating powers by the wind. Due to presence of Ca.sup.+ and Mg.sup.+ in the mantle peridotite glass cell, the panel composed of glass cells can conduct sequestration of carbon dioxide in air and the product of CO.sub.2 sequestration is mineralized carbon. Another means of CO.sub.2 sequestration in air is by placing the mantle peridotite panel at the top of the wing structure of plane and capture the CO.sub.2 while the plane is flying.

An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

An article includes a ceramic-based substrate and a barrier layer on the ceramic-based substrate. The barrier layer includes a matrix phase and gettering particles in the matrix phase. The gettering particles with an aspect ratio greater than one are aligned such that a maximum dimension of the gettering particles extends along an axis that is generally parallel to the substrate. The barrier layer includes a dispersion of diffusive particles in the matrix phase. A composite material and a method of applying a barrier layer to a substrate are also disclosed.

A method for manufacturing a planet gear or a sun gear of a gearbox of a wind turbine includes forming a base of the planet gear via at least one of casting or forging. The base of the planet gear includes an inner circumferential surface and an outer circumferential surface. Therefore, at least one of the inner circumferential surface or the outer circumferential surface of the planet gear includes a plurality of net or near-net gear teeth. The method also includes applying a coating material to at least a portion of the base of the gear and at least a portion of the plurality of gear teeth of the gear via an additive manufacturing process so as to increase a hardness of the portions of the base and the plurality of gear teeth that includes the coating material.

The disclosure relates to a method of manufacturing a fibre reinforced composite, wherein the surface of the fibre reinforced composite modified by using a laser radiation. In particular, the pre-treatment is performed before a bonding process. Time-consuming and dust generating grinding of the surface can be avoided.

An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

A wind turbine tower assembly device comprising a tower interface configured to be attached to a wind turbine tower during construction of the wind turbine tower, a nacelle interface for being attached to a part of a nacelle of a wind turbine and arranged to place the nacelle above a free end of a wind turbine tower which is attached to the tower interface; a lifting structure configured to move the nacelle interface relative to the tower interface to create a space between the free end of the wind turbine tower and the nacelle interface; a unit receiving structure configured to insert a tower unit into the space; and a tower assembly structure configured for joining the tower unit to the free end of the tower.

Disclosed is a leading edge protection element for a wind turbine blade, the leading edge protection element extending in a longitudinal direction between a first edge and a second edge and extending in a transverse direction between a third edge and a fourth edge, the leading edge protection element having a first surface and a second surface. The leading edge protection element comprising a film layer having a first film surface and a second film surface, the first film surface forming the first surface of the leading edge protection element, wherein the film layer comprises a metal material. The leading edge protection element comprising a rubber layer of a rubber material having a first rubber surface and a second rubber surface, the second rubber surface forming the second surface of the leading edge protection element, wherein the second film surface and the first rubber surface are bonded to each other.

A wind turbine blade includes: a metal receptor including a blade tip of the wind turbine blade; and a blade body portion connected to the metal receptor so as to be positioned on a blade-root side of the metal receptor, the blade body portion having a hollow structure and forming an airfoil shape in a blade tip region of the wind turbine blade with the metal receptor in a joint region to the metal receptor. As seen in a blade-thickness direction of the wind turbine blade, a tangent to a joint line between the metal receptor and the blade body portion at an intersection between the joint line and a leading edge of the wind turbine blade is inclined from a chordwise direction of the wind turbine blade.