A wind turbine blade assembly includes a first blade half and a second blade half fixed to the first blade half, defining a blade interior therebetween. The wind turbine blade assembly includes a shear web includes at least one aperture formed therein. The wind turbine blade assembly includes at least one bulkhead attached to the shear web, wherein the shear web and the at least one bulkhead are disposed in the blade interior. In some embodiments the at least one bulkhead includes a frame and a removable lid in order to expose the blade interior and the lid is returnably fixable to the at least one bulkhead. In some embodiments the first and second bulkheads include fluid conduits disposed therethrough and are spaced from one another to define first and second air circulation zones.

A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a vascular engineered lattice structure formed inside of the wall. The vascular engineered lattice structure includes at least one of a hollow vascular structure and a solid vascular structure configured to communicate fluid through the vascular engineered lattice structure.

The application describes methods of making composite bodies including fibre-reinforced composite material with carbon fibre reinforcement and also a metal-containing portion (4). The metal-containing portion (4) is formed by laying up metal reinforcement elements, such as tapes of titanium alloy, among the carbon fibre reinforcement tapes which make up the composite body. The proportion of metal reinforcement may increase progressively towards the surface and/or towards an edge (14) of the composite body. In an example, metal leading and trailing edges (14,15) of a fan blade (1) are integrally formed in this way.

A system and methods are provided for pre-stressing blade elements for a gas turbine engine. In one embodiment, a method includes rotating a blade element relative to an axis. The method may also include controlling rotational speed of the blade element to generate residual stress in the blade element. The method may also include rotating multiple blade elements and fan blade units to generate residual stress. Blade elements may be rotated to exceed a maximum operating speed of the blade element to 120% of the maximum operating speed of the blade element.

A lifting device for connecting two rotor blade segments of a wind turbine at the location of the wind turbine is adapted to move in the longitudinal direction of the rotor blade. The lifting device includes a frame structure, means for supporting and guiding the frame structure in relation to the rotor blade, means for lowering and/or lifting the frame structure in relation to the rotor blade, and means for lifting and/or lowering a rotor blade segment.

A system for locating airflow modifiers for installation on wind turbine rotor blades may generally include a plurality of airflow modifiers, with each airflow modifier including a base defining an outer profile that differs from the outer profiles of the remainder of the airflow modifiers. The system may also include a blade shell defining an exterior surface. The base of each airflow modifier may be configured to be coupled to the exterior surface of the blade shell. In addition, the system may include an installation template provided on the exterior surface of the blade shell. The installation template may define a different installation location for each of the airflow modifiers. Moreover, the installation template may include a geometric feature at each installation location that at least partially matches the outer profile of the airflow modifier configured to be installed at such installation location.

The invention relates to a compressible and expandable blade (2) for the rotor of a fluid pump (30) having at least two lamellae (3, 4, 5) which are disposed adjacently, are pivo table respectively relative to an axis of rotation (Ia) of the rotor and moveable relative to each other, and abut against each other in the expanded state of the blade such that they form together a continuous blade surface.

A turbine blade includes pressure and suction surfaces connected to define an interior through which coolant is passable. First and second pedestal arrays, each include pedestals respectively coupled to radially outboard portions of respective interior faces of one of the pressure and suction surfaces. The pedestals of the first pedestal array are separated from and directly opposed to pedestals of the second pedestal array by gaps respectively defined therebetween.

The invention relates to a compressible and expandable blade for the rotor of a fluid pump having at least two lamellae which are disposed adjacently, are pivotable respectively relative to an axis of rotation of the rotor and moveable relative to each other, and abut against each other in the expanded state of the blade such that they form together a continuous blade surface.

A multiple static vane component includes a plurality of airfoils each formed of ceramic matrix composite materials. Each of the airfoils are attached to an inner platform and an outer platform both formed of ceramic matrix composite materials. There is a plurality of individual parts forming the plurality of airfoils, the inner platform or the outer platform, bonded to each other with a braze joint. A gas turbine engine and a method are also disclosed.