A method for digitally designing a support with the shape of a fibrous blank obtained by three-dimensional weaving intended to form a fibrous preform of a turbine engine blade or propeller after shaping and compaction in a mold, includes providing a set of points representative of a face of the fibrous blank, the face being intended to form the root of the blade or the propeller and a portion of an aerodynamic profile of the blade or the propeller, generating a web connecting the points of the set of points, and digitally designing the support including at least an imprint of the fibrous blank having the shape of the generated web.

An automated laser shock peening (LSP) process equipment system for an aero-engine blade, including: a base, where a loading and unloading manipulator, working manipulator, reverse engineering mechanism, coating apparatus, and LSP apparatus are disposed; the loading and unloading manipulator is configured to grab a blade and place it on the reverse engineering mechanism, which includes a reverse engineering instrument and controller that are connected, the instrument can generate three-dimensional digital data of the blade, and the controller generates a working path for coating and LSP according to the data, and transmits the path to the working manipulator; the loading and unloading manipulator places the blade into the pallet, and the working manipulator drives the blade to a corresponding position according to the path. Independent locating and clamping systems of the pallet and the blade and the pallet and the manipulator fix a position of the blade relative to the manipulator.

This invention relates to a wind turbine blade component, a method of manufacturing such a wind turbine blade component and a wind turbine blade comprising the wind turbine blade component. The wind turbine blade component comprising a stack of layers arranged in a first group and in a second group, wherein the layers of each group has the same width. The layers of each group is continuously offset in an edgewise direction to form a tapered edge profile. The first group of layers may be arranged relative to the second group, or in an alternating order. The layers of the first group may further have a first length which is greater than a second length of the layers of the second group.

The present invention relates to a blade (7) comprising: —a composite material structure (17), —a blade root fastening portion (9) further comprising a shoulder (10) extending into the recess from the wall—a base (18) arranged in the recess and comprising a support member configured to abut against the shoulder (10) of the blade root fastening portion (9) and a passage (39) formed in the support member, the sections (23) of the blade root portion (22) of the composite material structure extending through the passage (39), and—a blocking part (19) arranged in the recess between the two sections (23) of the blade root portion (22) such that each section of the blade root portion (23) is pressed against the support member by the blocking part (19).

Disclosed herein is an article comprising a first group of plies having a number of plies N.sub.1 each having unidirectional tows oriented in a first direction β.sub.1 and a second group of plies having a number of plies N.sub.2 each having unidirectional tows oriented in a second direction β.sub.2; where β.sub.1 is not equal to β.sub.2; wherein N.sub.1 and N.sub.2 are both integer numbers. At least one of the first group of plies or the second group of plies has at least one tow of different thickness from another tow, has a different tow spacing from another tow spacing, or a combination thereof.

A method to design the kits and layup the reinforcement layers and core using projection system, comprising a mold having a contoured surface; a layup projection generator which: defines a plurality of mold sections; identifies the dimensions and location for a plurality of layup segments. A model-based calibration method for alignment of laser projection system is provided in which mold features are drawn digitally, incorporated into the plug(s) which form the wind turbine blade mold, and transferred into the mold. The mold also includes reflective targets which are keyed to the molded geometry wherein their position is calculated from the 3D model. This method ensures the precision level required from projection system to effectively assist with fabrication of wind turbine blades. In this method, digital location of reflectors is utilized to compensate for the mold deformations.

Fan or propeller vane (1) for an aircraft turbomachine, the vane being made from a composite material and comprising a blade (2) and a base (3), the base being formed by a longitudinal end (41) of a spar (4) which is formed by a fibrous reinforcement formed from threads woven in three dimensions and a portion (42) of which extends inside the blade (2), the blade (2) having an aerodynamic profile which is defined by a skin (5) which is formed by woven threads and which surrounds the portion of the spar, the spar (4) and the skin (5) being embedded in a polymerised resin, characterised in that the portion (42) of the spar comprises projecting longitudinal stiffening members (6) which together delimit spaces (8) for receiving longitudinal inserts (7) which are formed from a honeycomb material.

An apparatus for securing first and second skins to a core in a composite rotor blade includes an elongated member configured to be installed through a passage in the core of the composite rotor blade. The elongated member has a first end configured to be attached to an outer surface of the first skin and a second end configured to be attached to an outer surface of the second skin. The apparatus also includes a first patch configured to adhere the first end to the outer surface of the first skin, and a second patch configured to adhere the second end to the outer surface of the second skin such the elongated member extends from the outer surfaces of the first and second skins through the passage in the core.

The present invention relates to a blade comprising: - a structure made of composite material; - a blade root attachment part comprising a wall delimiting a cavity, a first opening formed in the wall and a second opening located under the blade root portion, the structure made of composite material extending through the first opening; - two locking parts configured to axially abut against a shoulder of the attachment part and to bear against the blade root portion; and - a cover for compressing the blade root portion against the locking parts.

A method of fabricating a paddlewheel for a flow meter is provided. The method can include providing an inner part of the paddlewheel. The method can also include inserting a plurality of magnets in the inner part of the paddlewheel. The method can also include overmolding an outer part of the paddlewheel over the inner part of the paddlewheel.