183results about "Vanes" patented technology

A stacked lamination endplate for a rotor that includes a number of adjacent laminations, stacked one on top of another, wherein each lamination has an identical shape, the shape having a central region, symmetric about a center axis, and a number of spokes, each spoke emanating radially outward from the central region, where each spoke includes a through-hole at its distal end, and wherein the laminations are stacked one on top of another and aligned, enabling, for each spoke, a bolt to be inserted through a corresponding through-hole of each lamination.

A tool for curing and bonding a honeycomb stack with void filler. The tool has a first tool piece with a cavity for receiving layers of unfilled honeycomb material and a second tool piece with a cavity for receiving at least one layer of void-filled honeycomb. The tool also has a compression seal arrangement that creates gas-tight seals between the first tool piece, second tool piece, and a barrier layer positioned between them, with a further seal covering the cavity of the first tool piece to form a gas-tight sealed volume including the first cavity, a pressure plate to cover the cavity of the second tool piece to apply pressure to the void-filled honeycomb, with a further seal to cover the pressure plate to form a gas-tight sealed volume including the second cavity.

A method for manufacturing a composite material revolution part for a propulsion assembly includes making a fibrous preform on a mandrel having a profile corresponding to that of the part to be manufactured, and densifying the fibrous preform by a matrix. Making the fibrous preform includes forming a strip-shaped fibrous blank including at least one layer of continuous fibers and at least one layer of discontinuous fibers, the fibrous blank being shaped on the mandrel, the layer of continuous fibers of the fibrous blank extending at least over a complete turn around the mandrel.

Transition of variable thicknesses of composite material laminates of a modular blade when the thickness varies by 50-400% and which smooths the centroid distribution, the centroid being represented as a function of the thickness and material of the laminate with respect to the corresponding radius of the blade. For this purpose, a non-structural material (10) is incorporated disposed on the lower part corresponding to the face of a mould (5) or the aerodynamic surface (11) is modified.

Sandwich panels 174, 176, 178 are produced by simultaneously and continuously applying outer layers 122, 124 to the top 108 and bottom 110 faces of an elongate thermoplastic foam panel 102. The outer

A method of manufacturing a sail body (3) for forming part of a wind power assisted propulsion device (4) includes laying a first fabric (14) formed from a first fiber on a mold (16) defining the shape of a part (2) of the sail body (3), and laying a plurality of strips (22) formed from a second fiber on the surface of the first fabric (14) such that at least a part of the second fiber extends longitudinally along the sail body (3).

A composite panel assembly includes a first composite panel having a first base structure. The first base structure includes a first face of the first base structure and a second face of the first base structure. The first composite panel further includes a first composite sheet of the first composite panel and a second composite sheet of the first composite panel. The first composite sheet of the first composite panel is bonded to the first face of the first base structure and a second composite sheet of the first composite panel is bonded to the second face of the first base structure. An interlocking member is defined in the first base structure. The composite panel assembly further includes a component having a portion that extends into the interlocking member, such that an interlocking mechanical joint is formed between the first composite panel and the component.

Systems and methods are provided for protecting aerodynamic structures, such as wind turbine blades, rotor blades, aerodynamic aircraft structures, etc. Long fiber reinforced composite materials with helicoidal structures having materials aligned with graded hardness and stiffness are used to develop efficient, highly tunable leading edge protection (LEP) solutions that have longer durability than conventional solutions, while resulting in a lighter, and optionally more environmentally sustainable solution. At least a portion of the multiple plies are helicoidally arranged relative to one another to tailor the stress wave propagation velocity of the aerodynamic blade and provide the aerodynamic blade's load-bearing strength.

An apparatus is provided for an aircraft propulsion system (20). This apparatus includes an acoustic panel (72) and a mount (84). The acoustic panel (72) includes a perforated face skin (88), a back skin (89), a perforated intermediate layer (90), a first cellular core and a second cellular core. The first cellular core includes a first section (27A) and a second section (27A). The first section (27A) is between and is connected to the perforated face skin (88) and the perforated intermediate layer (90). The second section (27A) is between and is connected to the perforated face skin (88) and the back skin (89). The second cellular core is between and is connected to the perforated intermediate layer (90) and the back skin. The mount is attached to the back skin along the second section.

A structural shell comprises a basalt fibre-reinforced material, wherein the basalt fibre-reinforced material comprises a polymer material, the polymer material being capable of at least partially the

The present invention relates to a covering for rotor blades comprising a fabric and a protective top layer, the covering having a weight of up to 800 g / m2, the covering having an elongation at break in both a warp and a weft direction of at least 20%, wherein the elongation at break is determined according to ISO 13934-1:2013, wherein the protective top layer is a film, and wherein the protective top layer is laminated to the fabric. The invention also relates to a use of the covering for covering rotor blades of a wind turbine.

A ceramic composite component (2200) includes a ceramic core structure (2204) having a plurality of hollow cells (260) defined by a plurality of walls (262) extending from a first side (2210) of the ceramic core structure (2204) to a second side (2212) of the ceramic core structure (2204), the second side (2212) opposite the first side (2210). A ceramic matrix composite (CMC) structure (2206) is coupled to the ceramic core structure (2204). The CMC structure (2206) comprises a plurality of CMC plies (302, 402, 402A, 402B) defined by a first side (2214) of the CMC structure (2206) and a second side (2216) of the CMC structure (2206) opposite the first side (2214) of the CMC structure (2206). A first CMC face sheet (2208, 2208A) is bonded to the first side (2210) of the ceramic core structure (2204) and the first side (2214) of the CMC structure (2206). A second CMC face sheet (2208, 2208B) is bonded to the second side (2212) of the ceramic core structure (2204) and the second side (2216) of the CMC structure (2206).

The present invention relates to a fibrous structure (900) for making a part (90) of composite material, the fibrous structure (900) comprising a stack of several layers of fibers (910, 912, 914), and a reinforcing element (920) situated between a lower layer (912) and an upper layer (914), wherein the reinforcing element (920) comprises: - a support (922) interposed between the lower (912) and upper (914) layers and having a lower face (922a) covered by the lower layer (912), and an upper face (922b) covered by the upper layer (914), and - strands (924) projecting from the lower (922a) and upper (922b) faces of the support (922) and engaged respectively in the lower (912) and upper (914) layers. Figure for the abstract: Fig. 4

A method for manufacturing a fan blade or fan component of composite material, the method comprising using a permanent core having a plurality of interconnected surface channels on a surface thereof to promote resin flow; forming a reinforcing fabric envelope over the permanent core; a mold is closed over a permanent core of the reinforcing fabric encapsulant to form a mold cavity between a surface of the permanent core and an inner surface of the closed mold, and resin is injected into an opening of the closed mold to allow the resin to fill the entire mold cavity via surface channels of the permanent core to allow the resin to cure, and releasing the fan blade or fan component from the mold; wherein the injection of resin is accomplished with or without a positive pressure system, and wherein the permanent core is not removed from the fan blade or fan component prior to use.

To disclose use of a low Tg compatible resin as an adhesive layer for welding a thermoplastic composite structure to a thermoplastic or thermoset structure.SOLUTION: The present invention is especially suitable for welding large parts such as wind turbine halves and spar caps. A useful thermoplastic composite is one formed by infusion and curing of long fibers by a reactive acrylic liquid resin-based material such as an ELIUM (R) resin-based material from Arkema.SELECTED DRAWING: None

A ceramic matrix composite includes at least one ply (110) of ceramic fibers (112) and a ceramic matrix material (116) deposited on the ceramic fibers (112). A fiber volume fraction is between about 35-45% and an areal weight of the fibers is between about 150-450 g / m2. A method of fabricating a ceramic matrix composite component (108) is also disclosed.

The invention relates to a method for manufacturing a honeycomb structure for a part, in particular for an aircraft turbomachine, this honeycomb structure comprising a grid of cells (86), a first skin (82) of composite material covering the grid (86), and optionally a second skin (84) of composite material having the grid (86) positioned between the first and second skins, the method being characterized in that it comprises the steps of: (a) creating a first stack (820) of fiber layers by draping so as to form the first skin, (b) depositing at least one first interface film (800) by draping onto the first skin, (c) positioning the grid of cells (86) on the first interface film, (d) optionally depositing at least one second interface film (802) by draping onto the grid (86), and (e) optionally creating a second stack (840) of fiber layers by draping so as to form the second skin.Figure for the abbreviation: Figure 11.

The present invention relates to a spar cap for a wind turbine blade and a method for manufacturing said spar cap. The spar cap comprises: a plurality of reinforcing fibre layers comprising unidirectionally oriented reinforcement fibres, wherein the plurality of reinforcing fibre layers are arranged such that the spar cap tapers in thickness towards a first longitudinal end, and a number of first fibre skin layers arranged on a first surface of the plurality of reinforcing fibre layers, and a number of second fibre skin layers arranged on a second surface of the plurality of reinforcing fibre layers, such that the plurality of reinforcing fibre layers are arranged between the number of first fibre skin layers and the number of second fibre skin layers. The number of first fibre skin layers and the number of second fibre skin layers extend beyond the plurality of reinforcing fibre layers towards the first longitudinal end of the spar cap, and the first longitudinal end of the spar cap is serrated along a transverse direction, forming a first serrated section.

The present application discloses a composite protective layer, a preparation method thereof, and a protection device for a wind turbine blade. The composite protective layer includes a stacked first modified ultra-high molecular weight polyethylene layer and a modified polyethylene layer. By providing the stacked first modified ultra-high molecular weight polyethylene layer and the modified polyethylene layer, the first modified ultra-high molecular weight polyethylene layer is used to accelerate heat transfer, and its ultra-weather resistance and high impact resistance can resist natural damage for a long time. The modified polyethylene layer transfers heat to assist in removing ice and snow on the outer layer. The composite protective layer obtained by the cooperation of each protective layer is light in weight, soft and bendable, can be attached to the blade surface, will not bring excessive weight, does not affect the structural safety, and also has good de-icing efficiency and mechanical property retention rate.

For the production of components made of fiber-reinforced composites, in particular for the production of rotor blade belts, a unidirectional non-crimp fabric made of glass fiber rovings is provided, the non-crimp fabric having a first stabilizing layer on the underside thereof and a second stabilizing layer on the upper side thereof, which layers are sewn together by pillar stitching.

The present disclosure provides a defect-detectable fiber fabric, including a plurality of bunches of fibers and a plurality of braided threads configured to respectively fix together fibers of each bunch of fibers. The plurality of braided threads include first braided threads each having a color different from a color of any of the plurality of bunches of fibers, and a respective distance between every two adjacent first braided threads is configured to make wrinkle defects that could be formed in fabric layers detectable. After the curing and molding, the positions of the defects and the layer(s) where the defects are formed can be determined according to the states of the first braided threads.

A composite blade (10) is provided with: an airfoil part (11); a blade root part (12); and main laminates (32) and sub-laminates (33) each of which include a composite material layer of a fiber-reinforced resin and which are alternately laminated in the blade root part (12). A lateral surface (12a) of the blade root part (12) includes a contact-enabled surface (13) capable of making contact with an attachment groove (50). The main laminates (32) extend from the blade root part (12) to the airfoil part (11) so as to merge together before reaching the airfoil part (11). The sub-laminates (33) extend from the blade root part (12) to respective merging points of the main laminates (32). The contact surface (13) has a first edge part (14) and a second edge part (15). Inside the blade root part (12), a first section (41) positioned around the first edge part (14) and a second section (42) positioned between the first section (41) and a center surface (5) of the blade root part (12) are set. In the first section (41), the end parts of the sub-laminates (33) are not positioned. In at least a part of the second section (42), respective parts of the main laminates (32) and the sub-laminates (33) are alternately positioned along the blade thickness direction.

The present invention provides a reinforced fiber sheet exhibiting a stable shape and favorable bulking properties, a method for manufacturing same, and a fiber-reinforced resin molded body. The reinforced fiber sheet according to the present invention comprises a plurality of reinforced fiber bundles that are arranged in one direction, wherein first and second reinforced fiber bundle layers, in which there is no direct binding force between reinforced fiber bundles within a layer, are disposed so as to have mutually distinct fiber orientations, and are integrally formed by being fastened together using fastening elements, satisfying conditions (i) and (ii). (i) Fastening surfaces of the first and second reinforced fiber bundle layers have fastening sections that include at least one fastening element, and an average surface area S1 of 100 mm2. (ii) In the fastening sections, the surface area ratio of the fastening elements to the fastening section is 0.1% to 80%, inclusive.

The present disclosure provides a defect-detectable fiber fabric, including a plurality of bunches of fibers and a plurality of braided threads configured to respectively fix together fibers of each bunch of fibers. The plurality of braided threads include first braided threads each having a color different from a color of any of the plurality of bunches of fibers, and a respective distance between every two adjacent first braided threads is configured to make wrinkle defects formed in fabric layers detectable. By using the fiber fabric including the high-density distributed first braided threads to manufacture blades of wind turbines and other products, the wrinkle defects can be identified in time according to the states of the first braided threads in the process of laying the fiber fabric on a large area. After the curing and molding, the positions of the defects and the layer(s) where the defects are formed can be determined according to the states of the first braided threads, thereby preventing destructive detection or maintenance.

A lightweight avalanche shovel includes a blade, a shaft and a handle, all of which are made at least in part from carbon fibers. The overall shovel weight is lower than typical avalanche shovels while maintaining UIAA certification standards. For example, the shovel weight may be approximately 300 g.

A composite panel assembly includes a first composite panel having a first core structure. The first core structure includes a first core structure first face and a first core structure second face. The first composite panel further includes a first composite panel first composite sheet and a first composite panel second composite sheet. The first composite panel first composite sheet bonded to the first core structure first face and a first composite panel second composite sheet bonded to the first core structure second face. An interlocking feature is defined in the first core structure. The composite panel assembly further includes a component having a portion that extends into the interlocking feature such that an interlocking mechanical joint is formed between the first composite panel and the component.

The invention relates to a method for manufacturing a cellular structure for a part, in particular of an aircraft turbine engine, this cellular structure comprising an array of cells (86), a first skin (82) made of composite material covering the array (86), and optionally a second skin (84) made of composite material having the array (86) between the first and second skins, the method being characterized in that it comprises the steps consisting in: (a) producing a first stack (820) of layers of fibres by lay-up so as to form the first skin, (b) depositing at least one first interface film (800) by lay-up on the first skin, (c) positioning the array of cells (86) on the first interface film, (d) optionally depositing at least one second interface film (802) by lay-up on the array (86), and (e) optionally producing a second stack (840) of layers of fibres by lay-up so as to form the second skin.