114results about "Vanes" patented technology

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 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.

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.

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.

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.

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.

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.

According to the present invention there is provided a method of assessing constituent components of a composite structure (10). The composite structure (10) comprises a plurality of layers of fibre material (12) embedded in a thermoset epoxy matrix having a cross-linked network structure. The method comprises exposing the composite structure to a treatment fluid (22) to at least partially degrade the thermoset epoxy matrix. The treatment fluid (22) comprises formic acid and / or acetic acid. The method further comprises temporarily restraining the composite structure during exposure to the treatment fluid to maintain the order and / or orientation and / or number of the layers of fibre material. Further, the method includes separating one or more layers of fibre material from one or more other layers of fibre material to thereby assess the constituent components of the composite structure (10).

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 unidirectional laminate comprising a fiber-reinforced composite material having a principal relaxation temperature (Tα) in the range of approximately 110°C to 140°C. The composite material comprises multiple unidirectional reinforcing fibers coated with an adhesive composition and a matrix resin. The unidirectional laminate has a tensile modulus of at least 450 GPa when the fiber volume fraction is greater than or equal to 50% and fatigue mechanical properties of at least 450 MPa at 1 mm cycles, measured according to ASTM E 739-91.

The invention relates to a component (11) for an aircraft turbomachine, the component (11) comprising:-a body (12) comprising a composite material comprising an organic matrix and fibres embedded in the matrix, and-a fire barrier (13) arranged on at least one surface of the body (12), characterized in that the body (12) comprises at least one surface of the body (12); the fire barrier (13) is multilayer and comprises:-a perforated first layer (14) comprising glass fibers, and-a second layer (15) comprising fibers different from the glass fibers, the first layer (14) being located between the body (12) and the second layer (15).

The present application relates to the field of wind power generation, specifically to a wireless induction heating fan blade and a preparation method, comprising a blade base layer, a wind power generation column, a guide rail and a transmitting induction coil, the blade base layer is sequentially provided with a wireless induction layer and an electric heating functional layer from inside to outside, the guide rail is embedded in the wind power generation column, and the transmitting induction coil is arranged inside.The wireless induction heating fan blade is applied to the fan blade, and the transmitting induction coil is acted on by an external wireless power supply transmitting device, an electrode electrically connects the transmitting induction coil and the electric heating functional layer, the wireless power supply electromagnetic induction technology makes the electric heating functional layer heat, effectively solves the blade icing problem, reduces the fan blade load, the fan blade and the flexible electric heating functional film can be well attached, greatly reduces the influence on the fan operation aerodynamic characteristics, improves the wind energy utilization rate, increases the economic benefit of wind power generation, and the wireless induction transmitting guide rail and the wind power generation column are integrated, saving the space utilization.

The present invention relates to an orthotropic sandwich structure (1) with differentiated bending stiffnesses, comprising a first membrane (21) and a second membrane (22) spaced apart by a distance H, as well as a shearing structure (3) connecting them and made up of a plurality of shearing elements (4) each having a generatrix (G) of curvilinear length L. The ends (I1, I2) of the generatrix are positioned at a distance d1 from the first membrane (21) and at a distance d2 from the second membrane (22), respectively. According to the invention, the generatrix (G) has a curvilinear length L at least equal to 1.25*(H-(d1+d2)), and the straight line (D) passing respectively through the orthogonal projections (J1, J2) of the ends (I1, I2) on the membranes (21, 22) forms, with a direction (ZZ') perpendicular to the mean surface (Sm) of the shearing structure (3), an angle (B) at most equal to 45°.

A method for forming a composite article includes: mating a polymeric barrier (54) with a fiber scrim (52); applying a first layer (58) to a tool (400); applying the mated polymeric barrier (54) and fiber scrim (52) atop the first layer (58); and applying multiple further fiber layers (56) atop the mated polymeric barrier (54) and fiber scrim (52).

The present invention relates to a woven fabric for the manufacture of fibre reinforced composites having an area weight from 100 to 200 g / m2 which comprises unidirectional reinforcing fibres, carbon fibres and flow passages forming elements arranged in warp and / or weft direction, and, optionally additives. The flow passages forming elements are arranged transverse to the reinforcing fibres and the carbon fibres forming flow passages at the side of the flow passages forming elements. Moreover, the present invention relates to a vacuum induced resin infusion process for forming a fibre reinforced composite from such woven fabric as well as the fibre reinforced composite.

A molding material comprising: (a) a structural reinforcement layer comprising a fibrous reinforcing material, optionally combined with a second resin composition; and (b) a surface reinforcement layer for contacting a mold or tool surface, comprising a first nonwoven fibrous carrier combined with a first resin composition containing a rheology modifier and a curing agent, the first resin composition providing the outer mold or tool contact surface of the molding material. The molding material can be cured to form a molded article having a high-quality surface finish that requires minimal preparation before painting and / or application for its intended use. The molded article may be provided with a sacrificial discontinuity indicator means to aid in the uniform removal of a portion of the surface reinforcement layer of the molded article for a particular application.

The present invention relates to a variable-pitch vane (100) made of a composite material for an unducted fan of an aircraft, the vane comprising: a fibrous reinforcement formed as a single piece of three-dimensional fabric comprising an airfoil portion (102) and a root portion (104) forming a retaining bulb and intended to be connected to a variable-pitch mechanism (20), the three-dimensional weaving being carried out continuously between the root portion and the airfoil portion, the fibrous reinforcement defining an internal shaping cavity (111) formed by a separation (D1) extending inside the root portion and the blade portion, wherein a matrix densifies the fibrous reinforcement and reinforcing metal shells (105) are arranged around the root portion.

A fabric is described herein that includes a first fiber oriented in a first direction, a second fiber oriented in a second direction, and a stitching thread that maintains the first and second fibers in their respective orientations, where the second direction is different from the first direction, the first fiber includes glass fiber and / or carbon fiber, and the second fiber is a textured yarn.

The present invention relates to a sandwich panel comprising an upper top layer (UTL) comprising a polyarylene ether sulfone polymer and a fibrous reinforcing agent, a foam core layer (FCL) comprising a polyarylene ether sulfone polymer and a lower top layer (LTL) comprising a polyarylene ether sulfone polymer and a fibrous reinforcing agent, wherein the upper top layer (UTL) is joined to the foam core layer (FCL) via a first film (F1) comprising a blend of a polyarylene ether sulfone polymer and a further polymer, and wherein the lower top layer (LTL) is joined to the foam core layer (FCL) via a second film (F2) comprising a blend of a polyarylene ether sulfone polymer and a further polymer. A further aspect of the invention is a method for producing a sandwich panel and the use of a sandwich panel as a construction part for the aeronautical industry and as a rotor blade for constructing a wind turbine. Yet another aspect of the invention is a method for reusing a sandwich panel.

A method for forming a composite article such as a vane includes mating a polymeric barrier with a fiber scrim. A first layer is applied to a tool. The mated polymeric barrier and fiber scrim are applied atop the first layer. Multiple further fiber layers are applied atop the mated polymeric barrier and fiber scrim.

To provide a damping coating applied to a turbine component including a damping coating comprising a viscoelastic layer (71) and a constraining layer (72).SOLUTION: A coating is applied to a base (21) material. The coating includes a viscoelastic layer (71) and a constraining layer (72), the viscoelastic layer (71) is arranged on the base (21) material, and the constraining layer (72) is arranged on the viscoelastic layer (71).SELECTED DRAWING: Figure 8