Abstract: In structural reinforcement for a composite blade of a turbine engine, the reinforcement being for adhesively bonding to a leading edge of the blade and presenting over its full height a section that is substantially V-shaped, having a base that is extended by two lateral flanks, there is provided an assembly of a plurality of fiber bundles that is mounted in at least one housing in the base, which assembly defines fiber content that varies along the full height of the housing.

Abstract: Structural preform layers of multiple rigid unidirectional strength elements or rods are constructed and arranged for use in fabricating load-bearing support structures and reinforcements of wind turbine blades. Individual preform layers include multiple elongate unidirectional strength elements or rods arranged in a single layer along a longitudinal axis of the preform layer. Each preform layer includes one or more fibrous carrier layers to which the multiple strength elements or rods are joined and arranged in the single layer. Each strength element or rod is longitudinally oriented and adjacent to other elements or rods. Individual strength elements or rods include a mass of substantially straight unidirectional structural fibers embedded within a matrix resin such that the elements or rods have a substantially uniform distribution of fibers and high degree of fiber collimation.

Abstract: The present application relates to a blade of low pressure rectifier axial turbomachine. The blade can also be a rotor blade and/or a turbine blade. The blade includes a composite material with a matrix and a reinforcement that includes a mesh forming a three dimensional structure with a plurality of rods that describe a three-dimensional mesh based on polyhedrons. The three-dimensional structure extends over the majority of the thickness of the blade between the pressure side surface and the suction side surface and/or the majority of the length of the blade between the leading edge and the trailing edge. The rods of the reinforcement are bonded to each other and are distributed throughout the volume between the pressure side surface and the suction side surface of the blade. The rods form a three-dimensional mesh occupying the entire blade. The present application also relates to an iterative method for manufacturing a blade by additional layer manufacturing.

Abstract: A rotor blade of a wind power plant in which the rotor blade has a longitudinal extension that extends from a rotor blade root substantially to a rotor blade tip. At least in one region of the rotor blade, an aerodynamic cross-sectional profile is provided, which has a leading edge (nose) and a trailing edge, which are connected via a suction side and a pressure side of the cross-sectional profile. The rotor blade is subdivided at least in a longitudinally extended section into a front rotor blade section with the leading edge and a rear rotor blade section with the trailing edge. The rear region of the front rotor blade section and the adjacent front region of the rear rotor blade section are connected through an I-beam.

Abstract: A fan includes a frame, rotor supported by this frame and having a central hub and a number of blades and a drive mechanism for rotatably driving the rotor, in addition to a ring to which the end zones of the blades are connected. The ring is assembled from two part-rings of the same form which each include a circular strip of sheet material, the free ends of which are mutually connected to form the outer surface of a truncated cone, and a third part-ring which mutually connects the inner edges of the first two part-rings. The end zones of the blades are connected to the third part-ring. The ring has a diameter of more than about 1.50 m. The number of blades amounts to at least eight. The blades are hollow and include a framework structure which is provided with a skin connected thereto.

Abstract: A turbine blade includes a core element having a base portion, a tip portion, and an intermediate portion extending between the base portion and the tip portion. The intermediate portion includes a non-uniform cross-section and is a high-strength fiber material. The turbine blade further includes a shell disposed around the core element, and the volume between the core element and the shell forms a void.

Abstract: A turbine vane for a gas turbine engine may include a composite airfoil structure. The composite airfoil structure may have an opening. The turbine vane may include a spar. The spar may have a body, which may be disposed within the opening. A standoff structure may be disposed within the opening. In some non-limiting embodiments, a cooling air gap may be defined between the body and an internal surface of the composite airfoil structure.

Abstract: A rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a hub and a rotor blade connected to the hub to extend radially away therefrom. The rotor blade may include biasing fibers, oriented to increase the twist of the rotor blade in response to an increase in the speed of rotation of the rotor corresponding to a mission, task, or maneuver.

Abstract: A hybrid part for use in a gas turbine engine has a platform and an attachment feature. The platform and an exterior portion of the attachment feature are formed from a monolithic ceramic material. A ceramic matrix composite material is located adjacent interior portions of the platform and the attachment feature and is bonded to the monolithic ceramic material.

Abstract: A partial pitch wind turbine blade in which the pitch system of the blade functions as a lightning receptor. As the pitch system is of a relatively large dimension, it is able to dissipate the effects of a lightning strike without damage, and removes the needs for additional blade features normally used to conduct lightning around or away from the pitch system.

Abstract: A rotor blade with a supporting structure, wherein the rotor blade has a rotor blade base section and a rotor blade tip section, is provided. The supporting structure includes a first supporting segment for supporting the rotor blade base section and at least a second supporting segment for supporting the rotor blade tip section. Furthermore, the supporting structure includes the first supporting segment and the second supporting segment along the rotor blade longitudinal direction. The first supporting segment is joined to the second supporting segment in a supporting structure transition section, wherein the supporting structure transition section is located in between the rotor blade base section and the rotor blade tip section. Finally, the first supporting segment and/or the second supporting segment include a fibre material. A method for manufacturing the rotor blade is also provided.

Abstract: A rotor blade in a fiber-reinforced composite design for a tail rotor of a rotary wing aircraft (helicopter), with a blade section (5; 5?) having a blade skin (a, r) and a blade body (b . . . g, s, t), which blade section (5; 5?) forms an aerodynamically effective profile, with a blade tip (6) that faces away from the hub of a drive device of the rotor; and with a coupling section (9, 11; 9?, 11?) which faces towards the hub, with an attachment device (2) for a tension-torque-transmission element (3) and for a control tube (4) is improved in that the blade section (5; 5?) and the coupling section (9, 11; 9?, 11?) include spar tapes (a . . . g) that go all the way through and that are made of unidirectional fiber material.

Abstract: A method of making a fiber preform, and the preform, for fabricating a turbine engine blade out of composite material, the method including: making a single-piece fiber blank by three-dimensional weaving with layers of longitudinal yarns interlinked by yarns of layers of transverse yarns; and shaping the fiber blank to obtain a single-piece fiber preform including a portion forming an airfoil preform and at least one portion forming a platform preform. During weaving, yarns of a first group of longitudinal yarns are extracted from the fiber blank beside one of side faces of the blank to form a portion corresponding to a blade platform preform, and yarns of a second group of longitudinal yarns are inserted into the fiber blank with mutual crossing of the yarns of the first group and the yarns of the second group.

Abstract: A composite fibre component for a rotor blade of a wind power plant having a first surface, shaped in a predefined fashion, on a first side of the composite fibre component. The composite fibre component is developed such that the composite fibre component has a second surface, shaped in a predefined fashion, for connecting to a further component for the rotor blade on at least one partial area of a second side, facing away from the first side, of the composite fibre component. A manufacturing device for manufacturing a composite fibre component for a rotor blade of a wind power plant by using a vacuum infusion method, and to a method for manufacturing a composite fibre component for a rotor blade of a wind power plant by using a vacuum infusion method.

Abstract: A fiber structure for reinforcing a composite material part, the structure being woven as a single piece by multilayer weaving between a first plurality of layers of yarns extending in a first direction and a second plurality of layers of yarns extending in a second direction. The second plurality of layers of yarns includes at least one layer of variable-weight yarns, each variable-weight yarn including a separable assembly of individual yarns, each having a determined weight. The fiber structure includes at least one portion of reduced thickness in which the variable-weight yarn presents a weight that is less than the weight that it presents prior to the reduced thickness portion.

Abstract: A method of finishing a fan blade includes bonding a sheath and a cover to an aluminum fan blade with an airfoil, a root, a leading edge and a tip; imparting residual stresses onto the blade; coating the blade to protect exposed areas of the blade; and curing the blade in low-temperature cure cycles to preserve residual stresses imparted.

Abstract: A composite gas turbine engine structure includes a retention ring with airfoils mounted on, integral with, and extending radially away from retention ring. Retention ring includes annular composite plies, a circumferentially segmented airfoil ring including airfoil ring segments disposed around one of outer and inner circumferences of retention ring. Airfoil ring segments include annular bases and radially extending clockwise and counter-clockwise airfoil segments at clockwise and counter-clockwise ends of annular base. Composite airfoils include circumferentially adjacent ones of the clockwise and counter-clockwise airfoil segments. A flowpath shell circumferentially disposed around segmented airfoil ring traps annular bases between flowpath shell and retention ring. Composite airfoils airfoils extend through slots in flowpath shell. Plies may be wrapped in a single spiral made from a continuous composite tape. Slots may be circumferentially angled.

Abstract: Systems and methods for reducing wind pressure on wind turbine blades by selectively opening excessive wind portals in the turbine blades. One embodiment comprises a wind turbine system in which each of the turbine's blades has a portal therethrough that is opened or closed by a movable panel. Each panel is connected on one edge to the corresponding blade at the edge of the portal. Hook-and-loop material (Velcro) is attached to the edges of each portal and panel, allowing the panels to alternately open and then close the portals over a series of high wind events. Excessive wind pressure forces the panels to be released, opening the portals. Gravity or reversed wind direction with respect to the blade can be used to reseal the panels.

Abstract: The invention relates to a method of cutting off laminate layers for use in a fibre-reinforced laminate object comprising a number of combined laminate layers, wherein, along a section of the at least one rim of the laminate layer, a tapering cut is performed through the thickness of the laminate layer, whereby the thickness of the laminate layer is reduced. Since not only the number of laminate layers, but also the thickness of the individual laminate layers are reduced, a laminate layer is accomplished that can be used in a laminate object, by which both the issues of areas rich in resin, air pockets and the risk of delamination are reduced. The invention also relates to a laminate layer for use in a fibre-reinforced laminate object comprising a number of combined laminate layers and a fibre-reinforced laminate object in the form of the blade of a wind turbine, wherein the blade of the wind turbine comprises a number of combined laminate layers.

Abstract: Rotor blade or rotor blade segment for a wind turbine, having at least one cable for fixing the rotor blade or rotor blade segment to a rotor hub or to a further rotor blade segment, wherein the at least one cable is redirected in a U-shaped manner within the rotor blade or rotor blade segment.

Abstract: The invention relates to a wind turbine blade with a lightning protection system, the lightning protection system comprises at least one lightning receptor arranged freely accessible in or on the shell unit surface at or in the immediate vicinity of the tip of the blade. The lightning protection system further comprises a lightning down conductor made of electrically conductive material extending within the shell body from the lightning receptor to the root end of the blade. The lightning receptor and the lightning down conductor are electrically connected. The shell body comprises at least a first conductive layer extending along at least a longitudinal part of the lightning down conductor in a transverse distance therefrom. The first conductive layer is electrically isolated from the lightning down conductor and from the lightning receptor, and has a sheet resistance in the range 1-5 Mega Ohm per square.

Abstract: Method for fabricating a reinforcing coating for a part made of composite material. Pre-impregnated reinforcing fibers are used in the form of slivers and said slivers are laid on the part in two layers of longitudinal slivers by being placed thereon. This fabrication makes provision for using an angular orientation for the slivers of each layer respectively of 0° and of some other angle relative to said determined direction of the solid body for covering using an interlaced pattern type that gives layer crossing lines parallel to a longitudinal axis of the solid body for covering, which pattern type is selected to form interlacing patterns that limit the number of layer crossing lines along the longitudinal axis of the solid body for covering to a single line.

Abstract: A blade (10) for a rotor of a wind turbine (2) is disclosed. The blade is assembled from an inboard blade part (50) closest to the hub and an outboard blade part (110) farthest from the hub of the wind turbine. The inboard part (50) comprises a load carrying structure (60) with a first aerodynamic shell (70) fitted to the load carrying structure (60), and the outboard part (110) comprises a blade shell (141, 143) with a load carrying structure (142, 144) integrated in the blade shell (141, 143).

Abstract: Mechanical strength of a composite material is enhanced by a simple process. In a composite material comprising a resin or a rubber and an oxide glass, the resin or the rubber is dispersed in the oxide glass, or the oxide glass is dispersed in the resin or the rubber, and the oxide glass is softened and fluidized by heating at or lower than a heat decomposition temperature of the resin or the rubber.

Abstract: The present invention provides a structural element, in particular for an aircraft or spacecraft, comprising a core, the material density of which varies, at least in portions, in order to optimize the natural vibration behavior of the structural element. The present invention further provides a method for producing a structural element, in particular for an aircraft or spacecraft, comprising the following steps: providing a structural element which has a core; determining the natural vibration behavior of the structural element; and varying the material density of the core of the structural element, at least in portions, in such a way that the natural vibration behavior of the structural element is optimized. The present invention provides still further an aircraft or spacecraft and a rotor blade, in particular for a wind turbine, comprising such a structural element.

Abstract: A composite component for a wind turbine blade is provided. The composite component includes a stack of at least one fibre layer and a membrane which has a first surface and a second surface which is an opposite surface with respect to the first surface. The membrane is arranged with the first surface on top of the stack. The membrane is perforated with openings, wherein the membrane is formed in such a way that the openings are permeable for a fluid flowing along a first direction directing from the first surface to the second surface and impermeable for a fluid flowing along a second direction directing from the second surface to the first surface.

Abstract: The invention concerns a rear box section for a rotor blade, in particular of a wind power installation, comprising a pressure-side surface, a suction-side surface, a trailing edge separating the pressure-side and suction-side surfaces, and a connecting side which is opposite to the trailing edge and which is adapted for mounting to a corresponding connecting surface of the rotor blade. The invention concerns in particular a rear box section which is sub-divided into a foot segment having the connecting side and one or more head segments which have the trailing edge and which can be coupled to the foot segment. The invention also concerns a rotor blade for a wind power installation, and a wind power installation.

Abstract: Structural preform layers of multiple rigid unidirectional strength elements or rods are constructed and arranged for use in fabricating load-bearing support structures and reinforcements of wind turbine blades. Individual preform layers include multiple elongate unidirectional strength elements or rods arranged in a single layer along a longitudinal axis of the preform layer. Each preform layer includes one or more fibrous carrier layers to which the multiple strength elements or rods are joined and arranged in the single layer. Each strength element or rod is longitudinally oriented and adjacent to other elements or rods. Individual strength elements or rods include a mass of substantially straight unidirectional structural fibers embedded within a matrix resin such that the elements or rods have a substantially uniform distribution of fibers and high degree of fiber collimation.

Abstract: A ceramic matrix composite member used as a turbine blade includes a principal part forming a blade part and a dovetail part, and a subordinate part forming a platform part. A principal fiber in a ceramic fiber fabric forming the principal part is a continuous fiber. An extension direction of the principal fiber is in parallel with a direction in which stress is applied. The ceramic fiber fabrics respectively forming the principal part and the subordinate part are joined together and formed into an integrated three-pronged fiber fabric. The ceramic fiber fabric forming the principal part and the ceramic fiber fabric forming the subordinate part are integrated together by being set into a mold with the ceramic fiber fabric forming the subordinate part folded at a desired angle to the ceramic fiber fabric forming the principal part. Then, a ceramic matrix is formed in the obtained molded body.

Abstract: This disclosure describes new construction for rotary elements that find use in compressor devices, e.g., centrifugal compressors and blowers. This construction utilizes composite materials (e.g., carbon fiber composites) that require less machine time and reduce the weight of the rotary element, while meeting the operational characteristics of compressor devices for use in a wide range of industrial applications. In one embodiment, the rotary element has a bi-furcated material design, which uses a first material (e.g., carbon fiber) to form blades and other features of an impeller and a second material (e.g., metal) to form a sleeve with properties that can securely affix the impeller to a drive shaft of the compressor device.

Abstract: A method reinforcing an axisymmetric annular metal part by including a winding of composite material. A metal blank for the part is prepared, a cavity is formed therein that opens out into a coaxial inside face thereof, and that presents a right cross-section of axial extent that decreases from the inside towards the outside, a reinforcing yarn is wound in the cavity, the cavity is closed, the assembly is subjected to a hot isostatic compression process, and the blank is machined to obtain a final part.

Abstract: The present invention provides a structural element, in particular for an aircraft and spacecraft, comprising a core, the rigidity of which varies at least in portions for optimising the aeroelastic characteristics of the structural element The present invention also provides a method for producing a structural element, in particular for an aircraft and spacecraft, which comprises the following steps: provision of a structural element comprising a core; determination of the aeroelastic behavior of the structural element; and variation, at least in portions, of the rigidity of the core of the structural element such that the aeroelastic behavior of the structural element is optimised. The present invention further provides an aircraft and spacecraft comprising a structural element of this type, and a rotor blade, in particular for a wind turbine, comprising a structural element of this type.

Abstract: A method of providing through-thickness reinforcement of a laminated material which includes a matrix material including a step of creating a locally heated zone in the laminated material so as to locally soften the matrix material by focussing a set of at least two energy beams at a location where through-thickness reinforcement is required and a step of inserting a reinforcement element through the thickness of the laminated material at the location of the locally heated zone to through-thickness reinforce the laminated material.

Abstract: A rotor wing in a fiber-reinforced composite design including fiber layers, in particular for a tail rotor of a rotary wing aircraft, with a rotor blade (1) that includes a blade skin (40, 50) and a blade body (41-57) that includes an aerodynamically effective profile, with a tension-torque-transmission element (3) connected to it, which is designed in one piece with the rotor blade (1), and with fiber layers (42-47) that extend through the tension-torque-transmission element (3) and are scarf-join in the rotor blade (1), is improved in that the fiber layers (42-47) extend right through from the tension-torque-transmission element (3) to the blade body (41-57). Furthermore, a method for producing the rotor wing is described.

Abstract: A reinforcing structure 9 for a wind turbine blade is in the form of an elongate stack 27 of layers 31 of pultruded fibrous composite strips supported within a U-shaped channel 28. The length of each layer 31 is slightly different to create a taper at the ends of the stack; the centre of the stack 27 has five layers 31, and each end has a single layer 31. The ends of each layer 31 are chamfered, and the stack is coated with a thin flexible pultruded fibrous composite strip 33 extending the full length of the stack 27. The reinforcing structure 9 extends along a curved path within the outer shell of the blade. During configuration of the blade components within a mould 37, the reinforcing structure 9 is introduced into the mould 37 by sliding the channel 28 along the surface of an elongate wedge 29 within the mould 37 along the curved path.

Abstract: The invention relates to a device (10) for manufacturing a fiber composite component (3, 4, 5), which is connected to an attachment element (22), for a rotor blade (2) of a wind turbine (1), wherein the fiber composite component (3, 4, 5) is or will be manufactured from at least one fiber material (15, 21) and at least one matrix material, wherein the attachment element (22) is provided with a first region (221) arranged outside of the fiber composite component (3, 4, 5) and a second region (222) integrated into the fiber composite component (3, 4, 5), comprising a manufacturing mold (11) for the fiber composite component (3, 4, 5) with a recess (12), wherein the recess (12) has a first region (121) for receiving the first region (221) of the attachment element (22), and a retention device (13), by means of which fluid matrix material is or will be retained from the first region (121) of the recess (12).

Abstract: An airfoil member can have a root end, a tip end, a leading edge, and a trailing edge. The airfoil member can include an upper skin, a lower skin, and a composite core member having a plurality of cells, an upper surface network of the cells can be bonded to the upper skin, a lower surface network of the cells can be bonded to the lower skin. The composite core can have a septum layer embedded in the cells that form the composite core, the septum layer being configured to provide tailored characteristics of the airfoil member.

Abstract: Disclosed is a turbine rotor device for a gas turbine, the turbine rotor device comprising a turbine rotor body, and a pre-stressed fiber-wound layer, wherein the pre-stressed fiber-wound layer is wound on the periphery of the turbine rotor body to exert a predetermined pre-loading force on the turbine rotor body. Additionally, a rotor, and a gas turbine and a turbine engine having the turbine rotor device are also provided.

Abstract: A hybrid turbine blade and method of fabrication, comprising a shank portion and an airfoil portion. The airfoil portion comprising a composite outer structure having a recess formed therein and an alternating stack of at least one composite section and at least two insert sections disposed in the recess. The outer composite structure and the at least one composite section having a first density. The at least two insert sections having a second mass density, which is less than the first mass density. The composite outer structure and the alternating stack of at least one composite section and at least two insert sections together define an airfoil portion that meets all mechanical load carrying requirements of said hybrid turbine blade such that no load transfer needs to occur through said at least two insert sections.

Abstract: A tension-torque-transmission element (3; 3?; 4) for a rotor blade of a rotary wing aircraft (helicopter), in particular for a fenestron blade of a tail rotor, with a connecting section on the blade side and a connecting section (30; 30?; 40) on the axis side, with a connecting eye (32) on each connecting section, and with a torque-transmission section (34; 34?; 44) that connects the connecting sections (30; 30?; 40), is improved in that the tension-torque-transmission element (3; 3?; 4) is designed in a fiber-reinforced composite design including several layers (A to G) of a textile fabric. A method for producing such a tension-torque-transmission element (3; 3?; 4) is also described.

Abstract: A method for making a rib for an aerofoil structure, the aerofoil structure including a skin component, the method including the steps of scanning the inner surface of the skin component to determine the surface profile thereof, providing a rib having a rib body and a rib foot protruding from the body, machining a foot surface profile into the rib foot, the foot surface profile being arranged to complement the skin inner surface profile where the rib foot is intended to abut the skin component.

Abstract: A core for a composite structure is described. The core has first and second core layers, and an interlayer region between the first and second core layers. At least one of the first and second core layers has hinge portions that facilitate draping of the core without interrupting the interlayer region. The interlayer region may include functionality such as a radar reflecting layer and/or optical fibres. Alternatively, the core may be a bonded core in which the interlayer region includes an adhesive layer for bonding the first and second core layers together.

Abstract: The invention provides a method for preparing a pre-form comprising at least two layers of fiber tows, these layers being at least partly fixed by a resin. The method comprising steps of providing a work surface, and alternating distribution of layers of resin and layers of fiber tows.

Abstract: The wind turbine blade (1) includes a structure made of a fibre reinforced polymer material including a polymer matrix and fibre reinforcement material embedded in the polymer matrix. The fibre reinforcement material includes carbon fibres that have been produced by carbonisation of a precursor to a carbonisation degree of 60% to 80%.

Abstract: A layered composite component is disclosed, the component including: a plurality of stacked layers defining a component thickness between opposed component surfaces and at least one reinforcing element extending from each of the opposed component surfaces the reinforcing elements extending at least partially through the component thickness. Another layered composite component is also disclosed, the component including: a plurality of stacked layers defining a plane and having a primary in-plane axis, wherein the at least one block array of reinforcing elements extends into the component along a reinforcing direction that is angled with respect to the plane of the stacked layers, and wherein the at least one block array is angled in the plane of the stacked layers with respect to the primary axis.

Abstract: A system may include a structure having a leading edge and a fiber-reinforced composite cover. The fiber-reinforced composite cover may include a protective portion and a retaining portion, wherein the retaining portion extends about the structure to self-retain the protective portion along the leading edge, and the protective portion is different from the retaining portion.

Abstract: The invention relates to a rotor blade for a wind turbine, comprising a root of the rotor blade and a rotor blade airfoil. The object of providing a rotor blade which can be easily and inexpensively produced even when of great lengths and which, what is more, enables a system for protection against lightning to be incorporated in a simplified way is achieved, for a rotor blade of the generic kind, by having the rotor blade consist of at least partly a fiber-reinforced plastics composite having metal inserts embedded in the matrix of the fiber-reinforced plastics composite.

Abstract: A fan blade for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side.

Abstract: A turbine rotor includes a plurality of blades of composite material comprising fiber reinforcement densified by a matrix. Each blade comprises a blade body extending between an inner end having a blade root and an outer end forming the tip of the blade. The rotor also includes outer platform elements of composite material comprising fiber reinforcement densified by a matrix, each outer platform element including an opening in which the outer end of a blade is engaged. The portion of the outer end of each blade that extends beyond the outer platform element includes a slot or a notch for receiving a locking element.

Abstract: With a hybrid fan blade, the supporting structure (1) in fiber-composite material is enclosed by an enveloping structure (2) only in an area of the airfoil, with a suction-side sheet-metal cover of the enveloping structure being pre-stressed in tension and a pressure-side sheet-metal cover of the enveloping structure being pre-stressed in compression. This reduces the hazard of delamination between the enveloping structure and the supporting structure.