Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An example apparatus includes a compressor comprising a rotor defining a radial direction and a circumferential direction, the rotor including a slot; a first blade and a second blade disposed in the slot, the first blade including a first platform and a first dovetail, the second blade including a second platform and a second dovetail; and a hollow block disposed circumferentially between the first blade and the second blade in the slot, the hollow block including: a platform interface portion to interface with the first platform and the second platform, the platform interface portion including a central opening defined by a circumferential face of the platform interface portion; and a hollow dovetail interface portion to couple the first dovetail and the second dovetail.

Abstract: A turbine rotor wheel for an aircraft turbomachine includes a rotor disk, an annular shroud extending around the disk, and blades arranged between the disk and the shroud. The root of each of the blades has two tabs configured for attachment to the disk. The tabs are arranged upstream and downstream, respectively, of a wall of the disk, relative to the axis. The tab arranged upstream is engaged in a first recess of the disk and configured to cooperate by abutment with a peripheral edge of the first recess. The tab arranged downstream is engaged in a second recess of the disk and is configured to cooperate by abutment with a peripheral edge of the second recess.

Abstract: This invention relates to a root end structure, a wind turbine blade comprising such a root end structure and a method of manufacturing such a wind turbine blade. The root end structure comprises a plurality of fastening members distributed along a root end of a blade part, wherein a first plurality of pultruded elements are arranged in between the fastening members and a second pultruded element is further arranged at the blade joint ends adjacent to an outermost fastening member. Each first pultruded element has opposite facing second sides each facing a first side of an adjacent fastening member. The second pultruded element has one second side facing the outermost fastening member and another second side facing the blade joint interface. The second pultruded element comprises a transition portion forming a smooth transition for the inner layers extending further along the mould edge surface.

Abstract: The present invention is directed to a turbomachinery blade and a method of fabricating the turbomachinery blade. The turbomachinery blade comprises a plurality of blade segments, and the plurality of the blade segments are separate from one another at least partially in an axial direction forming radial seams between adjacent blade segments. The method comprises forming a plurality of blade segments which are separate from one another at least partially in an axial direction; and forming radial seams between adjacent blade segments.

Abstract: A rotor assembly for a piece of rotational equipment includes a rotor disk configured to rotate about a rotational axis. The rotor disclose includes a first rotor attachment member including a first mount slot and a second rotor attachment member including a second mount slot. The rotor disk further includes an outer diameter surface extending between the first rotor attachment member and the second rotor attachment member. The rotor assembly further includes a rotor blade including an airfoil, a platform, a first mount portion retained within the first mount slot, and a second mount portion retained within the second mount slot. The platform includes an inner platform surface facing the outer diameter surface. The rotor disk and the rotor blade define a circumferential portion of a circumferentially-extending cavity between the inner platform surface, the outer diameter surface, the first rotor attachment member, and the second rotor attachment member.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section extending from a root section. The airfoil section includes a sheath that receives a core. The core includes first and second ligaments received in respective internal channels defined by the sheath, and each one of the first and second ligaments includes at least one interface portion in the root section dimensioned to receive a retention pin.

Abstract: A platform for a gas turbine engine according to an example of the present disclosure includes, among other things, a platform body that extends in a circumferential direction between first and second sidewalls to define a gas path surface, and opposed rows of flexible retention tabs that extend from the platform body and are dimensioned to wedge the platform between adjacent airfoils.

Abstract: A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of vanes. The first rotor disk is configured to rotate about a rotational axis. The first rotor disk is configured from or otherwise includes disk material. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The vanes are arranged circumferentially around the rotational axis and axially between the first rotor disk and the second rotor disk. The vanes include a first vane, which first vane is configured from or otherwise includes vane material that is different than the disk material.

Abstract: A locking spacer assembly for filling a final spacer slot in a disk groove between platforms of adjacent blades of a blade assembly in an industrial gas turbine engine is presented. The locking spacer assembly includes a first side piece, a second side piece, a mid piece and a bolt. The bolt is disposed into the mid piece to position the mid piece in a radial position in an assembled state. The mid piece contacts the first side piece and the second side piece in the assembled state to prevent axial movements of the first and second side pieces in the disk groove. The bolt prevents a radial movement of the mid piece.

Abstract: A component for a gas turbine engine, comprising: a first wall defining an exterior surface of the component; a second wall, arranged such that a coolant channel is defined by the space between the first and second walls; and a plurality of apertures provided through the first wall to connect the coolant channel to the exterior surface of the component; wherein adjacent at least one aperture the coolant channel comprises a flow modifier, configured to locally change the pressure of the coolant flowing in the coolant channel in the region of the aperture relative to a region of the coolant channel adjacent another aperture.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction, and the airfoil section defines a pressure side and a suction side separated in a thickness direction. The airfoil section includes a metallic sheath that receives a composite core, and the core includes first and second ligaments received in respective internal channels defined by the sheath such that the first and second ligaments are spaced apart along the root section with respect to the chordwise direction. The first and second ligaments define respective sets of bores, and the respective sets of bores are aligned to receive a common set of retention pins.

Abstract: A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk and a plurality of rotor blades. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is mounted to the first rotor disk and to the second rotor disk. The rotor blades include a first rotor blade. The first rotor blade includes an attachment projecting axially along the rotational axis into a first pocket in the first rotor disk and a second pocket in the second rotor disk. The attachment has a dovetail cross-sectional geometry when viewed in a plane perpendicular to the rotational axis. A portion of the first rotor disk extends circumferentially across and covers the attachment.

Abstract: A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of disk mounts. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is mounted to the first rotor disk and to the second rotor disk. The rotor blades include a first rotor blade. Each of the disk mounts connects the first rotor disk and the second rotor disk together. The disk mounts include a first disk mount that further supports the first rotor blade.

Abstract: A rotor assembly for a gas turbine engine includes, among other things, a rotatable hub that has a metallic main body that extends along a longitudinal axis, and that has an array of annular flanges that extend about an outer periphery of the main body to define an array of annular channels along the longitudinal axis. Each of the annular channels receives a composite reinforcement member that extends about the outer periphery of the hub.

Abstract: A turbine engine having a bypass fluid conduit coupled to the turbine section includes at least one particle separator located within the bypass fluid conduit to separate particles from a bypass fluid stream prior to the bypass stream reaching the turbine section for cooling. A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser, a particle outlet, an angular velocity decreaser downstream of the angular velocity increaser, and a bend provided between the angular velocity increaser and the angular velocity decreaser.

Abstract: A blade for use in a gas turbine engine is disclosed. In various embodiments, the blade includes a pressure side sheath and a suction side sheath secured to the pressure side sheath. The pressure side sheath and the suction side sheath are configured to form a continuous sheath that wraps around an interior section of the blade.

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a thickness direction. The airfoil section includes a metallic sheath that receives a composite core. The core includes first and second ligaments received in respective internal channels defined by the sheath such that the first and second ligaments are spaced apart along the root section with respect to the chordwise direction.

Abstract: The present disclosure generally relates to integrated core-shell investment casting molds that provide filament structures corresponding to cooling hole patterns in the surface of the turbine blade or stator vane, including in locations that are inaccessible due to the presence of protrusion patterns. The filament structures also provide a leaching pathway for the core portion after metal casting. The invention also relates to core filaments that can be used to supplement the leaching pathway, for example in a core tip portion of the mold.

Abstract: An apparatus and method for minimizing a cross-flow across an engine cooling hole can include a component, such as an airfoil, having an outer wall bounding an interior from an exterior. A cooling passage is formed in the interior of the component for cooling the engine component. A cooling hole or film hole can be provided in the outer wall fluidly coupling the interior to the exterior. The cooling passage can be shaped to minimize cross-flow over the cooling hole at the interior of the component.

Abstract: A rotor blade for a turbomachine, in particular in an aircraft engine, with a cooling arrangement for cooling a surface inside the rotor blade by means of a cooling medium, in particular cooling air. The rotor blade having an impingement cooling device with a plurality of impingement cooling openings for deflecting the cooling medium flowing in the interior of the impingement cooling device onto the surface that is to be cooled by means of impingement cooling inside the rotor blade and that is located outside of the impingement cooling device, so that the surface can be cooled by means of an impingement cooling through a cooling medium than exits from the impingement cooling openings, wherein the impingement cooling device is movably mounted with respect to the rotor blade.

Abstract: A fuel injector guide is provided for a turbine engine combustor. The fuel injector guide includes a tubular base, an annular flange, a plurality of ribs and a flow turbulator. The base extends along an axis between first and second ends. The flange extends radially out from the base at the second end. The ribs are disposed around the base and extend axially out from the flange towards the first end. The flow turbulator is disposed between an adjacent pair of the ribs.

Abstract: A rotatable body includes a rotor and n buckets, each bucket being coupled to the rotor in a tangential entry manner. The rotor supports each of the n buckets coupled to the rotor, so the buckets may be stably coupled to the rotor, using a unified annular dovetail tenon that protrudes axially from the rotor. Each bucket includes a bucket dovetail mortise for engaging with the unified annular dovetail tenon in order to couple the bucket to the rotor. A method of manufacturing the rotatable body includes assembling first to (n?1)th buckets with the rotor wheel by successively inserting the first to (n?1)th buckets through the tangential entry; assembling the nth bucket with the adapter; assembling the adapter with the rotor wheel, by inserting the adapter assembled with the nth bucket into the tangential entry; and collectively moving all the buckets by one half pitch in the circumferential direction.

Abstract: A rotatable body includes a rotor and n buckets, each bucket being coupled to the rotor in a tangential entry manner. The rotor supports each of the n buckets coupled to the rotor, so the buckets may be stably coupled to the rotor, using a unified annular dovetail tenon that protrudes axially from the rotor. Each bucket includes a bucket dovetail mortise for engaging with the unified annular dovetail tenon in order to couple the bucket to the rotor. A method of manufacturing the rotatable body includes assembling first to (n?1)th buckets with the rotor wheel by successively inserting the first to (n?1)th buckets through the tangential entry; assembling the nth bucket with the adapter; assembling the adapter with the rotor wheel, by inserting the adapter assembled with the nth bucket into the tangential entry; and collectively moving all the buckets by one half pitch in the circumferential direction.

Abstract: A closing assembly for closing a blade ring inserted into a circumferential T-groove of a blade support of a turbomachine, having two insertion elements, each has a C-shaped basic form having a resting leg, retention leg, and connection leg connecting the resting leg and the retention leg and is designed to reach around a ridge of the T-groove. The resting leg reaches over the ridge and the retention leg reaches under the ridge, and an intermediate element, is positioned between the insertion elements to prevent the insertion elements from moving to the center of the T-groove. The intermediate element reaches below the retention legs of the insertion elements in the assembled state, and a positioning element is associated with the intermediate element, which is supported between the groove base of the T-groove and the intermediate element and to position the intermediate element at a desired distance from the groove base.

Abstract: A rotor blade of a turbine engine may have internal passages to permit the travel of cooling air through the blade. These passages may include a tip flag, a serpentine channel, and a trailing edge channel. The tip flag may extend radially outward along the leading edge of the rotor blade and may turn axially aftward along the tip of the rotor blade. The tip flag may terminate forward of a portion of the serpentine channel and the trailing edge channel. Thus the tip flag may be a “partial tip flag.” The internal passages may be arranged to ameliorate the effect of ambient pressure variations, such as between the leading edge and the trailing edge of the rotor blade, on the flow travel of cooling air through the rotor blade.

Abstract: There is provided a turbine including a rotor wheel including a plurality of dovetail grooves and at least one insertion groove, the dovetail grooves and the insertion groove arranged in a circumferential direction of the rotor wheel; a plurality of first buckets, each of the first buckets including a vane, a platform provided at a first end portion of the vane, and a dovetail provided at the platform and having a shape corresponding to a corresponding dovetail groove; at least one second bucket including a vane, a platform provided at a first end portion of the vane, and at least one protrusion portion provided at the platform and configured to be inserted into a corresponding insertion groove of the insertion groove; and a fixing member configured to be inserted through the protrusion portion and the rotor wheel and configured to restrict radial movement of the second bucket.

Abstract: A new system and apparatus for detachably joining a first component to a second component is disclosed, along with a method for detachably joining two components. Embodiments of the present invention include a tensioning apparatus and system for clamping joints. The tensioning apparatus may include a wedge block and a fastening device. The clamping joint may be a tongue and groove joint that is tightened using the tensioning apparatus.

Abstract: A root bushing for a blade root of a wind turbine rotor blade, including a cylindrical bushing body and a flat contact body is provided. The contact body is provided on a face of the bushing body. This has the advantage that due to the provision of the contact body, the contact area between the root bushing and the pitch bearing is increased. In another embodiment, the root bushing includes a central bore which protrudes through the bushing body and the contact body. In another embodiment, an outer wall of the bushing body is provided with a connection structure for connecting the root bushing to a composite material of the wind turbine rotor blade.

Abstract: A new system and apparatus for detachably joining a first component to a second component is disclosed, along with a method for detachably joining two components. Embodiments of the present invention include a tensioning apparatus and system for clamping joints. The tensioning apparatus may include a wedge block and a fastening device. The clamping joint may be a tongue and groove joint that is tightened using the tensioning apparatus.

Abstract: A compressor blade mounting arrangement includes a compressor blade having an airfoil, a base attachment and a platform disposed between the airfoil and the base attachment. The base attachment includes a first root portion extending radially inwardly from the platform and a second root portion extending radially inwardly from the platform, the first root portion and the second root portion defining a hollow portion therebetween. The base attachment also includes a compression plate disposed within the hollow portion and in fitted engagement with the first root portion and the second root portion. The base portion further includes at least one tab protruding from at least one of the first root portion and the second root portion. The compressor blade mounting arrangement also includes a wheel including a channel extending from a base wall to a rim of the wheel, the channel having a varying opening width.

Abstract: A device for attaching blades to a rotor disk of a turbine engine is provided. The device includes: a rotor disk provided at its outer periphery with a plurality of slots, each slot being formed between two adjacent disk teeth and extending axially between front and rear faces of the disk; a plurality of blades, each having a respective root mounted in a slot of the disk; and at least one pin mounted in the rotor disk to pass through the roots of at least two adjacent blades and extending between the front and rear faces of the rotor disk so as to attach the blades to the rotor disk.

Abstract: A turbomachine having a flow channel and a housing radially surrounding the flow channel, a plurality of stationary and moving blades being situated in the flow channel, stationary blades being situated adjacent to the moving blades in the axial direction, and the stationary blades having at least one stationary blade hook which engages with at least one housing hook for the purpose of connecting the stationary blades to the housing. A sealing and lining element is situated in the radial direction between the moving blades adjacent to the stationary blades and the housing, and has a sealing structure interacting with blade tips of the moving blades. A heat protection element is provided in the area between the sealing and lining element and the housing, and a sealing element being situated on the heat protection element for the purpose of sealing contact with the housing hook.

Abstract: A system for attaching a rotating blade in a turbine includes a bush having an axial slot and a radial slot that intersects with the axial slot. A radial retention member fits within the radial slot, and an axial retention member fits within the axial slot and engages with the radial retention member. A method for attaching a rotating blade in a turbine includes inserting a bush into an axial passage in a rotor wheel and inserting a radial retention member into a radial passage in the rotor wheel and through at least a portion of the bush. The method further includes inserting the rotating blade in a slot in the rotor wheel, inserting the radial retention member into a retention slot in the rotating blade, and inserting an axial retention member into the bush.

Abstract: A pinned root fixing arrangement of axial flow steam turbine rotor discs made of a low alloy that is less susceptible to stress corrosion cracking (SCC). Such an arrangement has a first ratio, which is defined as ratio of the axial breadth of the disc fingers and the sum of the axial breath and the axial breadth G of the gap between adjacent disc fingers, in the range of about 0.4 to about 0.6 and further has a second ratio, which is defined as the ratio of the length of the disc fingers and the blade fingers to the diameter, between 4 and 6.

Abstract: A fan rotor blade has a rotor blade leading edge. On a hub side of the rotor blade leading edge, a vertical hub section is formed. From a top end of the vertical hub section to a mid-span side of the rotor blade leading edge, a backward tilt mid-span section is formed. From a top end of the backward tilt mid-span section to a tip end of the rotor blade leading edge, a forward tilt tip section is formed. From a hub end of the rotor blade leading edge to a base end of the vertical hub section, a backward tilt hub section is formed. The backward tilt hub section is backwardly tilted so that a top end thereof is positioned behind a base end thereof.

Abstract: Locking spacer assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a spacer, the spacer including a platform and a plurality of legs extending generally radially inward from the platform. The locking spacer assembly further includes a clamp configured to contact and cause elastic deformation of each of the plurality of legs in a generally axial direction towards each other. The locking spacer assembly further includes a locking lug configured to contact and impart a force against each of the plurality of legs in an opposite generally axial direction.

Abstract: A locking blade for a rotor can include an airfoil portion with a root from which a tongue extends. Opposed bucket segments can engage the tongue and can be retained in a longitudinal direction of the blade by a fastener, such as a pin, that can extend through holes in the segments and tongue. Tines parallel to and on opposite sides of the tongue can extend from the root and include holes through which the fastener can extend, the bucket segments extending between respective tines and the tongue. The structure can eliminate an assembly gate in a rotor.

Abstract: Systems and devices adapted to retain dovetail components (e.g., buckets) in a turbine drum rotor and reduce rotor component displacement are disclosed. In one embodiment, a turbine bucket includes: a bucket base portion shaped to complement a bucket shank slot in a rotor of a turbine, the bucket base portion including: a forward portion shaped to extend upstream of a first stage circumferential slot of the rotor in to a first rotor post of the rotor; a circumferential protrusion formed in an aft end of the bucket base portion and shaped to connect to the rotor, and a set of axial protrusions formed on tangential sides of the bucket base portion and shaped to connect to the rotor; and a bucket platform extending radially outboard from the bucket base portion, the bucket platform configured to complement a vane.

Abstract: Embodiments of the present disclosure include a system having a turbine blade segment having a blade and a mounting segment coupled to the blade. The mounting segment is configured to couple to a slot in a rotor, and the mounting segment has a cavity extending radially into the mounting segment.

Abstract: The stationary vane unit of a rotary machine includes: a first band member that extends in the circumferential direction and comes into contact with the outer shrouds of the plurality of stationary vane members from one side thereof in the main axial direction in which a central axis extends; a second band member that extends in the circumferential direction and comes into contact with the outer shrouds of the plurality of stationary vane members from the other side thereof in the main axial direction; and a fastening member that fastens the first band member and the second band member to each other so that the outer shrouds of the plurality of stationary vane members are connected to each other.

Abstract: A rotor blade for a flow machine, in particular a steam turbine, includes an insertion root with a first finger and two second fingers which are arranged on either side of the first finger in axial direction. The first finger and the second fingers have a shoulder in axial direction on axial sides facing one another such that the fingers have a radially outer first portion and a radially inner second portion whose axial extension is shorter than that of the outer, first portion. In relation to a total axial width between axial sides of the two second fingers which face away from one another, the radial height of the first, radially outer portion is in the range of 0.39 to 0.45, particularly 0.40 to 0.44, and the radial height of the second, radially inner portion is between 0.40 and 0.46, particularly between 0.41 and 0.45.

Abstract: A rotor blade of a wind power installation for fixing to a rotor hub and having a rotor blade longitudinal axis, including a rotor blade inner part towards the rotor hub, and a rotor blade outer part away from the rotor hub, wherein the rotor blade inner part and the rotor blade outer part are connected together by means of at least one connecting device and the connecting device includes at least one anchoring element anchored in the rotor blade outer part, at least one counterpart element anchored in the rotor blade inner part, and at least one connecting bolt which extends through the counterpart element and is fixed in the anchoring element.

Abstract: A method of repairing or of reworking a turbomachine disk including, on its rim, at least one external radial tab with an axial bore to accept an axial pin including a head and a shank with a threaded portion, the pin being slipped into the bore such that the head comes to press against one face of the tab through tightening of a nut on to the shank with the threaded portion against the opposite face of the tab, the pin forming a retaining mechanism to keep a tab secured to a component attached to the rim. A spot face is machined in the tab around the bore corresponding to a wearing zone, and a replacement pin including a flange pressing against the surface of the spot face, of a diameter greater than that of the head, is fitted.

Abstract: A locking device for enabling the circular locking of a set of blades provided with a hammer base on the rim of a turbine engine compressor hub is disclosed. The rim includes a peripheral groove on the outer surface thereof for receiving the bases of the blades of the set and two shoulders framing the groove with surfaces which form bearings for holding the blades; and a cut-out provided in at least one of the shoulders to enable the bases of the blades to be inserted in the groove. The locking device translatably immobilizes the blades in the groove and is positioned in the groove between two consecutive blades and in turn translatably held in the groove by an attachment device. A carrier is shaped so as to fit into the cut-out and to rest circumferentially on at least one engagement surface of the shoulder.

Abstract: A blade assembly for a groove of a wheel of rotating machinery is described. The blade assembly includes, a blade root having two longitudinal sides, a base, and a roof, wherein the profile of the longitudinal sides includes a rounded surface, a blade connected to the roof of the blade root, and one or more keys juxtaposed along each longitudinal side of the blade root, each key having an inboard side and an outboard side, wherein the profile of the inboard side of each key is configured to mate with the profile of the blade root. The blade assembly allows replacement of a compressor blade without the need for unstacking the rotor to gain access to the damaged blade.

Abstract: In a turbine rotor blade assembly 1, a length h2 in the radial direction of a bucket dovetail 15 of a notch blade 10 is configured to be shorter than a length h3 in the radial direction of an effective blade portion 13 of a adjacent notch blade 30 and a length h4 in the radial direction of the bucket dovetail 15. Thus, during an insertion of the notch blade 10 in the axial direction, the rotational movement Rf around the radial direction and the circumferential movement of the notch blade 10 can be secured.

Abstract: A wind turbine blade for a wind turbine is a shell structure of a fibre-reinforced composite and comprises a root region and an airfoil region. The root region has a ring-shaped cross section and comprises a plurality of elongated bushings 7 with an inner thread 22 and which are embedded interspaced in the fibre-reinforced polymer so as to substantially follow the circumference of the root region and allow access from the outside to the inner threads 22. The bushings 7 are formed conically tapering from a second end towards a first end thereof, the first end of the bushing 7 being arranged at the end face of the root region.

Abstract: A wind turbine blade for a wind turbine is a shell structure of a fibre-reinforced composite and comprises a root region and an airfoil region. The root region has ring-shaped cross section and comprises a plurality of elongated bushings 7 with an inner thread 22 and embedded interspaced in the fibre-reinforced polymer so as to substantially follow the circumference of the root region and allow access from the outside to the inner threads. Each fastening member 7 is provided with a notch 60? in the periphery 11 thereof. A rod-shaped locking element 61 passes through the notch 60? in engagement therewith. The locking element 61 is fixedly and tightly fitting arranged in a through-going circular bore 65 extending through the wall of the root region.

Abstract: A wind turbine blade for a wind turbine is a shell structure of a fiber-reinforced composite and comprises a root region and an airfoil region. The root region has ring-shaped cross section and comprises a plurality of elongated bushings 7 with an inner thread 22 and embedded interspaced in the fiber-reinforced polymer so as to substantially follow the circumference of the root region and allow access from the outside to the inner threads. Each fastening member 7 is provided with a notch 60? in the periphery 11 thereof. A rod-shaped locking element 61 passes through the notch 60? in engagement therewith. The locking element 61 is fixedly and tightly fitting arranged in a through-going circular bore 65 extending through the wall of the root region.

Abstract: A wind turbine blade for a wind turbine is a shell structure of a fibre-reinforced composite and comprises a root region and an airfoil region. The root region has a ring-shaped cross section and comprises a cylindrical insert 7 embedded in the fibre-reinforced polymer so as to substantially follow the circumference of the root region. The cylindrical insert is provided with a number of mutually spaced threaded bores 12, 15 in a first end 9 thereof being accessible from the outside.