Abstract: A turbine engine airfoil structure including an airfoil adapted to be supported to extend across a gas passage for a hot working gas in a turbine engine. The airfoil structure further includes a platform structure located at one end of the airfoil and positioned at a location forming a boundary of the gas passage. The platform structure includes a platform member including a gas side surface extending generally perpendicular from the airfoil at a junction with the airfoil, and providing a structural connection to the airfoil. The platform structure further includes a separately formed platform cover attached to the platform member at the gas side surface. The platform cover extends from a location adjacent to one of the sidewalls of the airfoil, and includes an outer surface located for contact with the hot working gas passing through the gas path.

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 leading edge member for a composite vane of a gas turbine engine. The leading edge member includes a first leg and a second leg. The first leg includes a proximal end joined to a proximal end of the second leg.

Abstract: A turbomachine rotor blade, which includes a body radially extending and an insert covering the body tip, the insert being made of a first portion radially covering the blade tip and of a second portion partly covering the intrados face of the blade. The cross-section of the insert along a radial plane with respect to an axis of a rotor is corner-shaped and the first portion of the insert extends tangentially with respect to the main axis of the rotor and the second portion extends globally radially with respect to the main axis of the rotor.

Abstract: An impeller vane includes at least a first metallic core material and at least a first wear resistant material, wherein the hardness of the at least first wear resistant material exceeds the hardness of the at least first metallic core material. The impeller vane consists of a plurality of layers of the at least first metallic core material and the at least first wear resistant material, wherein the layers extend from a leading edge of the impeller vane to the trailing edge of the impeller vane and are arranged alternatingly throughout the cross section of the impeller vane. An impeller includes at least one of the above impeller vanes. The invention also relates to methods for manufacturing an impeller vane and an impeller having such.

Abstract: The present invention relates to a manufacturing method for wind turbine blade and a wind turbine manufactured according to that method. The wind turbine blade comprises two shell parts wherein each shell part has a leading edge connected to a trailing edge via an inner surface. One of the two shell parts comprises an extended shell section which is configured as a flexible shell section. The shell section is configured to flex in a radial direction from a first position to a second position relative to the leading edge when an incoming wind is acting on the pressure side of the wind turbine blade. The wind turbine blade may be manufactured using a non-bonding layer removable arranged adjacent to the glue line between the two shell parts which reduces the amount of manual grinding or polishing of the glue region. This provides a wind turbine blade with an improved blade characteristic where the extended flexible shell section is specifically designed to have significant flexibility.

Abstract: A modular fiber reinforced plastic flange for a structural composite beam which comprises a body formed of a plurality of elongate elements arranged in an array, wherein the dimensions of the body are substantially determined by the number and arrangement of the elongate elements in the array, and a skin member at least partially surrounding the array. Also, a structural composite beam comprising the modular fiber reinforced plastic flange and a shear web connected to the skin member of the modular flange. A method of making the modular flange and beams, and a kit of parts for making the modular flange are also disclosed.

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: According to one embodiment, a molten metal impeller is provided. It includes a generally cylindrical graphite body having a plurality of passages extending from a top surface to a side wall. A hub is formed in the center of the graphite body. A ceramic cap member is secured to the top surface of the graphite body. The cap member is comprised of a ring forming a central passage shaped cooperatively to overlap the hub and a plurality of vanes extending radially from the ring to an outer rim. The rim has a height between adjacent vanes which increases in the direction of intended impeller rotation. The rim further has a height which decreases from its radially outer most edge to an inner most edge.

Abstract: A turbomachine rotor includes: a rotor body having an outer surface; and a patterned abrasive or abradable coating formed over the outer surface of the rotor body, the patterned abrasive or abradable coating for directing a flow of a working fluid across the turbomachine rotor.

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: A rotor blade assembly is provided that includes a rotor blade and a rotor blade tip member. The rotor blade is provided with an integrated lightning down conductor and is attachable or attached to a rotor hub of a wind turbine. The rotor blade tip member is made of an electrically insulating material and is detachably attached or adapted to be detachably attached to a free ending of the rotor blade by a connecting device. The connecting device is a wire or a rod made of an electrically conductive material establishing or adapted to establish a mechanical and electrical connection of the rotor blade tip member with the lightning down conductor of the rotor blade.

Abstract: A blade for use in a gas turbine engine has an airfoil including a leading edge and a trailing edge. A sheath is positioned at the leading edge and secured to the airfoil by a first adhesive formed of a first material. The sheath is formed of a second material that is distinct from said first material. The first material is less electrically conductive than the second material. A grounding element is in contact with the sheath. The grounding element is in contact with a portion of the airfoil formed of a third material that is more electrically conductive than the first material. The grounding element and the portion of the airfoil together form a ground path from the sheath into the airfoil.

Abstract: A fan blade includes an airfoil with a leading edge and a trailing edge in a chordwise direction, a root and a tip in a spanwise direction; and a sheath with a solid portion to cover the leading edge and first and second flanks extending in the chordwise direction to bond to the pressure and suction sides of the airfoil, respectively. The dimensions of the sheath are varied with respect to the spanwise direction of the blade.

Abstract: A composite turbomachine blade (34) comprises a composite material including reinforcing fibers in a matrix material, the turbomachine blade (34) comprises an aerofoil portion (36), a shank portion (38) and a root portion (40). The aerofoil portion (36) has a leading edge (42), a trailing edge (44). The composite turbomachine blade (34) also has a metallic protective member (52) arranged in the region of the leading edge (42) of the aerofoil portion (36) of the turbomachine blade (34). The metallic protective member (52) is adhesively bonded to the composite material in the region of the leading edge (42) of the aerofoil portion (36) of the composite turbomachine blade (34). The metallic protective member (52) has at least one metallic projection (56, 58) extending from the metallic protective member (52) towards the root portion (40) of the composite turbomachine blade (34).

Abstract: A stationary blade and a steam turbine capable of reducing self-excited vibrations with a simple configuration are provided. A stationary blade has a cavity, extending in a blade-width direction, formed therein and slits communicating between the cavity and the outside. A wave-shaped plate spring that is in sliding contact with at least one of a pressure-side member and a suction-side member is provided between the pressure-side member, which is a portion on the pressure side of the cavity, and the suction-side member, which is a portion on the suction side of the cavity. When the stationary blade is elastically deformed, the wave-shaped plate spring causes friction between itself and at least one of the pressure-side member and the suction-side member. This friction attenuates relative positional displacement between the pressure-side member and the suction-side member. Thus, self-excited vibrations occurring at the stationary blade can be reduced.

Abstract: A method of forming a fan blade includes the step of applying an adhesive layer around a leading edge of a fan blade body. The adhesive layer includes an adhesive film supported by a scrim cloth, and the adhesive layer contacts a portion of an inner surface of the fan blade body and a portion of an outer surface of the fan blade body. A leading edge sheath is positioned relative to the fan blade body such that a first flank and a second flank of the leading edge sheath is positioned over the portion of the inner surface and the portion of an outer surface, respectively, of the fan blade body. Pressure is applied to the first flank and the second flank of the leading edge sheath to secure the leading edge sheath to the blade body and curing the adhesive film.

Abstract: A particle trap for collecting loose particles includes a container having an enclosure and at least one opening, and a feed hopper, wherein the feed hopper is connected to the at least one opening of the container, and wherein the particle trap is adapted for collecting particles moving in a direction of an opening of the feed hopper. Further, a method for collecting particles inside a wind turbine rotor blade is disclosed.

Abstract: A method of constructing a cured composite assembly includes positioning a composite assembly within a bonding tool, wherein the composite assembly comprises an uncured composite spar and a skin and performing a curing cycle on the composite assembly to simultaneously cure the uncured composite spar and bond the skin to the cured composite spar.

Abstract: A rotor blade abrasion strip and method to manufacturing the same. The abrasion strip being composed of a molded amorphous metal contoured to match a leading edge outer surface of the rotor blade. The abrasion strip being configured to removably attach to a leading edge of the rotor blade and configured to prevent damage to the leading edge during flight. The method includes molding the abrasion strip with the amorphous metal.

Abstract: Efficiency of a horizontal axis wind/water turbine (HAWT) is increased by the addition of a secondary blade associated with each main blade. The secondary blade is preferably a blade segment paralleling the main blade only in the outer reach of the main blade. The secondary blade travels rotationally ahead of the main blade and axially behind it, in an area in which air has not been disturbed by the main blades and in which disturbance of air by the secondary blade is not seen by the main blades. In one embodiment the secondary blade is carried by its associated main blade. In another embodiment, the secondary blades are carried by a ring or wheel which rotates with the main blades and the axle to which they are attached.

Abstract: A method for protecting a fan blade with an airfoil, a tip, a root and a sheath, the root to be inserted into a hub includes peening the airfoil of the blade; inserting a scrim cloth between the fan blade and the sheath to galvanically isolate the fan blade from the sheath; bonding the sheath to the blade with an epoxy adhesive; peening the blade root; bonding wear pads to the root with epoxy adhesive to galvanically isolate the root from the hub; applying a protective cover to the tip of the blade; and applying a coating to all exposed areas of the blade to inhibit corrosion.

Abstract: A compressor blade 1 of a gas-turbine engine has a flow-exposed leading edge 2. A component 3, made of wear-resistant material and featuring a higher erosive wear resistance than the base material, is attached to at least part of a length of the leading edge 2 The component 3 forming the flow-exposed leading edge 2 is strip-shaped, has an essentially rectangular cross-section and, with reference to a sectional plane perpendicular to the radial direction, is arranged only on an inflow side of the compressor blade profile in a partial area of a sectional surface of the inflow area.

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 hybrid airfoil for a gas turbine engine is provided that includes a body and a panel. The body has a first side and a second side orientated opposite the first side. The first and second sides extend between a tip, a base, a leading edge and a trailing edge. The body includes a plurality of cavities disposed in the first side of the body, which cavities extend inwardly toward the second side. The cavities collectively form an opening. At least one rib is disposed between the cavities. A shelf is disposed around the opening. The panel is attached to the shelf first mounting surface and to the rib, and is sized to enclose the opening. The panel is a load bearing structure operable to transfer loads to the body and receive loads from the body.

Abstract: An airfoil assembly includes an airfoil body extending between a leading edge, a trailing edge, a suction side, and a pressure side. A first sheath having an outer side and an inner side forms a cavity for receiving at least a portion of the airfoil body and is bonded on the inner side to the leading edge of the airfoil body. The first sheath is formed of a titanium-based metallic material. A second sheath is bonded to the outer side of the first sheath.

Abstract: A production method enables use of ultrasonic forming but does not leave a bonding face in a final product. One cuts into a plate member having a first side face and a second side face from the first side face toward the second side face to form a slit that does not reach the second side face; seals lips of the slit to leave an opening; causes superplastic forming of the plate member by pressurizing the plate member in a mold with gas through the opening; and cuts out a portion including the sealed lips.

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 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: A sheath for a fan airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side includes a solid portion to wrap around the airfoil leading edge; a first wing attached to the suction side of the airfoil; and a second wing attached to the pressure side of the airfoil. At least one of the first wing and the second wing extends at least about 35% of the chord of the airfoil.

Abstract: A blade assembly includes a blade body and at least one sheath assembly located at a leading edge of the blade assembly. The at least one sheath assembly is retained to the blade body in a chordwise direction via an interlocking arrangement between the at least one sheath assembly and the blade body. A tip cap is located at a tip portion of the blade and secured to the blade body thus securing the at least one sheath assembly to the blade body in a spanwise direction. A method of assembling an airfoil includes securing at least one sheath assembly to a leading edge of a blade body via an interlocking arrangement between the at least one sheath assembly and the blade body, and assembling a tip cap to the blade body, thereby retaining the at least one sheath assembly to the blade body in a spanwise direction.

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.

Abstract: A scratch-resistant blade such as an FRP wind turbine blade and a blade protective sheet which can be easily repaired when scratched. A blade is provided with a laminated protective sheet bonded to at least part of a leading edge of an FRP blade body of said blade, wherein the laminated protective sheet comprises an adhesive layer, a intermediate fabric layer and a durable surface layer, in that order from the blade body.

Abstract: A wind turbine blade attached to a hub of a wind turbine generator is provided with a blade body; a first covering layer covering at least a leading edge in a first region including a tip part of the blade body; and a second covering layer covering at least the leading edge in a second region of the blade body, the second region being disposed on a hub side of the first covering layer, and the first covering layer has a higher erosion resistance than the second covering layer.

Abstract: A wind turbine blade comprising an aerodynamic fairing supported along at least a portion of its axial length by a spar (12). The spar comprises at least two spar segments (12) joined end-to-end at an interface (9), each spar segment comprising a shear web (3) with a spar cap (4) on each side. The outer face (6) of each spar cap tapers inwardly towards the interface such that its depth is reduced towards the interface creating a recess on each side of the interface formed by the tapered faces of adjacent spar caps. A respective connection piece (8) is sized to fit into each recess. Each connection piece (8) is sized to fit into each recess. Each connection piece (8) being fixed to the tapered faces of adjacent spar caps to form a double scarf joint.

Abstract: A multilayer protective tape for rotor blades of wind energy turbines said tape having a protective top layer comprising a polymer film and an adhesive bottom layer, wherein the top layer has a continuous surface (S) that is outwardly curved or outwardly trapezoidal surface such that the tape has a cross-sectional profile having an inner section between two lateral sections and wherein the inner section has a thickness (Ti) made up by the thickness of the top layer and adhesive bottom layer that is greater than the thickness of at least one of the lateral sections (T1,T2) made up by the thickness of the top layer and adhesive bottom layer and wherein the thickness (T1 or T2) of at least one lateral section is at most 600 ?m and the thickness of the inner section (Ti) is at least 330 ?m. Also provided are processes for making profiled tapes and methods for applying the tapes to rotor blades and blades containing protective tapes.

Abstract: A wind turbine blade having a lightning protection function includes an outer shell, a spar arranged in a space inside the outer shell, a spar cap which is formed by a carbon-fiber plastic laminated member disposed on a blade root side and a glass-fiber plastic laminated member disposed on a blade tip side that are connected together, the spar cap supporting the spar to the outer shell, and a lightning protection unit. The lightning protection unit includes a receptor for receiving lightning which is provided in the outer shell on a side where the glass-fiber plastic laminated member is arranged, a down conductor which directs lightning current received by the receptor into the ground or the water, and a conductive metal member which covers the outer shell on a side where the carbon fiber plastic laminated member is arranged.

Abstract: A hollow-cast casting is provided, which includes at least one core opening that is caused by the production technique and which has a closure device that closes the core opening. The closure device can be inserted into the core opening axially in relation to the core opening and provides at least one surface region which, in axial projection in relation to the core opening, can be made to abut a surface region of the casting that is facing toward the casting. The surface region lies radially outside a cross-sectional area predetermined by the core opening.

Abstract: A coating is described for an airfoil blade component. The coating comprises a cermet material and has, when applied to the rotor blade, a compressive residual stress greater than about 60 ksi. In another embodiment, the compressive residual stress of the coating is in the range of approximately 90-110 ksi.

Abstract: A gas turbine engine component is described which (100), comprises: a shell having an internal cavity for receiving a multi-part insert; a multi-part insert located within the cavity, wherein the multi-part insert comprises separate insert parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert; an insertion aperture within a wall of the shell which is sized to receive each of the insert parts individually and wherein the multi-part insert cannot be withdrawn from the cavity through the insertion aperture when assembled.

Abstract: Described is a gas turbine engine component (100), comprising a shell having an internal cavity for receiving a multi-part insert; a multi-part insert located within the cavity, wherein the multi-part insert comprises multiple separate parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert; wherein the assembled insert includes at least one retention part, the retention part engaging with a wall of the cavity and at least one other insert part so as to retain the assembled insert within the cavity.

Abstract: A squealer tip formed from a pressure side rib and a suction side rib extending radially outward from a tip of the turbine blade is disclosed. The pressure and suction side ribs may be positioned along the pressure side and the suction side of the turbine blade, respectively. The pressure and suction side ribs may include chamfered leading edges with film cooling holes having exhaust outlets positioned therein. The film cooling holes may be configured to be diffusion cooling holes with one or more tapered sections for reducing the velocity of cooling fluids and increasing the size of the convective surfaces.

Abstract: A platform cooling configuration in a turbine rotor blade that includes platform slot formed through at least one of the pressure side slashface and the suction side slashface; a removably-engaged impingement insert that separates the platform into two radially stacked plenums, a first plenum that resides inboard of a second plenum; a high-pressure connector that connects the first plenum to the high-pressure coolant region of the interior cooling passage; a low-pressure connector that connects the second plenum to the low-pressure coolant region of the interior cooling passage.

Abstract: The invention relates to a wind turbine blade comprising one or more turbulence generating strips, where the strips are placed on a surface of the blade. The blade is characterized in that at least one joint area of the turbulence generating strips and the surface of the blade are completely or partially covered by sealing means. The invention further relates to a pitch controlled wind turbine comprising at least two pitch controlled wind turbine blades and pitch controlling means for pitching the blades. The pitch controlled wind turbine is characterized in that the blades comprises one or more turbulence generating strips, wherein at least one joint area of the turbulence generating strips and a surface of the blades are completely or partially covered by sealing means.

Abstract: A disk made of a first material has a groove in which a blade made of a second material is retained. A strip is placed between the blade and the disk to minimize rubbing damage to the blade and the disk and an insulating material is place between the rub strip and the blade for minimizing damaging responses of the blade to galvanic forces created by rubbing of the first material and the second material.

Abstract: A turbomachine blade having features arranged to initiate bending of the leading edge towards the pressure surface upon impact of a foreign object on the leading edge. The features may be features weaker than the material of the leading edge located on the pressure surface side of a mid-thickness line. By causing the leading edge to bend towards the pressure surface on impact the volume of the foreign object, typically a bird, that passes over the suction surface is reduced.

Abstract: The present invention relates to an aerofoil blade comprising a root, a tip, a leading edge and a trailing edge. At least part of the tip and at least a part of the trailing edge of the blade are reinforced by at least one portion of drapable reinforcing material wrapped around the tip and trailing edge.

Abstract: The present invention relates to a wind turbine component, having a connecting portion for connecting the wind turbine component to another turbine component and at least part of the connecting portion is formed of a first type of metal, characterized in that: the connecting portion is further provided with an additional part formed of a second type of metal which is connected to the metallic part of the connecting portion; and the second type of metal is more active than the first type of metal, whereby the additional part forms a sacrificial anode. The present invention further relates to a wind turbine having the above component.

Abstract: A squealer tip preform having a coating including an abrasive is disclosed. The squealer tip may be separately formed from a generally elongated blade to which the squealer tip preform is configured to be attached. The squealer tip may be configured such that an outer surface of the squealer tip preform is generally aligned with an outer side surface of the turbine blade defining a cross-sectional profile of the turbine blade. Forming the squealer tip preform with an abrasive coating separate from the turbine blade greatly reduces costs and improves efficiency as compared with conventional systems.

Abstract: A structural and acoustical vibration dampener for a rotatable blade comprises a layer of structural/acoustic damping material coupled to at least a portion of the blade. A fan blade comprises a structural layer and a layer of damping material coupled to at least a portion of the structural layer. A method of applying a structural and acoustical vibration dampener to a fan blade comprises identifying a region on the fan blade and securing the structural/acoustical vibration dampener to the fan blade over at least a portion of the region.