Abstract: A guide vane device for a turbine has an inner platform with a through hole forming a fluid channel for a cooling fluid, wherein the inner platform extends in a circumferential direction around a shaft of the turbine. The guide vane device further includes a hollow aerofoil with a cooling opening for exchanging the cooling fluid passing the through hole into or from the hollow aerofoil, wherein the hollow aerofoil is fixed to a first surface of the inner platform, and a rail with a recess with a cooling fluid passage forming a passage for the cooling fluid to the through hole, wherein the rail is fixed to a second surface of the inner platform and the rail extends along the second surface in the circumferential direction around the shaft. The cooling fluid passage has in the circumferential direction at least the dimension of the through hole.

Abstract: A turbomachine rotor includes a rotor blade mounted to a rotation element. The rotor blade includes a root for mounting the rotor blade to the rotation element. The root has a protrusion structure forming a stop face supporting the mounted root against the rotation element under action of a radially inwardly directed force. The protrusion structure defines a maximum clearance between the stop face and the rotation element. The root is radially moveable to a certain extent where in a radially outermost position the protrusion structure has the maximum radial clearance from the rotation element. The rotation element includes a groove therein. The groove has a groove face bearing the stop face of the rotor blade under action of a radially inwardly directed force. The groove is a circumferential groove extending in a circumferential direction with regard to an axis of rotation of the rotation element.

Abstract: A method of manufacturing a metal component from metal powder comprises preparing (12) a metal powder, providing (14) gallium on at least part of the surface of at least some of the metal powder particles, encapsulating (16) the metal powder in a container, evacuating (18) the container to remove air and/or gas from the container, sealing (20) the container, hot isostatically pressing (22) the container to consolidate the metal powder particles to produce the metal component and removing (24) the container from the metal component. The process is used to produce gas turbine engine metal components, for example turbine discs with improved fatigue properties.

Abstract: An apparatus for performing a supporting and/or a lifting operation to a wind turbine component inside the wind turbine nacelle is provided. The apparatus comprises at least a tool which comprises a manually operated linear actuator and a mounting device of said linear actuator in an element of the nacelle frame so that said linear actuator can be duly located with respect to the wind turbine component for performing said supporting and/or lifting operation.

Abstract: An airfoil and method of fabricating an airfoil including a first and a second side coupled together at a leading and a trailing edge and extending there between. The airfoil includes a plurality of first chord sections having a first chord length and extending outward from one of the first side or second side of the airfoil at the leading edge and a plurality of second chord sections having a second chord length and extending outward from the one of the first side or the second side of the airfoil at the leading edge. The leading edge including spaced-apart wave-shaped projections defining a waveform. The configuration defining a three-dimensional crenulated airfoil configured to facilitate desensitization of an airfoil unsteady pressure response to at least one impinging upstream generated wake or vortex by decorrelating spatially and temporally and reducing in amplitude an unsteady pressure caused by interaction of the airfoil with the upstream generated wake or vortex.

Abstract: A manufacturing method of a thin fan comprises the steps of: providing a plastic material containing a plurality of metal particles; molding the plastic material into a housing; removing a part of a surface of the housing to form a circuit layout area at the housing; and forming a metal layer in the circuit layout area.

Abstract: A windmill having a hub sealing apparatus for sealing an interface between a hub and a blade of the windmill, The hub sealing apparatus includes a bottom sealing ring configured to be sealed to the hub, a top sealing ring configured to be rotatably sealed to the blade, and a middle sealing ring configured to be sealed to the top sealing ring and the bottom sealing ring, so as to connect the top and bottom sealing rings.

Abstract: A lifting device configured to autonomously position a wind turbine blade in such a way that it can be mounted on a wind turbine tower. The lifting device (1) comprises a boom structure (2) and is furthermore provided with a positioning device (4) which is connected to the boom structure and can be displaced along the latter. The positioning device comprises a mounting structure (4f) for detachably mounting the wind turbine blade on the positioning device. The boom structure (2) and displacement structure (4a) of the positioning device (4) form an assembly for the approximate positioning of the mounting structure (4f) with respect to the wind turbine tower. The positioning device (4) furthermore comprises additional means (4d, 4e) for accurately positioning the wind turbine blade with respect to the wind turbine tower.

Abstract: A manufacturing method of an impeller includes forming a plurality of blades integrally on a blade attachment surface of one of a disc and a cover, placing the cover on a floor so as to face up the blade attachment surface of the cover, disposing the disc on the cover so as to face down the blade attachment surface of the disc, and bonding the plurality of blades to the blade attachment surface of the other of the disc and the cover which is not formed integrally with the plurality of blades by using a bonding material.

Abstract: A method to manufacture an integrally bladed rotor, including: cutting a block of material by an abrasive waterjet, undertaken so as to reveal blade preforms extending radially from a disk, while retaining the material forming a linking mechanism between at least two preforms of directly consecutive blades, wherein the linking mechanism is spaced radially from the disk; followed by removal of the linking mechanism.

Abstract: A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation, the rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals which extend from the rotor ring opposite the ramped interface.

Abstract: The invention aims at achieving a mounting of a turbomachine stator blading while avoiding a delicate machining process of the engine casing. It also aims at simplifying the mounting as well as at reducing the costs, and at decreasing the number of item references for the engine. To achieve these objects, the invention uses an extension of the engine casing. A turbomachine comprises at least one stator blading for air or gas stream flowing on the internal engine casing. The stator blading comprises a rim which is assembled on a radial extension of engine casing with axial fastening means. In a preferred embodiment of the turbomachine, the engine casing presents an annular wall provided with fingers originating axially from this wall and extending according to a curvature so that they present a radial extension tip against the rim of the stator blading.

Abstract: A process for manufacturing a single-piece blisk, including: using an abrasive water jet to cut a block of material, so as to create blade preforms extending radially outwards from a disk, while keeping material forming a connecting mechanism between at least two directly consecutive blade preforms; then milling on the blade preforms so as to obtain profiled blade blanks; then a finishing by milling of the blade blanks, so as to obtain blades with a final profile; then removing the connecting mechanism.

Abstract: A stator ring for use in a compressor of a gas turbine engine and a method of assembling the stator ring are provided. The stator ring includes a first plurality of segments that includes a first segment including a first circumferential end formed with a first cut and a second circumferential end formed with a second cut that is complementary to the first cut, wherein the first plurality of segments are configured to be circumferentially-coupled together, and a second plurality of segments that includes a second segment including a first circumferential end with a third cut and a second circumferential end with a fourth cut that is complementary to the third cut, wherein the second plurality of segments are configured to be circumferentially-coupled together.

Abstract: A rotor having a first low temperature material section, a second low temperature material section attached to a first end of the first low temperature material section and a third low temperature material section joined to a first end of the second low temperature material section. The first, second and third temperature material sections are exposed to steam at a pressure less than about 180 bar. A steam turbine and a method for producing a rotor are also disclosed.

Abstract: A method for forming an inclined-blade blower wheel is provided by arranging a plurality of blades about respective circumferences of first and second end caps. The plurality of blades extend longitudinally between the first and second end caps and parallel to an axis defined by respective centers of the first and second end caps. The first end cap is rotated with respect to the second end cap a predetermined amount, therein skewing the plurality of blades at a desired longitudinal pitch between the first end cap and second end cap. The first end cap and second end cap are then rotated in unison while crimping the circumferences of the first end cap and second end cap, therein securing the plurality of blades to the first and second end caps and fixing the desired longitudinal pitch of the plurality of blades from the first end cap to the second end cap.

Abstract: A tie rod for extending between a fan shroud and a shaft cap in a rotative assembly includes a first end with threads; a second end with threads; and an elongated portion between the first end and the second end. The tie rod has diameter to length ratio of about 1 to 40.810 to about 1 to 40.768.

Abstract: A ram air fan bearing housing for a ram air fan assembly includes a bearing section, a disk section, and radial support ribs. The disk section is at one end of the bearing section for connecting the bearing section to the ram air fan assembly. The disk section includes an outer ring with a circumferential support rib; and a disk wall connecting the outer ring to the bearing section. The disk wall includes arcuate cooling slots defined by edges, including an arcuate edge having an arc center at an axis of the bearing housing and positioned adjacent to and radially inward from the circumferential support rib. The radial support ribs extend axially along most of the length of the bearing section and extend radially along the disk wall to the circumferential support rib. The radial support ribs and the cooling slots alternate about the axis of the bearing housing.

Abstract: A welding method for an impeller having a plurality of blades, a disc and an exterior body including a shroud welded to the plurality of blades, comprising the steps of: a first step for forming a groove having a prescribed depth and a prescribed width toward one of the blades on a surface of the disc or the exterior body, which is opposite to a surface against the blade abuts, emitting laser light toward the bottom of the groove, and performing melt-through bead welding to bond the bottom of the groove to an end of the blade in such a way that a bead formed on the back of the disc or the shroud is curved with an inward depression; and a second step for performing overlaying welding after completion of the first step by supplying a filler metal to a molten zone while the bottom of the groove is scanned with the laser light.

Abstract: The present application thus describes a method of manufacture for a late lean injection system in a combustor of a combustion turbine engine.

Abstract: A rotor for an electric rotating machine includes a core body member formed with laminated core plates and a pair of end plates sandwiching opposing ends of the core body member. An output member is connected to an inner peripheral portion of one of the end plates with a connecting member. A first through-hole for allowing an insertion of the connecting member is press formed from the direction opposite to the direction outer and inner peripheral portions of the one of the end plates are press formed. Shear-droops formed at the outer and the inner peripheral portions of the one of the end plates during the press forming are arranged on the surface opposite to the surface thrusting the core body member. A shear-droop formed at the first through-hole during the press forming is arranged on the surface of the one of the end plates thrusting the core body member.

Abstract: It is intended to provide a power generating apparatus of renewable energy type in which a braking mechanism is attached to a rotor arranged upstream of a hydraulic transmission while saving space, and a method of attaching and detaching a blade for the apparatus. The power generating apparatus of renewable energy type is provided with: a rotor having a hub and a main shaft, the hub having at least one blade mounted thereon, the main shaft being coupled to the hub; a generator which generates power by torque inputted from the rotor; and a hydraulic transmission which transmits the torque from the rotor to the generator. A brake disc is fixed to the rotor by tightening together with the hub and the main shaft. A brake caliper is provided to force a brake pad against the brake disc to apply a braking force to the rotor.

Abstract: A blade attaching method is provided for a power generating apparatus which may include a blade, a hub having a blade attaching part, a bearing, a generator, and a pitch drive mechanism. The method may include, but is not limited to: a step of attaching a suspension device to the blade; a step of lifting the blade; a step of holding the blade so that the blade attaching part of the hub faces the blade root part of the; a step of rotating the blade attaching part by the pitch drive mechanism to a set angular position while holding the hub; and a step of fixing the blade to the hub after rotating the blade attaching part to the set angular position.

Abstract: A torque converter including a cover with at least one slot located about a periphery and a pump with at least one protrusion located about a periphery of the pump. The protrusion extends axially through the slot and is bent radially about the slot to join the cover and the pump. In some aspects, the converter includes a sealing element disposed between the cover and the pump and the sealing element is selected from the group consisting of an o-ring and a gasket. A method of transferring torque including: inserting at least one peripherally disposed protrusion for one of a pump and cover of a torque converter through at least one peripherally disposed opening in the other of the pump and cover, radially bending the protrusion to clamp the cover and pump, and transmitting torque from the cover to the pump through the protrusion.

Abstract: A bladed rotor includes a blade lock mountable to a rotor hub adjacent to a multiple of blade slots. The blade lock includes at least one interface feature adjacent to a first of the multiple of blade slots. A first rotor blade includes a blade feature which interfaces with the interface feature to permit the first rotor blade to be axially mounted within the first of the multiple of blade slots but not within a remainder of the multiple of blade slots.

Abstract: A part-holding device in a method for repairing a blade of a monobloc bladed disc of a turbo-machine, through electron-beam welding of a patch onto the blade along a junction plane is disclosed. The device includes a disc supporting device which supports the disc and an adjustable holding device which holds the blade and the patch. The adjustable holding device includes a platen which supports the adjustable holding device, arranged such that the space located above the junction plane allows for an electron beam to pass. The relative positions of the blade and the patch are set using the adjustable holding device that is supported by the platen, while leaving some space allowing for an electron beam to pass. Such a device is simple and reliable.

Abstract: A gas turbine engine includes a gas turbine engine internal compartment structure having an integral passageway. Wiring is routed through the integral passageway of the gas turbine engine internal compartment structure.

Abstract: A method and apparatus for fixturing an airfoil stub during linear friction welding are described. Critical clamping support structures are manufactured by a direct digital manufacturing process such as direct metal laser sintering to minimize time and expense of the process.

Abstract: A system includes a turbine. The turbine includes a first turbine blade comprising a leading edge, a blade platform coupled to the first turbine blade, and a protrusion disposed on the blade platform adjacent the leading edge of the first turbine blade. The protrusion is configured to increase a first static pressure of a cooling flow near the leading edge above a second static pressure of a hot gas flow near the leading edge.

Abstract: There is provided a vertical axis wind turbine comprising an upright rotatable shaft mountable on a support structure, a plurality of upright blades, and a plurality of prestressable supporting arms for attaching the plurality of blades to the shaft. The wind turbine may further comprise a shaft stabilizing assembly comprising a plurality of coplanar wheels having compliant outer layers, rotatably mounted on a support, for radially and rotatably supporting a rotatable shaft. The disclosure further provides a method of assembly of the wind turbine.

Abstract: A method of fabricating an integrally bladed rotor of a gas turbine engine according to one aspect, includes a 3-dimensional scanning process to generate a 3-dimensional profile of individual blades before being welded to the disc of the rotor. A blade distribution pattern on the disc is then determined in a computing process using data of the 3-dimensional profile of the individual blades such that the fabricated integrally bladed rotor is balanced.

Abstract: A wind turbine is described. The turbine includes a hub with one or more blades that rotatably mounted on a frame and operatively coupled to a shaft. The shaft is provided at least partially internally to the frame, and a center piece from which a plurality of spokes extends substantially radially is mounted on the shaft. The hub is provided with a plurality of circumferentially arranged axial protrusions. Flexible elements are arranged to connect the spokes to the protrusions.

Abstract: A method of fabricating an integrally bladed rotor for gas turbine engines according to one aspect includes a step of positioning a blade on a hub in a joining procedure by using a priority surface of the blade as a reference surface.

Abstract: Within the field of wind turbine generators (WTG), to provide a consistent way of manufacturing a WT blade there is disclosed a blade mould and a blade spar fixture to support the spar in the mould so as to provide a fixed predetermined relative position, and preferably also orientation, between at least a root end, such as a bushing in the root end of the blade spar, and a root end of the mould. Overall consistency is also obtained in that hereby a blade with anticipated aerodynamic and strength characteristics is provided, among others in that at least adjacent to the root of the spar there is substantially the same distance for a cured adhesive between an innermost surface of each of blade shells and an outermost surface of the spar.

Abstract: A method of forming a component for use in a gas turbine engine includes the steps of forming an airfoil/root assembly; creating a platform assembly structure having an opening; inserting the airfoil/root assembly into the opening; and bonding the platform assembly structure to the airfoil/root assembly to form the component.

Abstract: A method of repairing a bearing of a wind turbine generator is provided which is able to more permanently repair a gap which occurred between a constituent member of the wind turbine generator and a bearing ring of the bearing. For example, in the case of repairing the gap 13 between the main shaft outer cylinder 10 of the wind turbine generator 1 and the outer ring 12A of the main bearing 12, the plate 40 is inserted between the main shaft outer cylinder 10 and the outer ring 12A, and also the plate 40 is fixed to an inner circumferential surface of the main shaft outer cylinder 10 by the adhesive agent 41. On the other hand, slip is permitted between the plate 40 and the outer ring 12A of the main bearing 12.

Abstract: A method for machining components of a gas turbine, in particular for machining turbine blades, is described. The method includes the following steps: a) providing at least one component carrier having at least one component receptacle for detachable accommodation and fastening component to be machined, the component receptacle being designed with a contour similar to at least one contour of subarea of component to be accommodated; b) introducing at least one subarea of the component into component receptacle and form-fitting and/or substance-to-substance bonding of the subarea of the component to component receptacle; c) machining the component, which is attached to the component carrier; and d) releasing the machined component from the component carrier.

Abstract: A blade of a turbomachine or a flying machine includes a blade airfoil extending in a radial direction from a blade root to a blade tip. The blade airfoil has an inflow-side leading edge, an outflow-side trailing edge, a pressure side and a suction side. A surface of each of the pressure side and the suction side extends between the inflow-side leading edge and the outflow-side trailing edge. The blade tip has an end face with a camber line that extends from the inflow-side leading edge to the outflow-side trailing edge. At least one tip-side recess forms a depression from the end face into the blade airfoil, the depression extending continuously from the pressure side to the suction side and having a partial length of the camber line.

Abstract: A method for assembling a wind turbine includes: unloading a nacelle and hub from a truck; connecting the nacelle and hub to a carriage of an elevator in a vertical position; connecting blades to the hub, thereby forming a rotor; raising the carriage, nacelle, and rotor along a tower to a top of the tower; and pivoting the carriage, nacelle, and rotor to a horizontal position at the top of the tower.

Abstract: A rotor assembly for a gas turbine engine including a circumferential array of regularly spaced apart features provided on the disk which are each configured for receiving a balancing weight. The circumferential array of features has an angular orientation relative to the circumferential array of blades such that the features are each located at an at least substantially same offset angle from a stacking line of a respective adjacent blade.

Abstract: A composite of a magnesium part or a magnesium alloy part and a resin composition, improved to have high corrosion resistance, is manufactured by: a step of shaping a magnesium alloy part 1 from a casting or an intermediate material; a step of immersing and chemically etching the shaped part in an acidic aqueous solution; a step of immersing the chemically etched shaped part in an aqueous solution containing potassium permanganate and forming on the surface thereof a thin layer having manganese oxide as a component; a step of inserting the part, on which the thin layer has been formed, into a metallic mold for injection molding and injecting into the mold a resin composition selected out of a resin composition whose main component is polyphenylene sulfide, a resin composition whose main component is a polybutylene terephthalate resin and a resin composition whose main component is an aromatic polyamide resin and then integrally affixing the magnesium alloy part 1 and the resin composition 4; and a step of sub

Abstract: In a manufacturing method of an impeller for a fluid transmitting device, multiple guide grooves aligned in a peripheral direction to allow communication between adjacent ones of multiple positioning holes are provided in a concave inner surface of a core in advance; and in a step of melting a brazing material and causing the molten brazing material to penetrate into gaps between coupling pieces and positioning holes that are fitted to each other and further into gaps between the core and the blades, the molten brazing material is guided to the positioning holes through the multiple guide grooves. Accordingly, the step allows the molten brazing material to be efficiently guided to the gaps between the coupling pieces and positioning holes, thereby improving the yield of the brazing material and preventing an influence of a residual brazing material over the rotational balance of the impeller.

Abstract: A bidirectional turbine blade including: a blade root and blade tip; a first face and a second face running between the blade root and blade tip; a cross-sectional profile which is symmetrical about a chord line extending between longitudinal edges of the blade; and a twist of between about 5 and 35 degrees from the chord line, wherein the blade is capable of driving an underwater turbine from flowing water incident at the first face or the second face.

Abstract: A weld set-up and weld process are provided that alleviate micro-cracking as between a pair of welded pieces. The weld set-up is provided in which the weld pieces are configured to cause micro-cracking to occur in a portion of the welded pieces that is then removed by post-processing machining techniques. This weld set-up includes a primary weld piece and a secondary weld piece with a flange portion that extends over the primary weld piece. When used in conjunction with electron beam welding, application of the weld beam onto the secondary weld piece causes the formation of a preferential nailhead that is formed exclusively in the first weld piece.

Abstract: A method of conditioning a first, heterogeneous contact surface for operational engagement with a second contact surface, the method comprising: performing a smoothing operation on part or all of the first contact surface whilst subjecting said part or all of the first contact surface respectively to a contact pre-stress corresponding to a nominal operational contact stress between the first and second contact surfaces.

Abstract: The invention relates to a sectional blade for a wind turbine, the blade comprising at least a first blade section and a second blade section extending in opposite directions from a blade joint, where each blade section comprises a spar section forming a structural member and extending in the longitudinal direction of the blade, and where the first and second blade sections are connected by fastening means restraining any movement of the first blade section relative to the second blade section length ways. The first and the second blade sections are structurally connected by a spar bridge protruding from one of the blade sections and terminating axially in an end portion, which is received in the spar section of the other blade section. The spar bridge and the spar section have interlocking shapes by which rotation of the spar bridge in the spar section is prevented thereby preventing rotation of one of the blade sections relative to the other.

Abstract: A spinner configured to be mounted on a hub of a wind turbine to which at least one rotor blade is connected. The spinner defines a front portion configured to be positioned in front of an inner portion of the at least one rotor blade, and is structurally configured to cover a substantial portion of the inner portion of the at least one rotor blade in a wind direction during operation of the wind turbine. Further described is a wind turbine comprising the above-described spinner and a method for increasing the efficiency of an existing wind turbine, wherein the method includes mounting the above-described spinner to the hub of a wind turbine.

Abstract: A method for reducing vibration levels in a turbomachine including at least a first and a second bladed wheel, due to aerodynamic perturbations that are produced by the second bladed wheel or an obstacle on the first bladed wheel is disclosed. The method includes: defining an initial configuration of the blades; calculating the synchronous forced response on the first bladed wheel as a function of the harmonic excitation force produced by the second bladed wheel expressed in the form of a linear function of the generalized aerodynamic force for the mode considered; determining a geometric tangential shift value ? for the stacked cross sections of one of the two wheels to reduce the corresponding term to the generalized aerodynamic force. The set of cross sections with the tangential shifts thus defines a new configuration of the blades of one of the two wheels.

Abstract: A method for machining a gas turbine rotor which is provided with a cooling air slot which concentrically extends around the axis of the gas turbine rotor and is supplied with compressed cooling air via axial cooling air holes which at the side lead into the slot base of the cooling air slot, and the opening of which is covered by bridges which are arranged in a distributed manner over the circumference and spaced apart from each other by gaps. A crack-resistant slot shape is achieved without intervention into the configuration of the bridges by a material-removing tool, particularly a milling tool, being lowered in the gaps between the bridges one after the other into the cooling air slot and in this way the slot base of the cooling air slot being machined and widened over the entire circumference.

Abstract: A wind turbine is formed of a concrete tower which is erected by slip forming. A primary lifting device is erected onto the tower by being lifted together with the slip form and being subsequently transferred onto the tower from the slip form after the tower has been formed. The nacelle, generator, and rotor of the turbine are then lifted onto the tower using the primary lifting device. A secondary lifting device supported on the tower is used to lower the primary lifting device to the ground after the nacelle, generator and rotor are assembled. The height of the tower is therefore not limited by the availability of suitable cranes so that a greater height of tower can be erected to take advantage of winds at greater elevation.