Abstract: An annulus filler element (40) for a rotor of a turbomachine, the annulus filler element (40) comprising: a lid portion (42) having a radially outwardly facing surface for forming an inner wall of a flow annulus of the rotor between adjacent blades (102) and a radially inwardly facing surface; and a nose cone attachment portion (52) integrally formed with the lid portion (42) for connection with a nose cone (122) of the turbomachine.

Abstract: An axial-flow compressor for a gas turbine engine has a rotor drum (2) in thermally lower loaded first compressor stages (3 to 6) which includes a one-piece ring, or rotor rings (7 to 10) attached to one another. Fiber belts (18, 21) are wound onto these rings close to the rotor blades and include carbon fibers embedded in a high-temperature resistant polymer matrix. As the rotor disks can be dispensed with, since their function will be assumed by the fiber belts, the compressor features low weight, requires limited space only, and, in addition, can be produced cost-effectively.

Abstract: The invention relates to a process for manufacturing a blade connection of a rotor blade for a wind energy system which comprises fastening elements for fastening the blade connection to a hub, which fastening elements are provided on a circular arc, preferably equidistant from each other. Furthermore, the invention relates to a blade connection and a fastening element for a blade connection. The invention is based on the problem of improving the fastening of a rotor blade on the hub of a wind energy system as well as improving the manufacture and/or making a suitable blade connection available. The invention solves this problem as regards the process in that fastening elements formed in pieces are arranged on the circular arc and spaced from each other with spacer elements.

Abstract: A gas turbine engine fan section is disclosed that includes a hub. Circumferentially spaced fan blades are supported on the hub. A spacer is arranged between adjacent fan blades and is operatively supported by the hub. The spacer is configured to be collapsible in response to a fan blade load exerted on the spacer in excess of a threshold load. The spacer is generally rigid at fan blade loads below the threshold load.

Abstract: Method and impeller cover for protecting an impeller from damage. The impeller cover includes a removable body having a first face and a second face opposing the first face, the second face being configured to match a front face of the impeller of the compressor, and further having a frontal portion covering an entire frontal portion of the impeller of the compressor, and a fixing mechanism connected to the removable body and being configured to fix the impeller cover to the impeller of the compressor. The impeller cover is disposable.

Abstract: A dual-component locking spacer assembly for insertion in a circumferential dovetail slot includes a stationary member having a platform configured to fit into a space between the adjacent rotor blade platforms. A first leg extends transversely from an underside of the platform. A longitudinally extending groove is defined in the platform. A slide member is movably engaged with the stationary member along the groove, and includes an upper plate and a second leg connected to the upper plate. The slide member is movable along the groove between a first unlocked position wherein the first and second legs are spaced apart a first distance so as to be insertable into the dovetail slot, and a second locked position wherein the first and second legs are spaced apart an extended second distance so as to engage against opposite walls of the dovetail slot and lock the stationary member in position in the dovetail slot.

Abstract: A removable rotor blade platform includes a first platform leg, a second platform leg, and a platform portion coupled to the first and second platform legs. The first platform leg is configured to be retained by a first retainer coupled to a first rotor blade, and the second platform leg is configured to be retained by a second retainer coupled to a second adjacent rotor blade. A method of assembling a blade assembly that includes a removable platform, a rotor assembly including the removable platform, and a gas turbine engine assembly including the removable platform, are also described herein.

Abstract: A turbine blade with a detached platform in which the platform has a central opening in which the blade is inserted and held in place. The blade includes a root portion with a fir tree configuration to fit within a slot of a rotor disc. The platform includes two legs that also have a fir tree configuration to fit within the slot of the rotor disc. The blade is inserted into the central opening and the fir tree configurations of the blade root and the platform legs form substantially an aligned set of fir trees that fit within the rotor disc slot to retain both the blade and the platform within the slot. The blade is therefore separated from the platform such that thermal stresses are uncoupled. Also, the blade can be made from a different material than is the platform. The centrifugal load applied to the platform is not transferred onto the blade.

Abstract: A turbomachine rotor blade comprising a root (14) mounted in a channel of the periphery of a disk and held by an annular flange (18) which presses on the root (14) of the blade (12), this root comprising a stop (44) engaging in a matching cavity of the flange in order to stop it rotating about the axis of the disk, the central portion of the stop having a thickness less than that of the ends of the stop.

Abstract: A turbine rotor improved in machinability, appropriately balanced in stress, and having rotor hooks and rotor necks constructed to form an attachment structure with respect to an inverted fir tree blade root that has blade hooks and blade necks. The turbine rotor has rotor hooks and rotor necks constructed to form an attachment structure with respect to an inverted fir tree blade root that has blade hooks and blade necks with an “n” number of hooks, where n?3. In this structure, a convex portion of the innermost circumferential rotor hook is formed to be concave in a circumferential direction, with respect to a tangential line that connects a convex portion of the (n?1)th hook from the outermost circumferential rotor hook, and a convex portion of the (n?2)th hook.

Abstract: A method of handling a wind turbine blade during storage, transport or mounting of the blade is presented. The method comprises the steps of: establishing at least one mounting hole penetrating the surface of the blade, mounting one or more handling means including mounting means in said at least one hole, and handling the wind turbine by at least said handling means on the wind turbine blade. A handling system and handling means for handling a wind turbine blade as well as a wind turbine blade and use hereof are also disclosed.

Abstract: A method for assembling a stator assembly for a turbine engine is provided. The method includes providing a blade with a base including an end wall having at least one hole defined therein and providing a shim having at least one aperture extending therethrough. The shim aperture is aligned with the end wall hole, and the shim is secured to the blade base end wall using a fastener. The fastener is inserted through the shim aperture in an interference fit within the end wall hole. The blade and the shim are coupled to a turbine casing.

Abstract: A steam turbine blade includes a blade; a shroud attached to a tip of the blade; a blade root projecting toward the radial inner circumferential side of a turbine rotor so as to be fitted into a blade groove provided in an outer circumferential portion of a turbine rotor; and a platform disposed between the blade and the blade root. The blade root is inserted into the blade groove along the axial direction of the turbine rotor. The blade, the shroud, the blade root and the platform are integrally molded. The number of the blade roots is larger than that of the blades.

Abstract: A locking arrangement for locking a hub (1) of a wind turbine against rotational movement is disclosed. The locking arrangement comprises at least one first locking part (6) and at least one second locking part (8). The first locking part(s) (6) is/are movable along a substantially radial direction relative to the rotational axis of the hub (1), between a locking position and a release position. Each second locking part (8) is adapted to retain a first locking part (6) when the first locking part (6) is in the locking position. The first locking part(s) (6) and the second locking part(s) (8) are arranged with one of them on the hub (1) and the other one on the base frame (5). Thereby, a first locking part (6) and a second locking part (8) prevent rotational movement of the hub (1) relative to the base frame (5) when the first locking part (6) is in the locking position, and allow such movement when the first locking part (6) is in the release position.

Abstract: In a turbine rotor, a rotor radial-direction hook length (Hri) of an i-th rotor hook counting from the outermost circumference of the rotor and a blade radial-direction hook length (Hbi) of an i-th blade hook counting from the outermost circumference of the blade are set to satisfy the relationship of (Hri>Hbi). In the turbine blade, a rotor circumference-direction neck width (Wri) of an i-th rotor neck counting from the outermost circumference of the rotor and a blade circumference-direction neck width (Wbi) of an i-th blade neck counting from the innermost circumference of the blade are set to satisfy the relationship of (Wri>Wbi).

Abstract: A shim for a turbomachine blade is disclosed. The shim includes two branches which wrap around flanks of a blade root, and two tabs. Each of the tabs extend from one end of a respective one of the two branches. The tabs are folded towards each other and are interconnected in such a manner as to prevent them from unfolding. Advantageously, the shim includes a connection part which interconnects the tabs in such a manner as to prevent them from unfolding. The connection part is assembled to the tabs in such a manner as to allow the branches of the shim to spread apart. For example, the connection part can be suitable for stretching in the direction for spreading the branches apart.

Abstract: It has already long been known to use mobile cranes for mounting rotor blades to a wind power installation. Such cranes pick up the rotor blade at the base of the wind power installation and take it to the rotor blade connection of the hub of the wind power installation so that the rotor blade can be connected to the hub. That connection is usually made by screw means, in which case screw bolts are let into the connecting flange of the rotor blade and project into corresponding bores in the rotor blade connection of the hub so that nuts can be screwed on to the screw bolts. The object of the invention is attained by a blade mounting method having the features of claim 1. Advantageous developments are set forth in the appendant claims.

Abstract: A wind energy plant with a rotor hub which is connected to at least one pitch bearing, and with at least one rotor blade, the blade root of which is connectable to the pitch bearing via joining means, wherein a stiffening element is provided, which is arranged between the rotor blade root and the pitch bearing and connected to the same via the joining means.

Abstract: A fan blade anti-fretting insert is described whereby to reduce wear between the root portion of a fan blade and the root slot of the rotor fan hub of a turbo fan engine to which the fan blade are secured. The anti-fretting insert can be formed of a composite spring material having a memory and is dimensioned and shaped to be fitted between the fan blade platform and the outer surface portion of the rotor fan hub between adjacent fan blades, whereby to apply a pushing force against the platform and consequently to the fan blades secure thereto thereby applying a resulting pulling force on the root portion of the fan blades to prevent rocking of the root portion in their root slots formed in the rotor fan hub.

Abstract: A shroudless turbine rotor blade of the type having a platform damper interface, is provided with at least one slot which extends from the aerofoil side of a platform flow boundary to a point in the root. The slot extends between opposing flanks of the blade so as to divide the platform and partially divide the root. The segregated root is made more flexible by the slot which provides for greater platform vibratory amplitudes for a given length of root. The increased platform motion provides for improved dampability when the blade vibrates. The slot also provides a pair of confronting platform surfaces which are urged into mutual contact by centrifugal load acting on the blade to create an additional damping interface.

Abstract: A wind turbine wiring enclosure cabinet is provided having a housing and an electrical circuit connection means. The housing has a top surface, a bottom surface, and a sidewall in contact with the top surface, the top surface having a plurality of apertures formed therein. The housing has an interior, and the sidewall has at least one door accessing the interior. The electrical circuit connection means includes a plurality of non-conductive vertical members, and a plurality of conductive elements having connected thereto a plurality of connector retention means. Each connector retention means has a slot formed therein for insertion therein of a lay-in lug assembly, Each non-conductive vertical member has two sidewalls with an intermediate wall connected to each of the two sidewalls. The apertures formed in the top surface are arranged in a plurality of groups, as are the apertures formed in the bottom surface.

Abstract: A turbine blade assembly, which can be used for a gas turbine is provided. The turbine blade assembly includes turbine blades with platforms, gaps between the platforms of adjacent turbine blades and seals. Each seal covers the gap between the platforms of two adjacent turbine blades wherein the platforms are provided with slots extending in the downstream flow direction. The turbine blades have root cavities, wherein the seal covers at least the whole length of the root cavities of two adjacent turbine blades. The seal is formed from a strip and the seal is placed in two opposed slots formed in each of the platforms of two adjacent turbine blades and open towards the respective downstream ends.

Abstract: A damper for a turbine rotor assembly of a gas turbine engine is disclosed. The damper may have a forward plate. The damper may further have an aft plate including a larger surface area than the forward plate. The aft plate may have at least one aperture for regulating a flow of through the aft plate. The damper may also have a longitudinal structure connecting the forward plate and the aft plate.

Abstract: A tower includes an outer portion forming an outer covering for the wind turbine tower and an inner portion disposed within the outer portion. The inner portion includes a preassembled power module including an upwardly extending support and electrical components that extend outwardly beyond the upwardly extending support and guide supports coupled at a first end to the upwardly extending supports and extending outwardly beyond the electrical components.

Abstract: A wind turbine blade includes a permeable flap extending from a trailing edge of the blade.

Abstract: the present invention relates to a table for a wind turbine equipped with attachment devices 103 for attaching servicing equipment, 401, 402, said attachment means being attached at and accessible from the blade exterior. They may be located in cavities and be covered when not in use. Hereby it is accomplished that the blade can be serviced and repaired while positioned horizontally without the attachment devices as such otherwise influencing the aerodynamic properties of the blade. One possibility is that during manufacturing such a cavity is closed but the cavity can later be broken open. Additionally, the invention relates to a wind turbine featuring such blade and a method of servicing a blade when mounted on a wind turbine, wherein servicing equipment is attached to at least one attachment device in the blade. It is furthermore mentioned, that the attachment devices might be used when mounting a blade.

Abstract: A rotor blade for a wind power installation comprises a plurality of holes which are arranged in the region of the rotor blade root and which are in the form of through holes which extend substantially transversely with respect to the longitudinal axis of the rotor blade. Transverse pins are fitted into the holes. The tension elements are connected to the transverse pins. In that arrangement the tension elements in the state of the art extend within the rotor blade root and thus weaken the material in that region. In order to eliminate those disadvantages by means of a structural simplification, the rotor blade according to the invention is characterized by tension elements extending outside the rotor blade root.

Abstract: A fluid catchment system for a wind turbine is provided. The wind turbine has a nacelle mounted to a tower. The fluid catchment system includes at least one fluid accumulator in fluid communication with the interior of the nacelle and configured to receive fluid exiting from the nacelle. The fluid accumulator is configured to be positioned at least partially beneath the nacelle and to be attached to at least one of the tower and the nacelle. An oil absorbent material may be retained by the fluid accumulator. A fluid collector may be provided to collect fluid from the fluid accumulator. A fluid catchment system having a fluid accumulator located on a wind turbine blade is also provided. Further, a wind turbine including a fluid catchment system is provided.

Abstract: A rotor of a turbo engine, e.g., a gas turbine rotor, has a rotor base member, the rotor base member having a groove extending in the circumferential direction of the rotor base member, and having a plurality of rotor blades, each rotor blade having a blade, a blade root and a blade platform positioned between the blade and the blade root, and the rotor blades being anchored in the groove of the rotor base member by their blade roots. The groove and the blade roots have a profile, such that the blade roots of the rotor blades are insertable by a tilting motion or swiveling motion into the circumferentially extending groove of the rotor base member, and in the circumferential direction, a width of the blade root corresponds approximately to a width of the blade platform of the specific rotor blade.

Abstract: A rotor disc and rotor blade assembly in which the rotor blades include curved shear pins to secure the blade to the rotor disc. The blade includes an airfoil portion with an airfoil outline shape at the junction of the airfoil with the platform, and the root extends below the platform and has the general shape of the airfoil at the junction. An opening in the rotor disc also has the shape of the airfoil outline such that the root will fit snuggly within the opening in the rotor disc. Curved slots in both the opening and the root wall are formed on both sides of the opening and the blade root. Shear pins having a rectangular cross sectional shape fit within the slots to secure the blade to the disc. Because the root curvature follows the airfoil shape, the shear pins are located below the airfoil walls and absorb the shear stress caused by bending forces acting on the airfoil from the fluid reaction.

Abstract: The field of the invention is a blade root extender for a wind turbine assembled between the blade root and a hub fixed to the wind turbine's nacelle. The extender is made up of a hollow, corrugated cylinder, one or two terminal flanges with holes for some preloaded stud bolts that apply pressure to the blade root extender.

Abstract: The invention relates to a mast (10) for a wind turbine, which mast tapers towards the top and comprises at least two superposed annular mast sections (12, 14, 16, 18, 20). Every annular mast section consists of a plurality of prefabricated wall parts (A, B, C, D, E, F), wherein at least a part of which has a curved section, at least the curved sections of prefabricated wall parts in different annular mast sections having at least identical cross-section.

Abstract: An engine fan has fan blades capable of switching between a sucking and blowing operation when the fan is not in operation. An internal mechanism allows for blade pitch adjustment of all fan blades by twisting one blade about its own axis. End positions of the blade rotation may be held by forces generated by the rotating blades or held by a locking mechanism.

Abstract: A compliant seal assembly for sealing a gap between a dovetail tab of a bucket and a slot of a rotor. The compliant sealing assembly may include a sealing groove positioned about the slot and a compliant seal positioned about the sealing groove. The compliant seal is forced into the gap and about the dovetail tab when the bucket rotates.

Abstract: Blade insert connected in the lamination of a blade determining a double shear joint between insert and lamination. The insert is made up of two defined parts, head (2), designed to screw the insert to another structure (2?), and the body (3) that determines a cylindrical or conical shape with an internal conical cavity. In an embodiment, the insert is designed to be joined to the lamination (1) of the blade with adhesive means (4). In another embodiment, the insert is embedded in the blade lamination with an inner part (5) stuck to the body (3) of the insert.

Abstract: The invention relates to a rotor for a non-positive-displacement machine, particularly a rotor for a compressor of a gas turbine, on which at least one shaft collar with an outer periphery and with two radially extending faces are placed. The rotor also comprises a multitude of retaining grooves for moving blades, said retaining grooves being provided on the outer periphery and extending transversal to the peripheral direction and each retaining groove has a groove bottom. In order to provide a rotor for a non-positive-displacement machine that makes it possible to reduce flow losses while having a simple geometrical design of the attachment of moving blades, the invention provides that an annual groove, which extends in an axial direction and which is coaxial to the rotation axis of the rotor, is provided at least on one face of the shaft collar.

Abstract: A ceiling fan blade attachment for enhancing the efficiency of conventional planar ceiling fan blades. A deflection element of the fan blade attachment may improve, add to, and/or replace the functional surface area of a conventional fan blade. The deflection element of the fan blade attachment comprises a positive twist spanning from the proximal end of the ceiling fan blade to either at least the approximate midpoint of the ceiling fan blade or the distal end of the ceiling fan blade. Preferably, the pitch of the fan blade attachment at its proximal end may be between 20 degrees to 35 degrees relative to a horizontal plane and the pitch of the fan blade attachment at its distal end may be between 5 degrees and 16 degrees relative to the horizontal plane. At least one fixation member may provide for securing the deflection element to the ceiling fan blade.

Abstract: A wind turbine includes a nacelle and a rotor, the rotor being rotatably mounted on the nacelle by means of at least one main bearing unit. The wind turbine is characterized in that the main bearing unit includes at least one outer ring, at least one centre ring and at least one inner ring and wherein the centre ring is capable of rotation in relation to the outer ring and the inner ring or the outer ring and the inner ring are capable of rotation in relation to the centre ring. A method for servicing a main bearing unit of a wind turbine and a use hereof are also provided.

Abstract: A method and apparatus for a rotor assembly for gas turbine engine are provided. A first rotor blade including an airfoil, a platform, a shank, an internal cavity, and a dovetail is provided, wherein the airfoil extends radially outward from the platform, which includes a radially outer surface and a radially inner surface, the shank extends radially inward from the platform, and the dovetail extends from the shank, such that the internal cavity is defined by the airfoil, the platform, the shank, and the dovetail. The first rotor blade is coupled to a rotor shaft such that during engine operation, cooling air is channeled from the cavity through an impingement cooling circuit for impingement cooling the first rotor blade platform radially inner surface, and a second rotor blade is coupled to the rotor shaft such that a platform gap is defined between the first and second rotor blade platforms.

Abstract: The present invention relates to a method of manufacturing a blade for a wind turbine, wherein the blade is made in one or more moulds; and wherein the blade has integrally moulded root bushings in the root of the blade for direct or indirect attachment to a hub in a wind turbine. The novel aspect of the invention is that the root bushings (203) in the root (201) of the blade are leveled by shortening of at least one of the root bushings prior to the blade being removed from a supporting mould (205). The invention further relates to a blade made in accordance with the method and a leveling unit (207) for leveling the root of the blade, wherein the leveling unit comprises means for mounting on a mould.

Abstract: A method enables a stator assembly for a turbine engine to be assembled. The method comprises forming a recess within a portion of each base, and coupling the stator vanes within the turbine engine in a circumferentially-spaced arrangement such that the recessed portion of each base facilitates reducing excitation responses of each of the plurality of stator vanes during engine operation.

Abstract: A method for making a gas turbine engine turbine blade comprising an airfoil section a platform section, an under platform section, and a dovetail section, the exterior surface of the dovetail section comprising a shank exterior surface and a serrated exterior surface. The blade further includes a silicon-modified diffusion aluminide layer a surface of a turbine blade section selected from the group consisting of the exterior surface of the under platform section, the exterior surface of the dovetail section, and combinations thereof, the aluminide layer having a concentration of silicon at a surface of the aluminide layer in the range of about 1 weight percent to about 10 weight percent and a concentration of aluminum at the surface of the aluminide layer in the range of about 5 weight percent to about 25 weight percent.

Abstract: A turbine or compressor blade assembly includes a blade fixed to a dovetail section attachable to a wheel. The dovetail section has a dovetail shaped to fit in a correspondingly shaped slot in the wheel. A dovetail platform serves as an interface between the blade and the dovetail. An undercut fillet radius is formed at an intersection of the dovetail platform and a dovetail pressure surface, where the undercut radius has a multi-part profile shape configured to attenuate edge of contact stresses. An additional feature is the area where the undercut radius transitions into the P-cut area at the forward end (leading edge) of the dovetail.

Abstract: An annulus filler is provided for mounting to a rotor disc of a gas turbine engine and for bridging the gap between two adjacent blades attached to the rotor disc. The annulus filler defines an airflow surface for air being drawn through the engine. The annulus filler has one or more primary connectors for connecting the annulus filler to the rotor disc, and for resisting, in use, centrifugal forces on the annulus filler. Each primary connector allows rotation of the annulus filler around the centre line of the engine relative to the rotor disc at that primary connector. The annulus filler also has a secondary connector for connecting the annulus filler to the rotor disc and for resisting, in use, motion of the annulus filler relative to the rotor disc in a first axial direction. The secondary connector allows rotation of the annulus filler around the centre line of the engine relative to the rotor disc at the secondary connector.

Abstract: A gas turbine engine disk that includes a centrally disposed disk hub having an integrally-formed, radially outwardly extending web terminating at an outer end. The disk hub has a radially-displaced annular hub surface exposed to high pressure, high temperature discharge gases during engine operation. The radially-displaced annular hub surface acts as an axial free surface mitigating the formation undesirable axial stress in the disk hub.

Abstract: A method of joining a first part together with a second part is disclosed. The method may comprise providing a first part having a first joining portion including a first channel and a second part having a second joining portion including a second channel. The method may further comprise positioning the first part adjacent to the second part such that the first channel and second channel align with one another to define a cavity. The method may still further comprise preparing a mixture comprising at least one of a metal powder and a polymer binder, placing the mixture into the cavity so as to form a preform and solidifying the preform forming a metal element in the cavity.

Abstract: A seal plate assembly is provided in a rotor disc for a turbine engine. The seal plate assembly includes a radially extending flange on the disc and an annular groove defined between a radial surface on the flange and a face of the disc. An annular outer surface extends axially in facing relationship to an annular inner surface of the groove. A plate structure is supported between the inner and outer surfaces, and a lock structure is provided for holding the plate structure in place. The lock structure includes an axial leg that is adapted to be located between an inner edge of the plate structure and the inner surface of the groove, and the lock structure further includes a radial leg that is adapted to be located between the radial surface on the flange and an outwardly facing surface of the plate structure.

Abstract: A turbine wheel hole plug that includes: 1) an approximate cylindrical body, the cylindrical body sized such that the cylindrical body fits snugly into a turbine wheel hole; 2) a first flange at a first end of the cylindrical body, the first flange being approximately cylindrical in shape and having a diameter that is larger than the diameter of the turbine wheel hole; and 3) a second flange at a second end of the cylindrical body, the second flange comprising a flared flange. The first flange and the second flange may lock the cylindrical body into a preferred position in the turbine wheel hole.

Abstract: An impeller includes first and second impeller portions that are secured to one another. An interior cavity is formed between the first and second portions. The first impeller portion supports multiple blades. The first and second impeller portions respectively include first and second surfaces that are secured to one another near a tip of the impeller. Inlet and outlet apertures are provided in the impeller and are in communication with the inner cavity to provide a cooling flow path there through. A circumferential gap is arranged between the first and second impeller portions opposite the tip to permit relative axial movement between the first and second impeller portions during centrifugal loading of the impeller.

Abstract: A method of assembling a tower for use with a wind turbine is provided. The method includes providing a plurality of tower segments. Each tower segment includes a first interface and a second interface. The method also includes bonding the first interface of a first tower segment to the second interface of a second tower segment using an adhesive composition.