Abstract: The present invention includes a rotor-blade span-balancing system, including a span-balance pocket in a surface of a rotor blade; a cover operably configured to cover the span-balance pocket, wherein the cover is operably configured to be substantially flush with the surface of the rotor blade surface when covering the span-balance pocket, and wherein the cover includes a cover boss for reacting centrifugal force of the cover into the rotor blade; and one or more span-balance weights attached to the cover to span-balance the rotor blade.

Abstract: The invention relates to a balancing system of an aircraft turbomachine comprising a first annular row of first mounting ports for mounting balancing members, and a second annular row of second mounting ports for mounting balancing members which is axially offset from the first annular row, the number and angular positions of the first mounting ports being identical to the number and angular positions of the second mounting ports.

Abstract: A cover plate for maintaining axial alignment between a blade assembly and a rotor disk and transferring centrifugal loading directly to the rotor disk. The cover plate comprises a plate key extending axially from an elongate member, the plate key configured to engage a keyway of the rotor disk assembly and/or a notch of the blade key.

Abstract: A balancing assembly for a rotating component of a gas turbine engine includes a balance weight configured for insertion into a complimentary balance weight slot in the rotating component. The balance weight has a dovetail shaped cross-section and the balance weight slot has a complimentary dovetail shaped cross-section. A retaining ring configured for installation to the rotating component axially retains the balance weight in the balance weight slot. A method of correcting an imbalance of a rotating assembly includes inserting a balance weight into a balance weight slot in a rotating component of the rotating assembly, and installing a retaining ring at the rotating component to retain the balance weight in the balance weight slot in an axial direction. The balance weight has a dovetail shaped cross section, and the balance weight slot has a complimentary dovetail shaped cross section to retain the balance weight at the balance weight slot.

Abstract: A method for producing a centrifugal pump impeller having a base plate, which is a single piece with pump blades and a cover plate, which consists of a thermoplastic material, wherein contact areas are available, which are heated and melted by means of ultrasonic excitation and form a close bonded connection after cool-down. The objective of the invention is to ensure inherent stability with the individual parts and a simple and reliable pre-assembly as well as a fixed mechanical connection, wherein only a small amount of excitation energy is required, with a centrifugal pump impeller comprising a base plate and cover plate.

Abstract: In one embodiment, a rotor blade may comprise a blade body, a spar structure, and a blade nose. The blade body may comprise a skin, wherein the skin is configured to form an airfoil shape, and wherein the airfoil shape comprises an inboard end, an outboard end, a leading edge, and a trailing edge. The spar structure may comprise a first spar cap and a second spar cap, wherein the first spar cap is coupled to an upper portion of the skin, and wherein the second spar cap is coupled to a lower portion of the skin. The blade nose may comprise a cavity, wherein the cavity is configured to house a plurality of modular weights at a plurality of radial blade locations, wherein the plurality of radial blade locations comprises a range of locations between the inboard end and the outboard end.

Abstract: A method of identifying the balancing configuration installed on a turbine engine rotor using a plurality of screws forming balance weights that are mounted on the rotor at different angular positions of the rotor is provided. Each screw possesses a predetermined weight and each screw is associated with an element for identifying its weight and for identifying its angular position on the rotor. The method includes contactless scanning of all of the screws mounted on the rotor by an identification appliance capable of recognizing the elements for identifying the weight and the angular position associated with each screw.

Abstract: A compressor blade locking device can include: a first support including a first locking groove; a second support including a left groove and a first protrusion corresponding to the first locking groove; a third support including a second locking groove; a fourth support including a right groove and a second protrusion corresponding to the second locking groove; a center support disposed between the second support and the fourth support; and a tab disposed in the center support, wherein the tab is configured to be turned such that the tab is disposed in the left groove and the right groove.

Abstract: A turbomachinery rotor apparatus includes: a rotatable disk having an array of slots spaced around its periphery; an array of blades installed in the slots, wherein the blades have variable weights; and a plurality of connection components installed in the disk, each connection component forming a portion of a mechanical joint between one of the blades and its respective slot, wherein the connection components have variable weights.

Abstract: A fan of the invention includes an impeller having a plurality of blades and rotating around a rotation axis, and at least one balance weight having at least one claw portion and attached to the impeller to correct the center of gravity of the impeller. The impeller has a circumferential convex portion formed along the circumferential direction, and on which the claw portion is hooked to restrict a range of movement of the balance weight in the radial direction of the impeller, and at least one radial concave-convex portion formed along the radial direction, and on which the claw portion is hooked to restrict the range of movement of the balance weight in the circumferential direction of the impeller.

Abstract: A nickel-base superalloy consisting of, by weight: 14.6% to 15.9% cobalt; 11.5% to 13.0% chromium; 0.8% to 1.2% iron; 0.2% to 0.60% manganese; 2.00% to 2.40% molybdenum; 3.30% to 3.70% tungsten; 2.90% to 3.30% aluminum; 2.60% to 3.10% titanium; 3.50% to 5.10% tantalum; 1.20% to 1.80% niobium; 0.10% to 0.60% silicon; 0.02% to 0.06% carbon; 0.010% to 0.030% boron; 0.05% to 0.11% zirconium; up to 0.045% hafnium; and the balance being nickel and impurities.

Abstract: A balanced turbomachine part including one angular sector arranged to form a balancing ring centered about a ring axis. The angular sector includes a plurality of fasteners, a bearing face having a complementary shape to the balancing ring, the angular sector bearing on the bearing face. The part further includes a plurality of balancing masses each fastened to the corresponding fastener of the angular sector, at least one of the balancing masses also acting as a fastener for fastening the angular sector on the bearing face.

Abstract: The present invention relates to a balance structure of a fan, which comprises a hub and a balance slider. The hub has a circumferential portion and a top portion. The circumferential portion has a plurality of blades. The top portion is provided with a groove having a latch portion. The balance slider has a receiving portion slidingly engaging with the latch portion such that the balance slider can be slidingly disposed in the groove and the balance slider can move to a balance position automatically during the rotation of the hub. In this way, the effect of automatic balance can be achieved.

Abstract: Turbochargers operate at extremely high speed, so balance of the rotating core is of the utmost importance to turbocharger life. A special balancing washer is added to the clamping region between the compressor nut and the nose of the compressor wheel to aid in keeping the wheel, nut, and stub-shaft on the turbocharger axis and to thereby prevent introduction of core unbalance.

Abstract: A fan blade is mounted on a shaft or arranged to vary in pitch via rotation about a pitching axis. The fan blade is mounted with a center of mass offset from the shaft or pitching axis. This offset reduces torque around the shaft or pitching axis.

Abstract: A minidisk for a rotor system may comprise a balance flange defining a hole array, which may include a first hole having a first width. The first hole may be configured to receive a balance weight. A second hole and a third hole may have a second width. The second hole and the third hole may be disposed adjacent to the first hole. The second width may be greater than the first width.

Abstract: The present disclosure provides a frequency control method for a micro-grid and a control device. The method includes: determining a middle parameter at iteration k; determining a local gradient parameter at iteration k according to the cost increment rate at iteration k, the frequency difference between iterations k and k+1, and communication coefficients; performing a quasi-Newton recursion according to the middle parameter and local gradient parameter to acquire a recursion value; determining the cost increment rate at iteration k+1 according to the recursion value; determining an adjustment value of an active power according to the cost increment rate at iteration k+1; adjusting the active power according to the adjustment value if the adjustment value satisfies a constraint condition and judging whether the difference is smaller than a predetermined threshold; executing k=k+1 if yes and stopping the frequency control if no.

Abstract: A turbomachine module, comprising a mobile wheel rotatably mounted inside a housing of the module and surrounded by a sectorised sealing ring (18) that comprises an annular row of sectors, each ring sector comprising at least one circumferential hook that is configured to engage with an annular hooking rail of the housing, the module further comprising a sectorised protective annular shim (50) that is interposed between the hooks of the ring sectors and the rail of the housing and that comprises an annular row of sectors of shim, characterised in that the edges (60) of the circumferential ends of the sectors of shim are not aligned with the edges (58) of the circumferential ends of the ring sectors along the longitudinal axis of the module.

Abstract: A rotor blade comprises a blade platform and an airfoil. The airfoil comprises a blade tip, a leading edge, and a trailing edge with a stiffening compound lean contour. The blade tip is radially opposite the blade platform, and defines a blade span between the blade itself and the blade platform. The leading and trailing edges extend from the blade platform to the blade tip to define blade chords between the leading edge and the trailing edge. The compound lean contour comprises a positive lean section located at the lean tip, and extending along a lean axis to a lean end. The negative lean section is located radially inward of the positive lean section, and extends along the lean axis to the lean end.

Abstract: There is provided a vibration damper which is capable of damping torsional vibrations by pendulum movement of a plurality of inertial masses, and damping vibrations of plurality of order without letting the inertial masses to interfere. A distance between a center of curvature of an inner surface of a first through-hole and a center of curvature of an inner surface of a second through-hole formed in a rotary member is shorter than a distance between a center of curvature of an inner surface of a fifth through-hole and a center of curvature of an inner surface of a sixth through-hole formed in a first inertial mass. Moreover, a distance between a center of curvature of an inner surface of a third through-hole and a center of curvature of an inner surface of a fourth through-hole in a rotary member is longer than a distance between a center of curvature of an inner surface of a seventh through-hole and a center of curvature of an inner surface of an eighth through-hole formed in a second inertial mass.

Abstract: An airfoil includes, among other possible things, a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. A cover skin is attached to the main body. The cover skin is welded to the main body with a weld at outer edges. An adhesive is placed between inner surfaces of the cover skin and the main body. The adhesive is deposited inwardly of the outer edges of the cover skin. A method of constructing an airfoil is also disclosed as is a gas turbine engine.

Abstract: An impeller of an axial fan includes a cup-shaped blade support portion configured to cover a rotor holder, and blades in a circumferential direction outside of the blade support portion. Rotation of the impeller generates a downward air flow from the inlet to the outlet. The axial fan includes first and second balance correction portions. The first balance correction portion is located between the blade support portion and the rotor holder. The second balance correction portion is located axially below the first balance correction portion, and is located axially below the rotor holder and a junction of each blade with the blade support portion. The impeller includes a first cone portion located axially below the second balance correction portion, and decreases in diameter with decreasing height. The impeller includes a cylindrical portion including a cylindrical outer circumferential surface and located between the first cone portion and the second balance correction portion.

Abstract: A tie rod assembly for a mid-turbine frame includes at least one tie rod for connecting an outer frame case to an inner frame case. At least one tie rod includes an inlet passage that branches into a first branch and a second branch. A plug is located in the first branch to block flow through a portion of the first branch.

Abstract: An air inlet deflector for a structure having an air inlet. The deflector may be retractable within the structure, may be integrally formed with the structure, and may prevent the structure from ingesting foreign matter, such as birds. The deflector may include a series of ribs, spokes, or vanes that may vary in width and/or thickness from fore to aft, and/or may be curvilinear in one or more planes of view, and/or may serve double duty as inlet vanes for redirecting inlet air.

Abstract: Wind turbines are provided comprising a support structure having a tower and a nacelle mounted on the support structure. A first region (damper region) of the wind turbine including at least a first part of the nacelle is flexibly coupled to a second region (to be damped) of the wind turbine including at least the support structure. Methods are also provided for determining a suitable stiffness of the flexible coupling of the damper region to the region to be damped of any one of said wind turbines. These methods comprise determining a modal mass of the region to be damped depending on a given tower bending mode; and determining the stiffness of the flexible coupling of the damper region to the region to be damped depending on the calculated modal mass of the region to be damped and on the mass of the damper region.

Abstract: A wind turbine blade includes a first shell member including a first mating surface along a first edge of the wind turbine blade. Also, the wind turbine blade includes a second shell member including a second mating surface along the first edge of the wind turbine blade, wherein the second mating surface is opposite to the first mating surface. Further, the wind turbine blade includes a bonding material disposed between the first mating surface and the second mating surface and configured to bond the first mating surface to the second mating surface. Moreover, the wind turbine blade includes a constrainer positioned at a desired bond line and coupled to one of the first mating surface and the second mating surface, wherein the constrainer is configured to restrict the bonding material from migrating into an interior cavity of the wind turbine blade.

Abstract: An aircraft turbopropeller includes two coaxial contra-rotating unducted propellers, upstream and downstream respectively, each propeller including an annular row of blades. The blades of the downstream propeller have a reverse sweep in relation to that of the blades of the upstream propeller. The leading edges of the blades of the downstream propeller extend radially outwards from downstream to upstream, at least over a radially outer portion of the blades.

Abstract: Methods for installing blades of a wind turbine are provided. The method comprises: providing a blade holder, wherein the blade holder comprises a connection element adapted to be attached to a mounting surfaces and a lifting equipment attachment, the blade holder being provided with a steering mechanism. Then, the blade holder is attached to the blade. The blade holder is hoisted with the blade towards the rotor hub with lifting equipment. The blade holder is attached to the mounting surface of the hub using the connection element. The rotor hub is rotated using the weight of the blade holder and the blade to a first desired position for mounting the blade to the rotor hub. The blade holder is detached from the hub. Then, the blade may be mounted to the rotor hub. A wind turbine blade holder for holding a blade and for use in lifting the blade is also provided.

Abstract: A rotating assembly for a turbine engine, comprising a disc having an outer periphery having alternating slots and teeth, blades radially extending from the disc and roots of which are axially engaged in the slots, with spaces called slot cavities being provided between the roots of the blades and the slots, platforms laterally extending from the blades and circumferentially arranged end-to-end, so as to form spaces called inter-blade cavities, and a downstream annular shroud, comprising an outer annular sealing lip opposite the downstream ends of the platforms. The downstream shroud further comprises an intermediate annular sealing lip opposite the downstream faces of the teeth of the disc, radially between the slot cavities and the inter-blade cavities.

Abstract: Counterweight system for a wind turbine comprising a hub mounted to a nacelle such that the hub is rotatable around a rotation axis with respect to the nacelle. The counterweight system comprises: a mechanical unit comprising a fixed part and a rotatable part, the fixed part being mountable to the hub in such a way that the rotatable part is rotatable with respect to the hub substantially around the rotation axis of the hub; a drive unit for causing rotation of the rotatable part; a beam coupled to the rotatable part at a first point of the beam in such a way that the beam is arranged substantially perpendicular to the rotation axis of the hub; and a counterweight mass coupled to the beam at a second point of the beam. A method of mounting a blade to a hub by using said counterweight system is also provided.

Abstract: A shaft balancing assembly comprising a nose cone and a plurality of balance weights. The nose cone is mounted to a rotatable shaft of a turbine machine via a plurality of elongated fasteners such that a central axis of the nose cone is alighted with the rotatable shaft. The nose cone comprises a flange extending axially from a leading tip to a trailing edge and a plurality of apertures each adapted to receive a balancing weight and an elongated fastener. The nose cone flange is formed from a filament wound composite material and has a uniform thickness.

Abstract: The invention includes a disc-shaped disc section (30) that is attached to a rotating shaft (6), and blade sections (40) that are provided on a front surface (31) that is one side in an axial direction of the disc section (30). Balance holes (33) for attaching weight-adjusting weight members W thereto are provided at positions where the blade sections (40) are provided in a radial direction, in a rear surface (51) that is the other side in the axial direction of the disc section (30).

Abstract: A rotor for a turbomachine includes a rim defining a base of a rotor, an airfoil shaped blade extending from said rim and defining a chord line and a bore extending from said rim opposite said airfoil shaped blade. The rim further includes at least one rail extending away from said airfoil shaped blade.

Abstract: A blower assembly includes a centrifugal fan and a motor assembly. The centrifugal fan has a plurality of axially extending impeller blades, a first axial end, and an air inlet. The air inlet is at the first axial end of the centrifugal fan. The motor assembly comprises a stator, a rotor, and an air directing surface. The air directing surface is shaped and configured to direct air drawn into the air inlet radially outwardly toward the impeller blades. The air directing surface extends generally along the rotor axis from its first end to its second end. At least a surface region of the air directing surface generally circumscribes the rotor axis and diverges radially outwardly as such surface region of the air directing surface extends away from the first end toward the second end.

Abstract: A fan hub balancing structure includes a hub main body. The hub main body has a top section, a circumferential section extending from the circumference of the top section and a lip section. The lip section is connected with the lower end of the circumferential section. The lip section has at least one residual weight section on the lip section. After the residual weight section is removed from the lip section, a balancing section is formed on the lip section. The balancing structure is able to provide a balancing effect for the hub main body and facilitate the processing of the hub main body.

Abstract: Rotor blade assembly and methods for forming rotor blade assemblies are provided. A rotor blade assembly includes a rotor blade including a shell and defining a pressure side, a suction side, a leading edge and a trailing edge each extending between a tip and a root. The rotor blade further defines a span and a chord. The shell includes an inner skin, an outer skin, and a core disposed between the inner skin and the outer skin. The rotor blade assembly further includes a reinforcement assembly bonded to the shell, the reinforcement assembly comprising a reinforcement core.

Abstract: A rotor disk comprises a plurality of circumferentially distributed hooks, the set of hooks defining an annular groove adapted to cooperate with at least two flange sectors. At least one of the hooks comprises a second element through which a recess is formed which opens up at each of the transverse flanks of the second element and at the internal peripheral surface of the second element.

Abstract: A centrifugal force pendulum having a pendulum mass pair and a pendulum flange, in which an arcuate cut-out with a cut-out contour is provided, wherein the pendulum masses of the pendulum mass pair are situated on both sides of the pendulum flange and are connected to each other by at least one spacer bolt which is guided through the cut-out, wherein the spacer bolt has a damping arrangement which includes a stabilizing element and an elastic damping element, wherein the damping element is designed to damp a striking of the spacer bolt on the cut-out contour of the cut-out, wherein the damping element and the stabilizing element of the damping arrangement are positioned relative to each other so that the damping element is able to strike the cut-out contour of the cut-out directly.

Abstract: An airfoil comprises an airfoil body with an internal cavity and inner and outer covers. The airfoil body defines a first major surface of the airfoil, and a rib extends along the internal cavity. The inner cover is bonded to the airfoil body over the internal cavity, and includes a coupling element extending along the internal cavity in cooperative engagement with the rib. The outer cover is bonded to the airfoil body over the inner cover, and defines a second major surface of the airfoil.

Abstract: A turbine engine blade, including an airfoil which extends radially between a blade root and an airfoil tip, axially between a leading edge and a trailing edge, and tangentially between a pressure side and a suction side, the profile of the blade having a series of basic profiles, in a form of a vane section, stacked on one another along a stacking line connecting the center of gravity of all the vane sections. The projection of the stacking line of the airfoil on at least one plane extending radially from the blade root includes a double tangential inversion of the direction of the curvature thereof, located in the last thirty percent of the height of the airfoil, the projection plane being positioned substantially perpendicular to the chord of the blade.

Abstract: A device for absorbing kinetic energy for an aircraft structural element undergoing a dynamic impact. The device includes an outer enclosure made from a braided composite material configured to preserve its integrity after an impact, a foam core, contained in the outer enclosure and to at least partially fill the outer enclosure. The foam core is configured to at least partially absorb the kinetic energy generated by the impact. Reinforcing elements are integrated at least partially into the foam core to dissipate, combined with the form core, the kinetic energy generated by the impact. The reinforcing elements includes discontinuous threads inserted into the foam core by stitching, and each discontinuous thread includes an L- or T-shaped head, folded down outside the outer enclosure.

Abstract: The application describes an apparatus for and a method of mounting wind turbine blades on a wind turbine tower. A number of guide rods are provided in the vicinity of the blade root and hub for connection to corresponding socket sections. The guide rods and socket sections are provided on respective ones of a wind turbine blade and a wind turbine hub to facilitate connection of one to the other. The guide rods and the sockets may be provided on the same or on different ones of the blade or hub. The guide rods and sockets allow the blade to be positioned at the hub in the correct rotational orientation to facilitate connection of the necessary fasteners.

Abstract: A method of assembling a rotor blade assembly includes determining a first spanwise moment of a first component of the rotor blade assembly and comparing the first spanwise moment to a target first spanwise moment. The first spanwise moment of the first component is adjusted based on a result of the comparison. A second spanwise moment of a second component of the rotor blade assembly is determined and compared to a target second spanwise moment. The second spanwise moment of the second component is adjusted based on a result of the comparison. The first component is assembled to the second component, resulting in a rotor blade assembly meeting a target spanwise moment of the rotor blade assembly.

Abstract: Enriching and balancing the acoustic spectrum radiated by a propeller by introducing a differential pitch angle on certain blades of the propeller. Modifying the acoustic spectrum makes it possible to render the propeller noise more pleasant to the human ear.

Abstract: A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs. The balancing is achieved by removing material from at least one of the tabs.

Abstract: Rotor blade assemblies and methods for constructing rotor blade assemblies are provided. A rotor blade assembly may include a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge and a trailing edge each extending between a tip and a root, the rotor blade defining a span and a chord. The rotor blade assembly further includes an extension plate mounted to one of the pressure side or the suction side, the extension plate extending in the chord-wise direction between a first end and a second end, the second end extending beyond the trailing edge. The rotor blade assembly further includes a filler substrate provided on an inner surface of the extension plate and the trailing edge, the filler substrate tapering from the trailing edge towards the second end.

Abstract: An enclosure for carrying an adjustable payload. The enclosure is beneficially used on a rotorcraft blade or other similar structure. The enclosure has a first element having a first flange and an upper element. The first element has an upper surface which has a first angle with respect to a lower surface of the first flange in a direction extending from an inboard direction to an outboard direction. The upper element has a lower surface which has a second angle with respect to an upper surface of said upper element in a direction extending from an inboard direction to an outboard direction, the lower surface being in contact with the upper surface of said first element, the second angle being in a direction which is opposite to the direction of said first angle. The first element and the upper element define a cavity for holding a payload.

Abstract: A wind turbine generator with a bearing system is disclosed. The bearing system includes a lockable connection having a bearing surface and a support surface which surfaces are engaged when the lockable connection is locked. Forces from the shaft are transferred via the bearing into the support through the bearing surface, wherein a support angle of the support surface, relative to a shaft plane formed by rotating the shaft around a first axis, which first axis is perpendicular to the center axis and which first axis is comprised in a vertical plane, is in a range from and including 5 degrees to and including 70 degrees.

Abstract: A propeller rotor has a hub mounting a plurality of blades and a drive shaft for driving the hub and the blades about a central axis. A motor to change its position is operably connected to drive at least one counterweight. A sensor senses vibration on the propeller rotor and communicates with a controller. The controller controls the motor to change a position of the counterweight in response to a sensed imbalance. A method of operating a propeller rotor is also disclosed.

Abstract: A fan device includes a rotor 20 and recesses 40 to be filled with claylike weights 70. The rotor 20 includes an impeller 23 and a shaft 10. The impeller 23 has a hub 21 and vanes 22. The recesses 40 are provided on a surface 212 that crosses an axial direction of the hub 21. Each recess 40 has a first area 41 and a second area 42. The first area 41 is circumferentially arranged and extends in a substantially circumferential direction. The second area 42 is connected to an outer circumferential side of the first area 41 and has a shorter length in the circumferential direction than the first area 41. The weight 70 is closely adhered to wall surfaces 421 and 422 formed along a radial direction in the second area 42 so as to prevent separation thereof.