Abstract: Dampers (56, 76, 96) are utilized with regard to mounting arrangements (50, 70, 90) in gas turbine engines (10) in order to facilitate cooling. It is known to provide slotted upper surface or cottage roof dampers to enhance cooling effect. However, cooling efficiency cannot be optimized and improving cooling effectiveness particularly between the parts of a mounting arrangement can be difficult without detrimental reductions in overall efficiency of a gas turbine engine (10) incorporating such a mounting. By provision of impingement jets (54, 75, 94) which extend through the damper (56, 76, 96) into slots (51, 71, 91) which define an upper surface of the damper (56, 76, 96) improvements in cooling efficiency can be achieved. The slots (51, 71 91) are typically closed to reduce requirements with respect to pressure differentials. However, open ended slots (51, 71, 91) with impingement jets (54, 74, 94) can also be provided.

Abstract: A method for damping edgewise oscillations in one or more blades of a wind turbine includes the steps of detecting if one or more of the blades oscillates edgewise during operation of the wind turbine, and substantially cyclically generating a pitch angle difference between at least two of the blades. Further provided is an active stall controlled wind turbine and use hereof.

Abstract: A section of a gas turbine engine includes a damper which extends from a disk between a first blade and a second blade to provide a dissipating vibratory motion energy in the form of friction heating.

Abstract: The present invention relates to a rotor for gas or steam turbines having a disk (1), an outer cover (2) and a plurality of blades (3). The disk (1) defines the portion of less diameter of the rotor and has an inner surface configured to be coupled on a shaft (100) of the turbine or connected to an axially adjacent disk (1?, 1?); an outer surface configured for housing a plurality of blades (3). The outer cover (2) defines the portion of greater diameter of the rotor. The blades (3) have a root (31) configured to be coupled on the disk (1) and a tip (32) opposite to the outer cover (2). Between these blades there is a plurality of blades (3) welded together at the tip (32) to form groups of blades (3a) and individual blades (3b) intercalated between groups of blades (3a).

Abstract: An aerofoil assembly includes a plurality of rotatable blades. A damping member is disposed between at least two of the blades, each of the at least two blades having an aerofoil portion, a stem portion and a root portion. A recess is provided on two cooperating stem portions with a first shelf extending from a first end of each recess, and a second shelf extending from a second end of each recess to define a compartment. When the blades are aligned the damping member is held on one side of the shelves within the compartment. The damping member is provided with a projection at one corner and a projection on a diagonally opposite corner, the longitudinal distance between ends of the projections being greater than the distance between edges of the first and second shelf.

Abstract: The present invention relates to a blade made of composite, comprising a vane formed of woven filaments impregnated with a thermosetting resin with a protective element in the region of the leading edge of the vane comprising a part in the form of a rigid strip, said strip being secured to the vane. The blade is characterized in that at least one layer of a viscoelastic material is at least partially interposed between said rigid strip and the vane so as to form, with the protective element, a means of damping the vibrations of the vane.

Abstract: Provided are a wind turbine generator and a method for constructing a wind turbine generator that allow for alleviation of construction costs, particularly for large wind turbine generators, and alleviation of limitations on construction due to weather. Provided are a rotor head that has a plurality of wind turbine rotor blades and that is rotated by wind power received by the plurality of wind turbine rotor blades, a front segment disposed on top of a tower and constituting a nacelle to which the rotor head is attached, a rear segment attached to the front segment and constituting the nacelle, a front frame disposed in the front segment and positioned between the rotor head and the tower so as to support a load on the rotor head, a rear frame disposed in the rear segment and attached to the front frame, a front cover covering the periphery of the front segment, and a rear cover covering the periphery of the rear segment.

Abstract: A system for reducing vibrations in a rotating system uses a variable viscosity medium that is redistributed in a housing connected to the rotating system. Specifically, the medium is responsive to a control signal that is generated as a function of rotational speed of the rotational system. The control signal activates a triggering device that promotes a change in viscosity of the medium such that it is distributed within the housing in a manner that reduces vibratory loads.

Abstract: A frequency mistuned integrally bladed rotor (IBR) for a gas turbine engine comprises a hub and a circumferential row of blades of varying frequency projecting integrally from the hub. Each blade in the row alternate with another blade having a different pressure surface definition but similar suction surface, leading edge and trailing edge definitions.

Abstract: A rotor system includes a multiple of rotor blade yokes mounted to a rotor hub. A lead/lag damper is mounted to each of the rotor blade yokes and to a damper hub. An actuator system is operable to shift a damper hub axis of rotation relative the rotor axis of rotation to minimize 1P damper motions. A method of minimizing 1P damper motions within a rotor system includes shifting the damper hub axis of rotation relative the rotor axis of rotation to oscillate an inner connector of each lead/lag damper in phase with a 1P blade motion to minimize the 1P motion of the damper.

Abstract: In one embodiment, a rotor blade balancing apparatus may include a tube member defining an inner cavity, a plurality of weights, and a biasing member. The tube member may be for the insertion into a cavity of a rotor blade. Each of the weights may be adapted to be slide-ably inserted into the inner cavity of the tube member within a cavity of a rotor blade, and slide-ably removed from the inner cavity of the tube member within a cavity of a rotor blade in order to balance a rotor blade. The biasing member may be for biasing weights, which have been slide-ably inserted into the inner cavity of the tube member within a cavity of a rotor blade, towards an end of the tube member.

Abstract: A turbomachine rotor balancing system including a balancing flange provided with through-passageways, and balance weights mounted fixedly on the balancing flange by at least one screw/nut assembly passing through one of the passageways is disclosed. For each of the passageways, the flange has on its first face a first recess passing via the radial summit of the passageway. This first recess being deprived of contact with the screw head pressing on this first face. The flange has on its second face a second recess passing via the radial summit. The second recess being deprived of contact with the balance weight pressing on this second face.

Abstract: A method and device for reducing vibratory noise in a system with an integral rotating member includes independently operable drive systems for controlling the angular velocity of at least two independently rotatable masses. Control signals manipulate the drive system to rotate each mass at optimal speed, direction and phase to reduce noise induced in the system by the rotating member.

Abstract: A compressor blade (30) comprises a vibration damping coating (54) on a first surface of at least one portion of an erosion resistant material (56). The vibration damping coating (54) comprises a plurality of segments (58). The portion of erosion resistant material (56) and the vibration damping coating (54) are adhesively bonded to the compressor blade (30) such that the vibration damping coating (54) is arranged between the surface (50) of the compressor blade (30) and the portion of erosion resistant material (56).

Abstract: A blower is provided with an axial flow impeller 7, a fan motor 8 positioned in a suction side of the axial flow impeller 7, and a motor stay 9 supporting the fan motor 8. The motor stay 9 is substantially formed to have a linear shape and attached in parallel to a rotating surface of the axial flow impeller 7. An impeller blade front edge 17 of the axial flow impeller 7 is positioned in a region X which is closer to the motor stay 9 than a region Y in which an air flow turbulence in a wake flow of the motor stay 9 is expanded, and in which region X a range of the air flow turbulence is reduced. Accordingly, it is possible to inhibit the air flow turbulence in the wake flow of the motor stay 9 from affecting the aerodynamic characteristics and noise characteristics (for example, an increase of an NZ noise) of the axial flow impeller 7.

Abstract: A blade for a wind turbine generally comprises a shell body defined by first and second shells extending between a leading edge and a trailing edge, an inner spar supporting at least a portion of the shell body, and a damping element coupled to at least one of the shell body or inner spar. The damping element is configured to move relative to the shell body to dissipate vibrations of the blade, and has a greater degree of freedom in a flapwise direction between the first and second shells than in an edgewise direction between the leading and trailing edges.

Abstract: A blade includes an airfoil portion which defines at least one cavity with a damper located within the cavity, the damper includes a corrugated surface.

Abstract: The lifetime of plural shock absorbing resilient inserts of an adjustable pitch propeller with feathering blades may be increased. According to an embodiment, stops are implemented between metal surfaces that may be reached only in the event of shocks of great violence and following a certain elastic deformation of the shock absorbing inserts, which remain partially compressed. At the bottom of each circular cavity housing a respective annular insert of elastomer of the flange of a first cylindrical sleeve directly keyed on the drive shaft of the propeller a hole coaxial and of greater diameter than the diameter of a central hole of the annular insert and of the relative engaging pin is formed. Pins projecting from the face of the terminal flange of a second circular sleeve extend through the coaxially formed holes at the bottom of the respective circular cavities of the flange of the first sleeve.

Abstract: A composite-steel hybrid mast for a rotorcraft includes a tubular, steel portion having an internal surface defining a space therein and a composite portion disposed within the space defined by the internal surface of the steel portion and held in a fixed spatial relationship with respect to the internal surface of the steel portion.

Abstract: A turbomachine with a row of blades in which the blades are structured such that the blades can untwist at higher rotational speeds in order to provide optimal aerodynamics at different rotational speeds. Each blade is formed with a thin slot between the pressure side wall and the suction side wall so that stresses from centrifugal forces occurring during high rotations will not pass from adjacent walls and allow for the blade to untwist more than a solid blade. Each blade is formed from a fiber laminated composite material with the fibers oriented at different directions to form different stiffness in each direction so that a desired untwist can occur based upon a given blade mass and rotational speed. A thin sheet of a slippery material can be placed within the thin slot and between the adjacent airfoil walls to allow slippage between the adjacent walls and to promote damping for the blade.

Abstract: Easy to attach and detach blades for overhead ceiling fans. A first version has a ceiling fan blade with keyhole slots that fit over flat topped fasteners on a mounting arm. Pulling the blade away from the arm locks the slots to the fasteners. A second version is similar to the first and has a decorative bottom cover having snappable tapered protrusions which attach through the keyholes and into mateable through-holes in the mounting arm connection. The third version has a protruding end portion of the blade that fits into a slot in the mounting arm where spring loaded pistons press into grooves in the protrusion end portion of the blade. Latching handles allow users to manually move the pistons. A fourth version has a slot in the blade which fits about a mateable housing in the mounting arm where opposing spring loaded pistons press into interior wall grooves in the slot of the blade.

Abstract: A rotor head includes a hub and two joint members. The hub has opposite tubular end portions, each formed with a socket that extends inwardly from an end face thereof along a tube axis and that has inner and outer socket sections. Each of the joint members includes a link and a vibration absorbing component. The link has a hub coupling segment retained rotatably in the inner socket section of a respective socket, an intermediate segment extending from the hub coupling segment and disposed movably in the outer socket section of the respective socket, and a blade coupling segment extending from the intermediate segment and outwardly of the outer socket section. The vibration absorbing component is mounted on the intermediate segment, and is disposed in the outer socket section.

Abstract: A fan module of the present invention is disclosed. The fan module is used to be fixed on a first bottom board of a chassis and includes a frame, a circuit board, a plurality of elastic gaskets, a plurality of fixing parts and a plurality of fans. The frame has a second bottom board having a plurality of first openings. The fans are disposed in the frame. The circuit board is fixed onto the frame between the second bottom board and the fans, and electrically connected to the fans. Each of the elastic gaskets is respectively locked at a first opening of the second bottom board and contacts and interferes the first bottom board and the circuit board. In addition, each of the fixing parts respectively goes through a first opening and an elastic gasket and is fixed on the first bottom board of the chassis.

Abstract: Low-noise wind turbine blades are provided wherein metallic and/or polymeric cellular materials that are capable of bearing directional loads are used in the construction of wind turbine blade parts or entire sections. The use of such materials influences the air flow over them in such a way that the resulting boundary-layer turbulence is damped in a controlled way, thus weakening the noise scattering mechanism at the trailing edge, and the scattered acoustic waves are absorbed and attenuated by the material acting as an acoustic liner.

Abstract: A rotary body for use in a turbo machine includes a hub having an outer edge and a plurality of slots formed in the outer edge, the slots having first and second spaced-apart opposing inner surfaces extending from the outer edge to a depth within the hub, and a plurality of blades secured to the outer edge of the hub, the slots and the blades being arranged such that at least two of the blades are positioned between each pair of adjacent ones of the slots.

Abstract: An electromagnetic inertial actuator includes a support base and a parallel arrangement of a first flexure part, a voice coil motor part, and a second flexure part. The parallel arrangement is cantilevered from the support base.

Abstract: On a gas turbine rotor with internally cooled airfoils (4) of the turbine rotor blades and a mechanical sealing and damping element arranged between opposite side faces (6) of adjacent blade platforms (7), the gap is additionally aerodynamically sealed against the hot gas flow, by cooling air supplied from a cavity (5) of the airfoils via a cooling duct (9) into the gap between the side faces (6).

Abstract: A high modulus component, such as an aircraft engine turbine blade, is formed from a base metal that has a high modulus crystallographic orientation that is aligned with the primary, i.e. radial, direction of the turbine blade. The base metal is Ni, Fe, Ti, Co, Al, Nb, or Mo based alloy. Alignment of a high modulus direction of the base metal with the primary direction provides enhanced high cycle fatigue life.

Abstract: A turbine vane attachment system configured to eliminate movement of a turbine vane relative to a turbine vane carrier. The turbine vane attachment system may include a base attached to a turbine airfoil. The base may be configured to contact a wedge support along a plane that is generally nonparallel and nonorthogonal with a longitudinal axis of the airfoil. A bolt may connect the base with the wedge support. The bolt may change a distance between a channel in the base and an outer bearing surface. The turbine vane may be positioned in a vane carrier such that tongues extending from the vane carrier are positioned in the channels. As the bolt is advanced, the wedge support is moved laterally along the support surface of the base and the channels engage the tongues, thereby preventing movement of the turbine vane.

Abstract: The invention relates to a wind turbine comprising a rotor including one or more pitchable blades, and detection means for detecting edgewise oscillations in one or more of said blades. The wind turbine is characterized in that the wind turbine comprises control means for changing the pitch angle of one or more of the blades if the detection means detects edgewise oscillations in one or more of the blades, hereby damping or eliminating the edgewise oscillations. The invention further relates to a method for damping edgewise oscillations in one or more blades of a wind turbine and use hereof.

Abstract: A wind turbine blade comprising one or more oscillation dampers for damping oscillations or vibrations of the wind turbine blade. The first damper parts being rigidly connected to the blade or being a part of the blade. The dampers further comprise second damper parts, wherein the first damper part surfaces and the second damper part surfaces are arranged to move relatively to each other during the oscillations. Even further the dampers comprise a load transferring coupling, coupling the first damper part surfaces and the second damper part surfaces, so that the relative movement results in a oscillation-damping dissipation of kinetic energy.

Abstract: A turbine blade damper includes an outer part for damping vibration of the blade airfoil and a supporting inner part. The two parts are formed of different materials for the different performance required thereof in the blade.

Abstract: Cooling with regard to high-pressure turbine platforms is important in order to maintain gas turbine engine efficiency. Cottage Roof dampers located below junction gaps between adjacent platforms have been used but tend to present spent coolant flow at a high angle relative to hot gas flows about the aerofoil blades. The present arrangement has the junction gap angled such that the emergent coolant flow remains adjacent to the suction side to create a coolant film lingering above that suction side of the platform.

Abstract: A damping element for a wind turbine rotor blade is provided, the damping element comprising a laminate material made of at least one viscoelastic layer and at least one stiff layer adhered to said viscoelastic layer, wherein the damping element is adapted to be attached to a body of the rotor blade so that the at least one viscoelastic layer is in contact with the body of the rotor blade.

Abstract: A turbomachine blade comprising a root portion and an aerofoil portion, the aerofoil portion having a leading edge, a trailing edge, a concave metal wall portion extending from the leading edge to the trailing edge and a convex metal wall portion extending from the leading edge to the trailing edge, the concave metal wall portion and the convex metal wall portion forming a continuous integral metal wall, the aerofoil portion having a hollow interior defined by at least one internal surface, the hollow interior of the aerofoil portion being at least partially filled with a vibration damping material that is separated from the metal wall portions by a thermally insulating material.

Abstract: A blade of a rotor of a second stage of a compressor can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), where the axis (Z) is a radial axis intersecting the central axis of the compressor. The blade has a profile which can be identified by a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis. The blade also has a non-linearly variable trend of decreasing maximum thickness defined by the closed curves, substantially parallel to a base portion of the blade itself, fixable to the rotor. The variable trend of maximum thickness is substantially situated midway up the blade and is suitable for shifting the natural resonance frequencies of the blade itself outside a functioning velocity range of the rotor.

Abstract: The invention relates to a blade of a rotor of a ninth phase of a compressor, which can be defined by coordinates of a discreet combination of points, in a Cartesian reference system (X, Y, Z), wherein the axis (Z) is a radial axis intersecting the central axis of the compressor, the blade having a profile which can be identified by having a series of closed intersection curves between the profile itself and planes (X, Y) lying at distances (Z) from the central axis, the blade also comprising a thickening, substantially parallel to a base portion of the blade itself, fixable to said rotor, said thickening being substantially situated half-way up the blade and being suitable for shifting the natural resonance frequencies of the blade itself outside a functioning frequency range of said rotor.

Abstract: Easy to attach and detach blades for overhead ceiling fans. A first version has a ceiling fan blade with keyhole slots that fit over flat topped fasteners on a mounting arm. Pulling the blade away from the arm locks the slots to the fasteners. A second version is similar to the first and has a decorative bottom cover having snappable tapered protrusions which attach through the keyholes and into mateable through-holes in the mounting arm connection. The third version has a protruding end portion of the blade that fits into a slot in the mounting arm where spring loaded pistons press into grooves in the protrusion end portion of the blade. Latching handles allow users to manually move the pistons. A fourth version has a slot in the blade which fits about a mateable housing in the mounting arm where opposing spring loaded pistons press into interior wall grooves in the slot of the blade.

Abstract: A turbine airfoil of a turbine engine having cooling channels positioned on side surface edges of a platform of the airfoil. The platform may include at least one angled side surface that may be aligned with a side surface of a platform of an adjacent turbine blade. The airfoil may include a suction side edge formed from a first surface at an obtuse angle relative to an upper surface of the platform and a second surface at an obtuse angle relative to a bottom surface of the platform. One or more film cooling slots may be positioned in the first surface and may include a diffusion portion. A damper may also be positioned in a groove between the second surface and an adjacent platform. The damper may include cooling slots on a side surface proximate to the second surface of the suction side edge.

Abstract: A blade assembly 100 (FIG. 5) configuration that includes a means for distributing mechanical stress (e.g., a stress dissipater 54) is provided. The stress dissipater is configured to reduce the concentration of a peak mechanical stress without compromising the effectiveness of a seal between adjacent rotating blade assemblies.

Abstract: Including a disk, a plurality of circumferentially spaced apart airfoils extending radially outwardly from the disk, a plurality of shroud segments being disposed circumferentially between the plurality of airfoils and configured to attach to a corresponding airfoil of the plurality of airfoils and a plurality of wear surfaces, where at least one wear surface of the plurality of wear surfaces is configured and disposed to prevent excessive wear between the adjacent shroud segments. Each shroud segment of the plurality of shroud segments may be attached to a corresponding airfoil by weld connections to permit clearance during translation friction welding of the airfoil to the disk hub are located to avoid high stress areas.

Abstract: In a method for reducing noise generated in a turbo engine with cascades, and a stator-rotor arrangement, in which hydrodynamic pressure fluctuations occurring on the cascades are reduced by varying the surface circulation of at least one section of at least one stator. A structure is provided on one or more stators, influencing the surface circulation of at least one section of the stator.

Abstract: The balancing flyweight of a turbomachine rotor includes two pyramid shaped end parts each one having a base and an apex, and an intermediate part which connects the two bases of the end parts together. The two apexes are aligned on a longitudinal axis. The two end parts and the intermediate part exhibit, in cross section through a plane perpendicular to said the longitudinal axis, cross-sections having polygonal shapes centered on said longitudinal axis.

Abstract: An aerofoil 26 for a gas turbine engine (10, FIG. 1) comprises a cavity 38, a cellular material 42 located in the cavity 38 for stiffening the aerofoil 26, and a vibration damping medium 44 located in the cavity 38 for damping the aerofoil. The cellular material 42 is preferably a metal foam bonded to the inner surface 34a, 36a of the hollow aerofoil 26, and the vibration damping medium 44 is preferably a viscoelastic material. Various methods for fabricating the aerofoil 26 are also described.

Abstract: A vibration-isolating fixing mechanism for a fan frame. The mechanism, configured to couple the fan frame to first fastening portions of a casing, includes: coupling portions protrudingly disposed on two installation surfaces of the fan frame; positioning brackets each having second fastening portions and through-holes; resilient elements each circumferentially disposed between each coupling portion and each through-hole and extending to two through-hole-corresponding sides of each positioning bracket; and coupling elements coupled to the coupling portions respectively, positioned on one side of each resilient element facing away from the fan frame, and configured to position the positioning brackets and the fan frame relative to one another. Axial vibration isolation is achieved by insertion of the coupling portions into the through-holes circumferentially disposed with the resilient elements and by resilient contact between each resilient element and each coupling element.

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 turbine rotor blade includes a hollow airfoil joined to a platform and dovetail. A main flow channel extends longitudinally in span through the blade and is bound chordally by opposite partitions transversely bridging opposite sidewalls of the airfoil. A damper rib and transversely opposite damper pad are arranged together in a plurality of pairs spaced longitudinally apart in the airfoil and chordally positioned intermediate to the partitions to provide unobstructed forward and aft portions of the flow channel for channeling a coolant therethrough. The damper ribs and pads are configured to receive a wire damper through the channel to locally dampen vibration while minimizing obstruction of the coolant flow therethrough.

Abstract: There is disclosed a runner for a Francis-type hydraulic turbine where each runner blade has an outlet edge with two stress relieving grooves cut through the blade from the outlet edge adjacent the crown and the band. The grooves each present an opening across the outlet edge and the grooves each extend a predetermined distance from the outlet edge into the blade.

Abstract: A damping system for a turbine bucket. The damping system includes a damper pocket with a variable tangential depth and a damper pin positional within the damper pocket.

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