Abstract: A balance weight for a turbine rotor includes: (a) a block-like centerbody; (b) a pair of resilient spring arms extending laterally from opposite sides of the centerbody, the centerbody and the spring arms collectively defining an arcuate shape; and (c) at least one locating structure extending from a radially outer surface of the balance weight.

Abstract: A weight adjustment portion is formed at an upper end of a hub to project radially inward. An approximately U-shaped balance clip is attached to the weight adjustment portion. A gap to be constantly ensured is formed axially between the weight adjustment portion and a rotor holder. For ensuring the gap, a plurality of seats are provided on the lower surface of the weight adjustment portion at regular circumferential intervals. The rotor holder is press-fitted to the hub until the rotor holder comes into contact with the seats. The upper surface of the weight adjustment portion is positioned lower than the uppermost portion of the hub, thereby preventing the balance clip projecting from the uppermost portion of the hub when the balance clip is attached to the weight adjustment portion.

Abstract: The present invention relates to a concentrated-mass device including a main oscillating mass held radially in a horizontal plane by main resilient element inside a casing suitable for being secured to the hub. The device includes a secondary main oscillating mass suspended by secondary resilient element inside a recess in the main oscillating mass to oscillate along a vertical axis perpendicular to the horizontal plane, the secondary oscillating mass being constrained to move in translation together with the main oscillating mass in the horizontal plane.

Abstract: Described is a fan with a blade suitable for use as a ceiling fan. The blade may be regarded as a single blade, although shaft is not attached to blade at one end thereof; rather, shaft is attached to blade at a point between first end and second end. Blade is balanced by counterweights located in blade. In one embodiment, blade is connected to shaft by means that permit angular movement, such as a teeter hinge.

Abstract: A balance weight adapted to be assembled to a nose cone assembly of a turbine engine for improving a balance of the nose cone assembly is disclosed herein. The balance weight is one-piece and formed from a plurality of different materials including at least first and second materials. The first and second materials are arranged substantially heterogeneously relative to one another such that said first and second materials are separate from one another and fixed together.

Abstract: An impeller for a centrifugal pump that includes a disk-shaped shroud having a central axis, a front surface, a rear surface, and a circular perimeter, and a hub at the center of the shroud, the hub having an axial bore. The impeller further includes a first set of vanes on the front surface of the shroud, the first set of vanes extending radially inward from the perimeter towards the hub, a second set of vanes on the rear surface of the shroud, the second set of vanes extending radially inward from the perimeter towards the hub, a balancing area on the rear surface of the shroud, the balancing area extending radially outward from the hub, and a number of openings in the shroud, the number of openings configured to allow a fluid to pass from one side of the shroud to the other.

Abstract: A vertical axis wind turbine (VAWT) assembly effects sharing of the axial load on its bearings to increase equipment life and/or effective operation. The assembly includes: a support; a VAWT (e.g. Savonius) having a substantially vertical shaft; at least lower and upper substantially vertically spaced bearings mounting the shaft for rotation about a substantially vertical axis, the bearings operatively mounted by the support; and a load-sharing assembly connected to the upper bearing which allows the bearings to share at least 10% (such as 50-50) of the axial load. The load sharing assembly may include a spring surrounding an upper portion of the shaft, and operatively engaging the upper bearing. The shaft may include an upper shall extension, and the load sharing assembly a spring end cap operatively connected to the upper shaft extension and holding the spring against the upper bearing.

Abstract: A centrifugal impeller employed in a centrifugal machine, includes a main body, the main body generally being conical and defining a shaft bore in a center portion thereof; and a plurality of blade groups evenly arranged surrounding the shaft bore in sequence, each of the blade groups having a plurality of blades wherein neighboring blades having an interval angle, and the number and corresponding interval angles of the blades of different blade groups are identical. The present impeller structure can be employed to distribute the concentrated energy of the discrete tones noise of the blades, which is generated by the high-speed rotation impeller, and further to reduce the operating tones noise.

Abstract: A balancing assembly for use in a wind turbine having at least one pair set of blades, the balancing assembly comprising a ballast and a ballast receiving structure on at least one blade of the pair set of blades. The ballast provides a threaded portion for engagement with the ballast receiving structure. The ballast further provides at least one end configured with a drive socket for driving said ballast into said ballast receiving structure. The ballast is capable of being trimmed to achieve a predetermined mass necessary to achieve a balance between the blades in the pair set of blades.

Abstract: A rotor for a helicopter, having: a hub rotating about an axis and in turn having a number of blades; and an at least partly hollow drive shaft connectable to a drive of the helicopter and connected functionally to the hub to rotate the hub about the axis; the rotor also having vibration damping means in turn having a mass, and an elastically deformable member connected to the mass and supported by the shaft; the member extending at least partly inside the shaft, and being elongated parallel to the axis; and the mass vibrating, in use, at such a frequency as to oppose transmission to the shaft of the vibration produced by rotation of the hub and blades.

Abstract: A structure of a balancing fan is disclosed. The fan comprises a hub and a rotation balancing unit. The hub comprises a top portion and a ring portion disposed around the top portion. A plurality of blades extends from the hub. The rotation balancing unit is disposed among the outer side of the top portion and the inner side of the ring portion and comprises a guiding portion and at least one movable weight member. The movable weight member is positioned on the inner side of the guiding portion such that the movable weight member can move along the guiding portion when the hub rotates to provide the dynamic-balance effect and thereby stabilize the rotation of the fan.

Abstract: A rotor disc, such as one made of a damage intolerant material or other material sensitive to stress concentrations, has at least one balancing assembly which includes a plurality of circumferentially spaced-apart sacrificial protrusions projecting between adjacent stress-relieving slots. Selective material removal is permitted from the rotor disc, while managing stress concentrations in the rotor disc created by such material removal, such that the rotor disc may be balanced without detrimentally affecting its service life.

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

Abstract: A VAWT wind engine includes a support structure, an articulating rotor mounted on the support structure for rotation about a vertically extending axis, and at least one airfoil on the rotor for rotor-powering purposes. The articulating rotor is mounted in a manner enabling tilting movement of the rotor during rotation so that the airfoil produces rotor rotation and rotor tilt as the airfoil orbits the rotational axis. At least one mechanical linkage is included to actively vary airfoil pitch according to rotor tilt. The partially articulating rotor of a teetering-rotor embodiment seesaws up and down about a horizontally extending pivotal axis. The fully articulating rotor of another embodiment supports three airfoils as it tilts in any direction by virtue of a gimbal or other rotor hub assembly providing a 360-degree swiveling action, while furling hinges help protect the airfoils against damaging winds during wind engine shutdown.

Abstract: This invention provides convenient airframe vibration and tracking improvements of a helicopter rotor blade by use of an elastomer profile system that is attached through an adhesive system that allows convenient removal and relocation for use by the helicopter manufacturer or by the helicopter operator in a field environment.

Abstract: A method for manufacturing a turbine damper by a metal injection molding process is disclosed. The damper includes a base section and a wire section, and is formed of a nickel-base or cobalt base superalloy.

Abstract: The present invention relates to a turbomachine rotor balancing system (61) comprising a balancing flange (52) provided with through-passageways (78) and also comprising balance weights (54) mounted fixedly on the balancing flange by means of at least one screw/nut assembly (56) passing through one of the passageways. According to the invention, for each of the passageways (78), the flange (52) has on its first face (90) a first recess (94) passing via the radial summit (80) of the passageway, this first recess being deprived of contact with the screw head (86) pressing on this face (90), the flange (52) having on its second face (92) a second recess (98) passing via the radial summit (80), this second recess being deprived of contact with the balance weight (54) pressing on this face (92).

Abstract: Vibration is monitored in a dual rotor engine. A first total vibration of the engine is measured during operation. Relative phase of the two rotors is then clocked, and a second total vibration of the engine is then measured during operation. First and second total unbalances are then resolved at a common response frequency from the measured total vibrations. First and second rotor unbalances are then resolved for the corresponding rotors from the first and second total unbalances. In a further method, corresponding corrective balance weights may be determined for offsetting the resolved rotor unbalances.

Abstract: A steam turbine rotor is provided. The rotor includes at least one bearing section coupled axially to a steampath section comprising at least one end, said at least one end further comprising a flange and a bore, said flange and said bore configured to be coupled to the at least bearing section.

Abstract: A method and apparatus for assembling a rotatable machine is provided. The machine includes a first set of blades that extend radially outwardly from a rotor assembly and wherein a second set of blades is available for installation on the rotor assembly. The method includes determining at least one of a moment weight of each blade in the first set of blades and a geometric parameter of each blade in the first set of blades, determining at least one of a moment weight of each blade in the second set of blades and a geometric parameter of each blade in the second set of blades, and determining a mapping order of each blade for the rotor assembly using the moment weight and the geometric parameter of each blade in the first set of blades and the moment weight and the geometric parameter of at least one blade in the second set of blades.

Abstract: A rotor having at least two flightings includes a plurality of elongated support ribs rigidly interconnecting at axially spaced intervals, the outer edge of a first flighting with the inner edge of the other flighting, the ribs having a connecting boss at a distal end and a balancing mass intermediate a proximal end and the distal end. A method of forming the rib is further included.

Abstract: A rotor balance fitting to balance an aircraft rotor includes a ring, bore, and cup. The ring includes an inner surface configured to mate with an outer surface of a blade for the aircraft rotor. The bore is disposed through the ring and configured to receive a blade pin that passes perpendicularly through an axis of the blade and secures the blade to the rotor. The cup is disposed in the ring and is configured to secure a weight.

Abstract: A method of calibrating the mass of components intended to be mounted at the periphery of a rotor, the method consisting, for each of the components, in removing by machining a volume of material in a region of the component situated on one of its axes of inertia in order to bring the mass of the component to a predetermined value.

Abstract: The invention relates to 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. The invention further relates to a wind turbine, an oscillation damper, a method for damping oscillations of a wind turbine blade and use hereof.

Abstract: A rotating machine includes a stationary member and a rotating member moveable relative to the stationary member. The rotating member includes at least one balancing member assembly receiving portion having a plurality of internal threads. The rotating machine also includes a balancing member assembly including first and second interlocking balancing members. The balancing member assembly also includes a plurality of external threads that are operatively connected to the internal threads of the balancing member assembly receiving portion. With this arrangement, the balancing member assembly provides a dynamic balance for the rotating member.

Abstract: A rotor for a rotating machine, in particular a steam turbine includes at least one subregion composed of a metal structure having a reduced density and including a multiplicity of finely distributed cavities.

Abstract: A balancing group (22) is described for the rotor of a fluid rotary machine (10), wherein the rotor is of the type comprising at least one shaft (16) equipped with an internal pass-through hole (20) which develops along the longitudinal axis (A) of the shaft (16). The balancing group (22) includes at least a first inner element (24) and at least a second outer element (26), the first inner element (24) being suitable for being engaged by interference, in the direction of the longitudinal axis (A), inside the second outer element (26). The balancing group (22) thus formed is suitable for being inserted, in the direction of the longitudinal axis (A), inside the pass-through hole (20) of the shaft (16).

Abstract: The present invention relates to an aircraft turbomachine fan (1) comprising a turbomachine inlet cone (20) that has an exterior surface (19) intended to be closely followed by a flow section (22) of the turbomachine, an annular balancing flange (34) that rotates as one with a fan disk (4) about an axis of rotation (2) and is equipped with a plurality of weight-fixing holes (24), the fan also comprising one or more balancing weights (26) mounted fixedly on said annular balancing flange. Furthermore, the annular balancing flange (34) is positioned inside the inlet cone (20) in such a way that its weight-fixing holes (24) are isolated from the flow section (22). According to the invention, the flange (34) is produced as a single piece with a fan blade retaining ring (16).

Abstract: A method to introduce a deliberate mismatch into a turbomachine bladed wheel so as to reduce vibration amplitudes of the wheel in forced response. The method includes a step of determining an optimum value of the standard deviation for the mismatch as a function of operating conditions of the wheel inside the turbomachine, with respect to the maximum vibration amplitude response required on the wheel. The method further includes a step of at least partly placing blades with different natural frequencies on the wheel such that the standard deviation of the frequency distribution of all blades is equal to at least the mismatch value, the mismatch value being determined statistically.

Abstract: A method of ordering blades in a rotatable machine that includes a plurality of blades that extend radially outwardly from a rotor is provided. The method includes receiving at least one geometric parameter measurement of each blade in a row of blades, determining a maximum difference of at least one of the received geometric parameter measurements between adjacent blades in the row of blades, determining a vector sum of at least one of the received geometric parameter measurements, determining a plurality of moment weight vector sums of the rotor, and determining, using a computer, a sequence map of each blade using the maximum difference of the at least one geometric parameter measurement between adjacent blades in the row of blades, the vector sum of the at least one received geometric parameter measurement, and the plurality of moment weight vector sums.

Abstract: A device for balancing a turbomachine rotor includes at least one counterweight fitted to the rotor, wherein the counterweight includes two radial bearing surfaces oriented in two opposite radial directions, the said surfaces interacting with two radial bearing surfaces made on the rotor, the counterweight being held against the rotor by an axial retention device. In particular, the axial retention device can be a bolt with a nut, the bolt holding the counterweight against a coupling flange fixed ly attached to the rotor, including an axial bearing surface and the radial bearing surfaces.

Abstract: A cooling fan includes a fan housing (30) having a central tube (34) extending upwardly therefrom, a bearing (60) being received in the central tube, a stator (20) being mounted around the central tube, and a rotor (10) having a shaft (18) extending through the bearing. At least one notch (180, 184) is defined in an end of the shaft. A balance structure (62) is mounted around the shaft, and has a portion facing and surrounding an upper portion of the at least one notch of the shaft. The balance structure is made of magnetic material, which can attract the shaft downward to thereby counter the upward force generated by the rotor when it is driven to rotate. Accordingly, the noise problem incurred by the floating of the rotating rotor can be resolved by the present invention.

Abstract: A method of manufacturing a rotating component (110), the method comprising the following steps: providing a component comprising a first portion (20, 40, 60, 80, 100, 116), which first portion defines a first cavity (26, 46, 66, 86, 106), characterised by; identifying a first inertial property of the first portion and/or the entire component, introducing material (28, 48, 68, 88, 108) into the first cavity to achieve an adjusted inertial property of the first portion and hence a desired inertial property of the component. A rotating component (110) comprising: a first portion (20, 40, 60, 80, 100, 116) defining a first cavity (26, 46, 66, 86, 106), a second portion (118) defining a second cavity, the second portion being circumferentially spaced from said first portion, characterised in that the first cavity has a first material (28) deposit therein, said material having predetermined inertial characteristics so as to adjust the centre of mass (Z) of the rotating component.

Abstract: A method for balancing a rotor of a rotary machine, wherein the rotor includes at least two rotor blades and a rotor shaft, includes receiving at least one measurement of either a load, an acceleration, or a displacement that pertains to at least one bending moment acting on the rotor shaft, determining at least one value of the at least one bending moment acting on the rotor shaft based, at least in part, on the received at least one measurement, and determining a pitch offset angle value of at least one rotor blade that facilitates reducing the at least one bending moment acting on the rotor shaft.

Abstract: A method of manufacturing an electrical suction unit for use in a vacuum cleaner includes a turbine unit and an electrical motor with a rotor and a stator. The turbine unit is attached to the rotor and forms, together with the rotor, a rotatable part of the suction unit, which is rotatable about an axis of rotation. An amount of material is removed from the rotor and from the turbine unit to torque-balance the rotatable part of the suction unit. In this manner, the amount of material to be removed from the rotor to torque-balance the rotatable part is considerably reduced, so that the adverse influence of the removal of the material from the rotor on the performance of the electrical motor is limited.

Abstract: A method of correcting the balance of a gas turbine formed so that a balance between the generator side shaft end of a rotor and the shaft end of the gas turbine can be corrected within the range of service rotational speed. In the method, after the rotor is assembled in a casing, the balance is corrected while the rotor is rotated up to a high service rotational speed to remove its residual unbalance at the high rotational speed at which an unbalance due to the elastic deformation of the rotor occurs so as to reduce a vibration due to the unbalance. Accordingly, when the gas turbine is assembled, the residual unbalance resulting from the assembly of the gas turbine, a compressor, and a generator formed on a same rotating axis can be reduced. As a result, the gas turbine which does not increase a vibration at a critical speed can be provided.

Abstract: A centrifugal fan includes a plurality of blades, a first wall disposed at first axial ends of the blades, and a second wall disposed at second axial ends of the blades and having a shaft portion at a center. At least one of the first wall and the second wall has a cutout portion configured to control balance.

Abstract: Dynamically balanced molded blade assemblies may be formed. A face plate of a dynamically balanced molded blade assembly may have one or more openings and/or one or more protrusions so that the blade assembly is within acceptable balance tolerance when rotated by a motor shaft of a fluid moving device.

Abstract: Methods and systems for ordering blades in a rotatable machine is provided. The method includes receiving at least one geometric parameter measurement of each blade in a row of blades, determining a root sum squared value of a difference of a selected one of the received geometric parameter measurements between adjacent blades in the row of blades, determining a vector sum of a selected other one of the received geometric parameter measurements, determining a moment weight vector sum of each blade to be positioned on the rotor, and determining, using a computer, a sequence map of each blade using the root sum squared value of the difference of the geometric parameter measurement between adjacent blades in the row of blades, the vector sum of a selected other one of the received geometric parameter measurements, and the moment weight vector sum.

Abstract: Methods and systems of balancing a rotatable member are provided. A method includes separately balancing a first portion and a second portion of the rotatable member wherein the second portion mateable to said first portion, coupling the first and second portions to each other, measuring a physical dimension of the coupled first and second portions, and determining a balance weight magnitude and position based on the measured physical dimension.

Abstract: A device for balancing a rotating part, in particular a turbine rotor in a turbomachine such as a turbojet or the like, the device comprising at least one balance weight comprising engagement means for engaging it on an annular flange of the part, and locking means associated with the balance weight and with the annular flange to prevent the balance weight from moving relative to the annular flange and to block itself against moving both in rotation and in axial translation relative to the balance weight.

Abstract: A method of balancing a movable rotating object having multiple radial projections, such as a ceiling fan, the method comprising the steps of: attaching to a non-rotating portion of the object a source that emits a focused light, directing the focused light at a target, and then attaching a weight to a location on one of the rotating projections. Then observing the orbit traced by the light source on the target, changing the location of the weight to another location on one of the radial projections, and then observing the change in the orbit on the target.

Abstract: A method, system, and balanced rotating assembly are provided for field balancing an assembly including a power turbine. The method, system and assembly includes coupling the power turbine to a load, identifying a first balancing plane that is aft of the power turbine, and identifying a second balancing plane that is forward of the power turbine. A balancing correction is determined at each of the first and second balancing planes. A balance weight is mounted at the first balancing plane based on the balancing correction determined for the first balancing plane, and a balance weight is mounted at the second balancing plane based on the balancing correction determined for the second balancing plane, wherein each balance weight is coupled to at least two respective bolt head without removing the bolts.

Abstract: The present invention relates to a turbomachine rotor balancing system comprising a balancing flange (52) provided with through-passageways (78), the system further comprising balance weights (54) each mounted fixedly on the flange (52) by means of a first and a second screw/nut assembly (56a, 56b) having a first and a second screw (84, 84) passing through a first and a second passageway (78, 78). According to the invention, said first screw is pressing against a first tangential end side (116) of the first through-passageway, and at a distance from a second tangential end side, and the second screw is pressing against a second tangential end side (118) of the second through-passageway, and at a distance from the first tangential end side.

Abstract: A rotor disc includes a rim and a balancing device, which includes housings formed in the rim, and balancing masses housed in at least some of the housings.

Abstract: A structure of a balancing fan is disclosed. The fan comprises a hub and a rotation balancing unit. The hub comprises a top portion and a ring portion disposed around the top portion. A plurality of blades extends from the hub. The rotation balancing unit is disposed among the outer side of the top portion and the inner side of the ring portion and comprises a guiding portion and at least one movable weight member. The movable weight member is positioned on the inner side of the guiding portion such that the movable weight member can move along the guiding portion when the hub rotates to provide the dynamic-balance effect and thereby stabilize the rotation of the fan.

Abstract: A method of balancing a rotor, where the rotor comprises a plurality of holes, comprises the steps of measuring an imbalance of the rotor, identifying at least one characteristic dimension associated with at least one hole, identifying a change to the or each characteristic dimension to reduce the imbalance, and changing the or each characteristic dimension.

Abstract: A rotatable member is adapted for dynamic balancing by the addition of balancing weights in the form of high speed projectiles fired at the member during rotation in timed relationship with the rotation of the member so as to impact the member at specific circumaxial locations required for balancing the member. The member has an annular groove for receiving the projectiles and securing the same at the desired locations. The groove has a cross sectional configuration slightly smaller than that of the projectile in at least one direction of measurement so as to engage and capture the projectile in retention in the groove.

Abstract: An apparatus for balancing a shaft of an aircraft engine preferably includes a nose cone and the use of standard fasteners. The nose cone is adapted to cooperate with at least one standard fastener to retain the standard fastener to the nose cone to rotationally balance the shaft.

Abstract: An apparatus for balancing a shaft of an aircraft engine preferably includes a plate and the use of standard fasteners. The plate provides mounting for a nose cone, and the balancing apparatus may be accessed from the front of the assembled engine.