Abstract: A cantilever fan including a cantilever blade that is clamped at one end. The fan includes an actuator that applies a periodic force to the blade resulting in periodic deflections of the blade.

Abstract: A distributed mass device for reducing the vibration generated by a rotor, includes a support suitable for being constrained in rotation about an axis of rotation of the lift rotor. The distributed mass device further includes at least two main oscillating masses each provided with a through longitudinal recess, and each being connected to the support by respective deformable elements, the main oscillating masses being constrained to move solely in a horizontal plane by the deformable elements. The distributed mass device is provided with a secondary oscillating mass per main oscillating mass, each secondary oscillating mass being suspended inside the recess of the associated main oscillating mass by resilient elements.

Abstract: A fluid turbine comprises a rotor rotatable in use about an axis transverse to the direction of fluid flow. The rotor has a first part carrying a plurality of arcuate blades and a second part journalled in a base structure by means of two or more bearings. All the bearings are arranged on the same side of the blades so that the first part of the rotor is cantilever supported in the base structure.

Abstract: A balancing weight clip for balancing a rotor assembly of a gas turbine engine which includes a weight portion, and a first flange engaging portion and a second flange engaging portion extending from the weight portion. The weight portion and the first and second flange engaging portions define a flange receiving opening for receiving a flange of a disc of the rotor assembly. The first flange engaging portion is provided with a detent facing the second flange engaging portion and engageable with a mating groove provided on a face of the flange. At least one of the first and second flange engaging portions is elastically deformable so that the first and second flange engaging portions are elastically moveable away from one another to removably receive the flange in the flange receiving opening and engage the detent with the mating groove.

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 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: An energy saving fan comprising a pellet (1), a hub (2) connected with the pellet (1) and a plurality of curve shaped blades (3) extended radially outward from the hub (2). The roots (31) of the adjacent blades (3) are connected by a curve shaped connecting part (32) extending from the trailing edge (33) of a previous blade to the leading edge (34) of a subsequent blade. A first reinforcing rib (41) is formed on a windward surface (35) of each blade (3) from a trailing edge corner (331) to the hub (2), a second reinforcing rib (42) is formed on a leeward surface (36) of each blade (3) from a leading edge corner (341) to the hub (2), and a third reinforcing rib (43) is formed on the leeward surface (36) of each blade (3) from the hub (2) to the trailing edge (33). These reinforcing ribs improve the strength of the blade roots and prolong the service life of the blades.

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 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: A balanced rotor component for a gas turbine engine having a aerofoil with a root and an rotor with an axial aerofoil root slot. The aerofoil root has a cavity which holds a balance weight. The cavity is open along at least one wall and the balance weight is spaced from the slot wall to minimise stress concentrations.

Abstract: A rotor blade for an aircraft includes a composite portion having fiber-reinforced resin material, the composite portion having an outside surface that forms at least a partial airfoil shape. The weighted portion includes a plurality of weighted material layers and a plurality of fiber-reinforced resin material layers. Weighted material is configured to be compatible with and integrated into composite manufacturing processes used to fabricate the rotor blade. The weighted portion has a higher density than the composite portion and positioned to produce desired mass balance characteristics of the rotor blade.

Abstract: Shaft trim balancing devices, related systems and methods are provided. In this regard, an representative device for trim balancing a rotatable shaft includes: an intermediate section being annularly shaped and having terminating ends spaced from each other in an uncompressed state of the device; and first and second sets of counterweights extending longitudinally from opposing sides of the intermediate section.

Abstract: A damper device (10) for a rotor (2) having a rotary ring (11) and a plurality of levers (12), each lever (12) extending from a first end (12?) connected to said ring (11) by a first mechanical connection (20) to a second end (12?) suitable for being hinged to a blade (4). The damper device (10) includes non-rotary damper means (30) secured to non-rotary fastener means (40) and to a non-rotary member (51) of an interface (50), said interface (50) being interposed between said non-rotary damper means (30) and said ring (11) to convert a rotary movement of a blade (4) transmitted to a lever (12) into a movement in translation acting on said damper means (30).

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

Abstract: An impeller includes an impeller body which rotates about a rotation axis, and a vane which is provided at the impeller body. The impeller body receives force asymmetric with respect to the rotation axis in driving and rotation in a fluid in a manner that radially inward fluid force, which is generated due to arrangement of the vane, acts on a predetermined point in a peripheral direction. In the impeller body, a filled space filled, in a fluid, with the fluid is formed.

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 round axial fan with balancing structure includes a hub, a ring-shaped band located around an outer side of the hub, and a plurality of blades extended between the hub and the ring-shaped band. At least one removable area is defined on the ring-shaped band for serving as a balancing area. By determining and removing one or more balancing areas at appropriate locations from the ring-shaped band, uneven weight distribution of the components of the round axial fan can be adjusted to enable stable rotation of the fan without producing vibration. The provision of the balancing area on the ring-shaped band of the round axial fan also enables reduced material and labor costs for adjusting the weight distribution of the fan.

Abstract: An apparatus and method for balancing a gas turbine engine rotor includes a plurality of balancing weights adapted to be selectively attached to at least one of inlets or outlets of a cooling passage of the rotor. The weights include cooling access which permits coolant to communicate with the cooling passage.

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: An aircraft turbomachine fan is disclosed. The fan includes a turbomachine inlet cone that has an exterior surface intended to be closely followed by a flow section of the turbomachine, and an annular balancing flange that rotates as one with a fan disk about an axis of rotation and is equipped with a plurality of weight-fixing holes. The fan also includes one or more balancing weights mounted fixedly on the annular balancing flange. The annular balancing flange is positioned inside the inlet cone in such a way that its weight-fixing holes are isolated from the flow section. The flange is produced as a single piece with a fan blade retaining ring.

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: 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 balancing method and system for a partial pitch rotor blade for a wind turbine is described. Balancing elements are mounted to the pitch system of the rotor blade, which remove the need for complicated balancing operations to be performed which may affect the structural stability of the rotor blade body. A method is described wherein a suitable compensating balancing weight for mounting to the pitch system may be used, the weight chosen based on the known tip and root weights of standard blade extender and rotor blade parts used.

Abstract: A rotary wing aircraft including a vehicle vibration control system.

Abstract: A balance weight for a rotor includes: (a) an arcuate body including a front wall and a rear wall interconnected by an end wall, the front, rear, and end walls collectively defining a generally U-shaped cross-sectional shape; and (b) a projection extending outwardly from the rear wall, the projection being adapted to engage an aperture extending through a flange of the rotor.

Abstract: A wind power conversion apparatus driven by a fly wheel includes a wind channel, a fly wheel and a rotating shaft. The wind channel is configurated into a long hollow tapered tubular shape with both ends open. One end, which being larger is cross section, serves as a wind inlet, while to other smaller one serves as a wind outlet so as to conduct the wind flow into the apparatus via the wind channel. A fly wheel with several wind vanes is installed in the wind channel proximate to the wind outlet so as to convert the wind force into an adjustable rotating torque of the fly wheel. The fly wheel is able to keep rotating about the rotating shaft by its inertia for a certain duration of time even after the wind ceases to blow. With this apparatus, the kinetic energy of the wind blow is converted into an adjustable and storable mechanical energy to utilize.

Abstract: In the manufacture of integrally designed rotor wheels (BLISKs), the natural frequency of each blade is measured after forming by conventional shaping methods and the respective blade mass and its divergence from the smallest blade mass is calculated therefrom. The mass of each blade exceeding the smallest blade mass is removed by means of an etchant, so that all blades have essentially corresponding thickness, chord length, mass and natural frequency and are evenly loaded in operation. BLISKs manufactured in this way feature a long service life.

Abstract: The invention relates to a fan wheel (6) for a blower module (2), comprising a hub (5) and a radial fan ring (8) composed of a plurality of fan blades (12) and further comprising means for resolving imbalances in the fan wheel (6). According to the invention, balancing weights (18) can be fastened to the radial ends of the fan blades (12).

Abstract: A balancing cover connected with a rotor structure includes a plate, a plurality of blades and at least one balancing element. A central portion of the plate has an opening. Each blade has one end connected with the plate and mounted on a circumference of the opening, and the other end connected with the rotor structure. Each blade has at least one hole, in which the balancing element is disposed.

Abstract: Turbochargers operate at extremely high speed, so balance of the rotating core is of the utmost importance to turbocharger life. A special frusto-conical, or frusto-spherical, centering geometry is added to the interface of the compressor nut and the nose of the compressor wheel to aid in keeping the wheel, nut, and stub-shaft centered on the turbocharger axis to reduce the degree of core unbalance.

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: 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: Method and apparatus for vibration-based automatic condition monitoring of a wind turbine, comprising the steps of: determining a set of vibration measurement values of the wind turbine; calculating a frequency spectrum of the set of vibration measurement values; calculating a cepstrum of the frequency spectrum; selecting at least one quefrency in the cepstrum, and detecting an alarm condition based upon an amplitude of the cepstrum at the selected quefrency, and a wind turbine therefor.

Abstract: A rotary blade rotating hub mounted rotating assembly vibration control system (20) including a first imbalance mass concentration rotor (28), a second imbalance mass concentration rotor (44), a third imbalance mass concentration rotor (38?), and a fourth imbalance mass concentration rotor (44?). The first imbalance mass concentration rotor has a first imbalance mass concentration rotor center axis of rotation (136) centered on the rotating assembly center rotation axis (28). The second imbalance mass concentration rotor has a second imbalance mass concentration rotor center axis of rotation (142) centered on the rotating assembly center rotation axis. The third imbalance mass concentration rotor has a third imbalance mass concentration rotor center axis of rotation (136?) centered on the rotating assembly center rotation axis. The fourth imbalance mass concentration rotor has a fourth imbalance mass concentration rotor center axis of rotation (142?) centered on the rotating assembly center rotation axis.

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: The invention relates to an engine fan device for a vehicle, characterized in that the engine fan device (10) has at least one or more receiving contours (24, 30, 50), in which one or more balancing elements (28) can be received, wherein at least one receiving contour (24) has at least two planes (26), and/or wherein at least two receiving contours (24) each have at least one plane (26), wherein both planes (26) are different from each other.

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: An aircraft including at least one engine having counter-rotating rotors, the engine or at least one of the engines having imbalances associated with at least one ellipse. The aircraft includes at least one vibration damper attached in an arrangement such that, at a given engine speed and for at least one given common direction of a large axis of the ellipse or at least one of the ellipses, a speed related to the two ends of the damper is higher than for any other arrangement of the damper.

Abstract: An impeller includes an impeller body in which an internal flow path and a recessed section are formed; a lid covering an opening of the recessed section; and a balance weight arranged between the impeller body and the lid. The lid is attached and fixed to the impeller body through an engagement section. Holding sections for the balance weight are formed in a back-side surface of the lid. When attaching and fixing the lid to the impeller body, the balance weight is sandwiched between the holding section of the lid and the impeller body to be fixed.

Abstract: A method for reducing vibration in a rotary system (140; 240a; 240b; 340a; 340b) of an aircraft (100), for example an aeroplane or a rotorcraft, such as a helicopter, comprising balancing said rotary system (140; 240a; 240b; 340a; 340b), characterized by providing a substantially circular chamber (232a, 233a, 234b, 235a, 236a, 237a; 232b, 233b, 234b, 235b, 237b; 335a; 335b; 433a; 433b; 433c; 535a; 535b; 535c) having a fulcrumon an axis (260a; 260b; 360a; 360b; 460a; 460b; 460c; 560a; 560b; 560c) of a shaft (131; 231a; 231b; 331a; 331b; 431a; 431b; 431c; 531a; 531b; 531c) of said rotary system (140; 240a; 240b; 340a; 340b) and being partially filled with an amount of a thixotropic balancing substance (338a; 338b; 438a; 438b; 438c; 538a; 538b; 538c). An apparatus, and a system, for reducing vibration in a rotary system (140; 240a; 240b; 340a; 340b) of an aircraft (100) according to the method.

Abstract: An impeller include a substantially cylindrical impeller body with an internal flow path connecting between an inlet opening through a first end surface and an outlet opening through a circumferential surface; and a balance weight embedded in the impeller body. The balance weight has a vertically-elongated shape in which its height in a cylindrical axis direction is larger than its thickness in a radial direction. The vertically-elongated balance weight is embedded in a circumferential section of the cylindrical impeller body.

Abstract: A fan rotor includes a hub (10), a plurality of blades (20) radially disposed around the hub, and a magnet (30) located in an inner side of the hub. The hub includes a top wall (12) and a sidewall (14) surrounding the top wall. A plurality of spaced first ribs (17) is disposed between the top wall of the hub and a top wall of the magnet. A plurality of spaces (171) is formed between adjacent first ribs for accommodating equilibrium clay (50) therein.

Abstract: A balancing weight clip with a mass adapted to balance a rotor assembly of a gas turbine engine, includes a weight portion, a first flange engaging portion and a second flange engaging portion extending from the weight portion, each being engageable with a sidewall of at least one recess located on an edge of a flange of a disc of the rotor assembly. Each flange engaging portion is provided with a hook engageable with a mating groove provided on a face of the flange. At least one of the first and second flange engaging portions is resiliently biased so that the first and second flange engaging portions are elastically moveable away from one another to removably secure the balancing weight clip to the flange and engage each hook with the mating groove.

Abstract: An apparatus and method for balancing a gas turbine engine rotor includes a plurality of balancing weights adapted to be selectively attached to at least one of inlets or outlets of a cooling passage of the rotor. The weights include cooling access which permits coolant to communicate with the cooling passage.

Abstract: A method of balancing an assembly of rotary parts of a gas turbine engine comprising measuring at least one of the concentricity and parallelism of each component and considering globally all possible component stacking positions to generate an optimized stacking position for each component of the assembly to minimize assembly unbalance.

Abstract: A balancing assembly for a rotor assembly of a gas turbine engine includes a flange engaging portion defining a flange receiving opening for mating with the flange in a slidable manner. A hole extends through at least part of the flange engaging portion, the hole corresponding in size to a recess and adapted to receive a rivet or other suitable fastener to fix the balancing weight with respect to the disc.

Abstract: The aircraft is capable of two distinct fuel-efficient flight regimes: one is a vertical flight regime supported by two large two-bladed rotors with low disc loading located on right and left longitudinal booms. The booms extend between outboard regions of a front wing and inboard regions of a rear wing that has a larger span an area. The other flight regime is high speed up to high subsonic Mach number with the aircraft supported by wing lift with high wing loading, and with the rotors stopped and faired with minimal local drag contiguous to the booms. The longitudinal location of the aircrafts center of gravity, aerodynamic center and the center of the rotors are in close proximity. The front wing is preferably swept back, and the rear wing is preferably of W planform.

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 self-contained water generation system is disclosed. The present system allows for the generation of water using only wind power and standard air conditioning components. A wind turbine drives, directly or indirectly, a compressor that compresses refrigerant and provides the refrigerant to a condenser and evaporator. During the evaporation of the refrigerant, water is condensed and collected for use. The components of the water generation system may be configured in a housing and movably mounted atop a column so that the housing can rotate about the column, allowing the wind turbine maximize the use of wind forces.