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.

Abstract: A system is provided for balancing a movable turbine part of a turbine or of a compressor. The system includes a balancing weight element with a first hole and a second hole and a fixing element. The first hole and the second hole are formed in such a manner that the fixing element is detachably insertable in either the first hole or the second hole. The first hole is formed in such a manner that the inserted fixing element in the first hole detachably couples the balancing weight element to the movable turbine part in a spatially fixed position. The second hole is formed in such a manner that the fixing element is receivable in the second hole.

Abstract: A motor for a fuel pump includes a rotor which includes a shaft, a rotor core and a commutator fitted on the shaft. The rotor core is formed by stacking together a plurality of aligned laminations and includes a plurality of salient poles arranged along a circumference thereof. A center line of gravity of the rotor deviates from a rotational axis of the rotor. The rotor core has a first groove in one of the poles close to the center line of gravity of the rotor. The first groove extends from a first axial end of the rotor core to an axial middle portion of the rotor core.

Abstract: A centrifugal fan includes an upstream side impeller, a downstream side impeller, a motor, and a housing arranged to accommodate the upstream side impeller, the downstream side impeller, and the motor. The housing includes a first intake port through which a gas is drawn from an outside, an exhaust port through which the gas is discharged to the outside, and a flow path defined within the housing to bring the first intake port and the exhaust port into communication with each other. The flow path includes a first wind tunnel portion positioned below the upstream side impeller to extend in a circumferential direction and arranged to receive a gas stream from the upstream side impeller and a second wind tunnel portion positioned above the downstream side impeller to extend in the circumferential direction and arranged to receive a gas stream from the downstream side impeller.

Abstract: A turbomachine system includes a turbomachine that includes a rotor that includes a rotational axis, a first rotating segment having a first mating axial mount coupled to a first axial mount of the rotor in a first installed position and a first pin configured to insert into a first inserted position in both a first slot in the rotor and a first mating slot in the first rotating segment. The first pin in the first inserted position is configured to block axial movement of the first mating axial mount relative to the first axial mount. The turbomachine also includes a second rotating segment having a second mating axial mount coupled to a second axial mount of the rotor in a second installed position. The second rotating segment in the second installed position is configured to block removal of the first pin.

Abstract: The present invention relates to a gas-turbine balancing device with at least one annular groove provided on the outer circumference of at least one intermediate or high-pressure rotor of an intermediate or high-pressure compressor, with at least one balancing element being arranged in the annular groove, and with the balancing element being moveable in the circumferential direction along the annular groove and provided with a fixing device.

Abstract: According to the invention, at least one of the counterweights (40, 40.1, 40.2, 40.3, 40.4) is mobile mounted on a guiding slot (24, 34) coaxial to the hub envelope (22, 32) that surrounds the hub (21, 31) of the corresponding propeller (2, 3), the movement of said mobile counterweight (40, 40.1, 40.2, 40., 40.4) along said guiding slot (24, 34) being controlled on the basis of an estimation of the possible unbalance of said propulsive system (1).

Abstract: A fan for an aircraft turbine engine, including an intake cone including a balancing system including a plurality of mass accommodation holes and at least one balancing mass mounted in one of the holes. The balancing system further includes an attachment mechanism exerting pressure that flattens the balancing mass against the bottom of its mass accommodation hole, the accommodation hole being made blind in the intake cone, so as to open out inside the intake cone.

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: An axial-flow turbine assembly that includes one or more features for enhancing the efficiency of the turbine's operation. In one embodiment, the turbine assembly includes a turbine rotor having blades that adjust their pitch angle in direct response to working fluid pressure on the blades themselves or other part(s) of the rotor. In other embodiments, the turbine assembly is deployable in an application, such as an oscillating water column system, in which the flow of working fluid varies over time, for example, as pressure driving the flow changes. In a first of these embodiments, the turbine assembly includes a valve that allows the pressure to build so that the flow is optimized for the turbine's operating parameters. In a second of these embodiments, one or more variable-admission nozzle and shutter assemblies are provided to control the flow through the turbine to optimize the flow relative to the turbine's operating parameters.

Abstract: An aircraft system and method with a first counterweight rotating balancing rotor mass concentration, and a second counterweight rotating balancing rotor mass concentration to balance a first aircraft propeller. The system includes an inboard electromagnetic coil driver with a first inboard electromagnetic coil, and a second inboard electromagnetic coil, the inboard electromagnetic coil driver and the first counterweight balancing rotor and the second counterweight balancing rotor centered around the aircraft propeller shaft rotating machine member. The system/method utilizes a first control system controller to control the coils and position the mass concentrations to balance the first aircraft propeller. The system/method includes a third counterweight rotating balancing rotor mass concentration, and a fourth counterweight rotating balancing rotor mass concentration to balance a second aircraft propeller which positioned and controlled by a second control system controller.

Abstract: An aircraft system/method for propeller balancing.

Abstract: There is provided a free standing tidal power plant without a dam structure set to take up kinetic energy from a water flow. The tidal power plant includes a propeller-shaped water turbine in horizontal rotor configuration with rotor blades, the rotor blades having bidirectional profiles, wherein the rotor blades are fastened to a revolving unit, which defines a rotational plane, and an electric generator at least indirectly driven by the water turbine. Each rotor blade is associated with a first swivel axis and a second swivel axis, the first axis and the second swivel axis extending substantially along a longitudinal axes of a first coupling element and a second coupling element, respectively. The revolving unit includes a planar guide region having a sliding apparatus, a first guide groove and a second guide groove, the sliding apparatus connected to the rotor blade to transmit rotor blade forces.

Abstract: By providing a tube of deformable material which can be located within a hollow cavity of a blade it is possible to provide an element which through friction engagement can absorb vibration energy and therefore damp vibration in a hollow blade. The tube incorporates a number of cuts and/or grooves in an appropriate pattern in order to define a deformation profile once the tube is expanded in location. The tube is secured in position internally upon an expandable element which is typically an inflatable device. Once in position the tube is retained in its expanded deformable profile and the engagement between the tube and the hollow cavity wall surface results in energy absorption through vibration episodes. It is possible to provide a tube formed from a shape memory alloy which will expand in location to engage the hollow cavity wall surfaces for energy absorption during vibration episodes.

Abstract: An impeller of a fan comprises a hub, a plurality of blades, a permeable shell and a permanent magnet. The hub includes a top portion and a side wall, and the inside of the top portion adjacent to the side wall includes a plurality of first balance rooms. The blades are disposed around the hub. The permeable shell is disposed within the hub. The permanent magnet is disposed within the permeable shell, and at least a portion of the first balance room is defined between the top portion and the permanent magnet. A fan is also disclosed.

Abstract: A device (10) for reducing the vibration of a rotorcraft main rotor (1) provided with a hub (2) and a plurality of blades, said device having a support (20) together with at least one weight element (30). Said weight element (30) is fastened to said support (20) by connection means (40), and said weight element (30) is connected to said connection means (40) by guide means (50) for guiding said weight element (30) in movement in circular translation in a filter plane (P1) that is movable perpendicularly to an elevation axis (AX) of said device (10), said connection means (40) including resilient return means (41) serving to allow said filter plane (P1) to move in elevation while keeping the filter plane (P1) perpendicular to said elevation axis (AX) under the effect of said vibration.

Abstract: The present invention relates to a balancing body (1) for fastening to a ring (4, 5) of a continuous blade arrangement of a compressor or turbine stage of a gas turbine, wherein the balancing body has a first stop (11) for the form-fitting attachment of the balancing body in one peripheral direction (R) to a first axial shoulder (6; 7) of the ring.

Abstract: A device for reducing structural vibrations of aerofoils in an aircraft comprises, in the region of the aerfoil tips, at least one force generator (24a) acting substantially in the direction of movement of the vibrations. This arrangement has the advantage that such a force generator (24a) is considerably less susceptible to wear than conventional aerodynamic flaps and therefore effective vibration damping is possible with a reduced outlay on maintenance and greater efficiency.

Abstract: A coaxial dual-rotor model helicopter system includes a power control mechanism, a transmission mechanism, a control mechanism and a rotor mechanism. The rotor mechanism includes an upper rotor and a lower rotor coaxially installed on an upper side and a lower side of a main shaft and controlled by an inner shaft and an outer shaft for rotating. The control mechanism includes a Bell self-balance mechanism to control the upper rotor and a Bell-Hiller control structure to control the lower rotor. The power control mechanism controls the rotor mechanism through the transmission mechanism and the control mechanism. The present invention achieves balance effect through the upper rotor by employing the Bell self-balance mechanism that has a great stability to provide automatic control. The lower rotor aims to control direction and employs the Bell-Hiller control structure that has a high maneuverability to perform active control.

Abstract: A turbine rotor balancing system comprises a circumferential array of mounting features. One or more balance weights are each mounted to the respective associated said mounting feature. Each balance weight comprises: a front wall along the forward face of the mounting feature; an aft wall along the aft face of the mounting feature; and a radially inboard wall. One or more fasteners each extend at least partially through holes of the front wall and rear wall of an associated said balance weight and through a hole of the associated said mounting feature. An abutment surface of the rotor is positioned to engage an outboard end of at least one of the front wall and aft wall of each said balance weight to resist outward radial movement of the weight.

Abstract: A propeller balancing device includes at least one stationary outer disc and a drive wheel arranged adjacent to the outer disc. The drive wheel includes magnets arranged at the periphery. A balancing weight is arranged in a groove formed in one of the outer disc or the drive wheel. A propeller including the propeller balancing device and a method of balancing a propeller are also disclosed.

Abstract: A balancing weight to balance a blower wheel. The balancing weight is constructed in two pieces consisting of a spring clip and a supplemental weight. The spring clip features a retaining section for securing on the blower wheel and a receptacle section for mounting the supplemental weight.

Abstract: A radial fan wheel arrangement includes a circular bottom plate (2) and a circular cover plate (3) with a central inflow opening (4), as well as wheel blades (6) running between the bottom plate (2) and the cover plate (3). Pocket-shaped recesses (9) are configured at least on one side of a plate surface in the space between the wheel blades (6) in an outer edge area of the cover plate (3) or the bottom plate (2) or both. At least one counterweight (13) is mounted on at least one of the two plates (2, 3) on a plate edge in an area of the pocket-shaped recesses (9).

Abstract: An assembly includes a nose piece and a boreless compressor wheel having a nose end configured for receipt of the nose piece and a receptacle at a base end configured for receipt of a rotatable shaft. A method includes fitting a nose piece to a boreless compressor wheel, measuring unbalance and, based in part on the measuring, removing material from the nose piece. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: The invention generally relates elevator assemblies suitable for lifting heavy components associated with wind turbines. In certain embodiments, the invention provides an elevator assembly encompassing a wind turbine nacelle and an elevator frame. The elevator frame is configured to surround a tower supporting the nacelle of the wind turbine and is equipped with a means for balancing the frame along a horizontal axis. In some aspects, the means for balancing the frame include a ballast tank system.

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: The present invention relates to a wind turbine tower suspension arrangement comprising magnetic attachment means adapted to magnetically secure the suspension arrangement to an inner surface portion of the wind turbine tower. The suspension arrangement further comprises guiding means adapted to guide an element suspended in a substantially longitudinal direction of the wind turbine tower, the guiding means being connected to the magnetic attachments means. Moreover, the present invention relates to the method for applying a wind turbine tower suspension arrangement.

Abstract: A method for balancing a compressor rotor assembly including a forward weldment (211) and an aft weldment (212) includes pre-balancing the aft weldment (212) of the compressor rotor assembly (210) with compressor disks (220) prior to populating the compressor disks (220) with circumferentially installed compressor rotor blades (230). Pre-balancing the aft weldment (212) includes measuring a rotational balance of the aft weldment (212). Pre-balancing the aft weldment (212) also includes determining a number of underplatform weights (260) needed and a location for each underplatform weight (260) within a circumferential slot (236) of one the compressor disks (220). Pre-balancing the aft weldment (212) further includes mounting each underplatform weight (260) in the determined location.

Abstract: A cooling fan includes a frame and a rotor received in the frame. The rotor includes a hub, blades extending outwardly and radially from the hub, and a cover plate connected with the hub. The hub includes a top wall and a sidewall extending from a circumference of the top wall. The top wall of the hub defines a plurality of blind holes on an outer surface thereof, and the blind holes are shaded by the cover plate.

Abstract: The described embodiments relate generally to cooling fans and more specifically to a method for balancing an impeller assembly included in a cooling fan. In one embodiment, a balancing ring with an asymmetric shape can be included in an impeller assembly and rotated to correct an unbalance in the impeller assembly. In another embodiment, a balancing ring assembly can be provided including an inner balancing ring and an outer balancing ring. The size and shape of the inner balancing ring can be modified to better correct any unbalance in the impeller assembly.

Abstract: A damper for a turbine rotor assembly of a gas turbine engine may include a forward plate including a forward face and an aft face, and an aft plate including a forward face and an aft face. The aft face of the forward plate may he connected to the forward face of the aft plate with a longitudinal structure. An area of the aft plate in a plane transverse to the longitudinal structure may be larger than an area of the forward plate in the plane transverse to the longitudinal structure. The damper may also include a nub projecting from a lower portion of the aft face of the aft plate.

Abstract: A blower includes a fan that causes momentum to air by rotation, a shaft that defines a rotation axis of the fan, a bearing that supports the shaft outside of the fan, and a weight that is movable in a direction of rotation of the fan. In the fan, the weight is located opposite to the bearing with respect to an end of the fan adjacent to the bearing, and thus an increase in weight by the weight can be reduced.

Abstract: A system for minimizing non-integral vibrations in rotor blades located in a compressor section of a gas turbine engine includes a casing having a plurality of bleed slots, at least one of the bleed slots being located in close proximity to a row of rotor blades, a plurality of structural ligaments, at least one of the structural ligaments extending between two adjacent ones of the bleed slots; and a channel for reducing the height of at least one of the structural ligaments so as to minimize the non-integral vibrations in the rotor blades in the row.

Abstract: A first stage compressor disk of a gas turbine engine includes a body. The body includes a forward end, an aft end, and an outer surface. The body also includes a plurality of forward balancing holes through the outer surface. The forward balancing holes align circumferentially about the body. The body further includes a plurality of aft balancing holes through the outer surface. The aft balancing holes align circumferentially about the body and are located aft of the forward balancing holes. The first stage compressor disk also includes a radial flange at the aft end of the body. The radial flange extends radially outward from the body. The radial flange includes slots for mounting airfoils.

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: The present invention relates to a device for inserting a balancing weight into a rotor of a turbine, that includes an external component and an internal component. The internal component is connected in a helical manner to the external component. The internal component delimits a chamber which has a first and a second opening, a lower surface which is provided with a sealing joint and a cap in order to close in a tight manner the first opening of the chamber. The connection between the external component and the internal component is helical, that is to say, the result of a threading operation. Therefore, the internal component can thus move in a coaxial manner with respect to the external component.

Abstract: A damper for a turbine rotor assembly of a gas turbine engine is disclosed. The damper includes a width dimension, a height dimension, and a length dimension, and a forward plate and an aft plate. The aft plate is larger than the forward plate along the width and height dimension and includes an upper portion extending in the height dimension, the upper portion having a non-symmetric configuration. The damper further includes a longitudinal structure extending in the length dimension and connecting the forward plate and the aft plate.

Abstract: An air jet wind turbine generator comprises an air jet installed at the end of each turbine blade. The air jets are perpendicular to the turbine blades and capable of outputting a recoil velocity that is also equal to or within ±20 degrees of the linear velocity of the turbine blade ends. The air jets utilize a counteracting force to accelerate or decelerate each turbine blade and to compensate the rotating speed of the wind turbine. The air volume and speed of the air jets can be adjusted via a speed sensor, thereby constantly maintaining the wind turbine generator rotating speed at the set speed.

Abstract: A turbine rotor balancing system comprises a circumferential array of mounting features. One or more balance weights are each mounted to the respective associated said mounting feature. Each balance weight comprises: a front wall along the forward face of the mounting feature; an aft wall along the aft face of the mounting feature; and a radially inboard wall. One or more fasteners each extend at least partially through holes of the front wall and rear wall of an associated said balance weight and through a hole of the associated said mounting feature. An abutment surface of the rotor is positioned to engage an outboard end of at least one of the front wall and aft wall of each said balance weight.

Abstract: A turbine disc for a turbine is provided with a first protrusion and a second protrusion. The first protrusion and the second protrusion are formed in such a way that a balancing weight is coupleable between the first protrusion and the second protrusion. The first protrusion has a sealing section that is capable of sealing a fluid passage between the turbine disc and a further turbine part of the turbine.