Abstract: A wind turbine blade measurement system for optically determining a torsion of a wind turbine blade is disclosed. The wind turbine blade measurement system comprises: a wind turbine blade, which is configured to be mounted to a hub of a wind turbine, a first camera, and an auxiliary camera. The first camera is mounted in a fixed position on a support structure on an exterior surface of the root section of the wind turbine blade and arranged so as to measure along the spanwise direction of the wind turbine blade. The auxiliary camera is arranged at a position outside of the wind turbine blade, the auxiliary camera being arranged so as to being able to carry out measurements of a plurality of sets of markers arranged on the surface of the wind turbine blade and an orientation of at least one of the support structure and the first camera.

Abstract: A multisensory system provides both temporal and spatial coverage capacities for auto-detection of bird collision events. The system includes an apparatus having a first circuitry to capture and store a series of images or video of a blade of a wind turbine; and a memory to store the images from the first circuitry. The apparatus also has one or more sensors to continuously sense vibration of the blade or for acoustic recordings; and a second circuitry to analyze the sensor data stream and/or the series of images or video to identify a cause of the vibration and to trigger the camera(s). A communication interface transmits data from the second circuitry to another device, wherein the second circuitry applies artificial intelligence or machine learning to control sensitivity of the one or more sensors.

Abstract: A rotor blade for use in a turbine of a combustion turbine engine comprises an airfoil, which includes a concave pressure and convex suction sidewall extending axially between corresponding leading and trailing edges and radially between base and outboard tip end. The rotor blade further including at least one mid-span shroud engages a corresponding mid-span shroud on at least one neighboring rotor blade. The airfoil includes an inboard region between the at least one mid-span shroud and base of the blade—and an outboard region between at least one mid-span shroud and outward tip. The outboard region includes at least two cavities extending from the outboard tip end inboard toward the at least one mid-span shroud; and inboard of the at least one mid-span shroud, the inboard region is substantially solid.

Abstract: A multimodal renewable energy generation system for generating electric power from more than one renewable energy source is disclosed herein. The system includes two or more spinner units configured on a vertical pillar. The spinner units are configured for rotation under influence of a stream of a corresponding fluid. A set of electric power generators is operatively coupled to each of the two or more spinner units to generate electric power when the corresponding spinner unit rotates. At least one of the two or more spinner units is configured close to a base portion of the pillar to harness power from sea waves and remaining of the two or more spinner units are configured with an upper portion of the pillar for harnessing power from wind. The spinner units are configured for rotation in a horizontal plane even at less powerful winds or water streams.

Abstract: The present invention relates to a method of correcting rotor imbalance and a wind turbine thereof. The correction method comprises measuring the vibrations within at least one time window and determining an imbalance factor and an imbalance phase. The values of the parameters in the equation for calculating the correction action are then updated based on the imbalance factor and an imbalance phase. A correction angle for each of the wind turbine blades is calculated using these adjusted parameters. The correction angle is used to aerodynamically balance the rotor, and a model may be used to determine the initial values of the parameters. Another imbalance factor and imbalance phase is determined based on another set of measurements. This imbalance factor is then used to calculate a mass moment for correcting the mass imbalance in the wind turbine blades. The weight and location of a balancing mass is finally calculated based on this mass moment and installed in the respective wind turbine blades.

Abstract: An exhaust gas turbocharger for an internal combustion engine may include a rotor with a turbine wheel of a turbine, a compressor wheel of a compressor and a shaft. The shaft may be connected to the turbine wheel and to the compressor wheel in a rotationally fixed manner. A bearing cartridge may be included for mounting the rotor in a housing. The bearing cartridge may have an inner sleeve arranged on the shaft axially between the turbine wheel and the compressor wheel with respect to an axis of rotation and an outer sleeve arranged coaxial thereto. The outer sleeve may be rotatably mounted on the inner sleeve via at least one rolling body. At least two damping rings may be included which are coaxially arranged on the outer sleeve axially spaced from one another and supported on a respective bearing section of the housing.

Abstract: The present invention relates to a yaw system 5 for a windmill 1, the windmill comprising a tower 2 and a nacelle 3, the tower and the nacelle being joined by the yaw system and the yaw system further comprising a bearing fixed to the tower, on which bearing the nacelle rests and slides in a yawing movement, and at least one yaw motor arranged to allow the nacelle to perform a rotary motion along the bearing, wherein the yaw system 5 further comprises control means 8 for continuously operating the at least one yaw motor in such a way that the yaw motor strives to maneuver the nacelle according to a setpoint.

Abstract: The magnetic balance is verified of a magnetically-levitated impeller of a centrifugal pump with a pump housing having levitation magnets. The impeller includes embedded magnets and is movable within a chamber in the pump housing between first and second sides of the chamber. The centrifugal pump is mounted on an acceleration fixture while the impeller is held against a predetermined one of the first and second sides by the levitation magnets. A plurality of predetermined accelerations are applied to the acceleration fixture to exert a plurality of different forces of acceleration on the impeller. A determination is made whether the impeller detaches from the predetermined side as a result of each different force of acceleration to identify adjacent forces for which a transition occurs between detaching and not detaching. The transition is compared with a desired retention force to determine whether the pump achieves magnetic balance.

Abstract: A method of adjusting a rotary blade includes receiving performance data for a rotary blade, receiving an adjustment constraint for the rotary blade, defining an adjustment space for alternative adjustment solutions for the rotary blade including a plurality of alternative adjustment solutions, and calculating expected performance for one of the plurality of alternative adjustment solutions. Based on the expected performance of the one of the plurality of alternative adjustment solutions, the method determines whether to calculate expected performance for another of the plurality of alternative adjustment solutions.

Abstract: A method for predicting initial unbalance in a component comprising one or more elements, the method comprising: defining a statistical distribution of a mass moment weight of each of the one or more elements; restricting the statistical distribution to a selected range; and calculating an initial unbalance of the component for the restricted distribution of the one or more elements.

Abstract: The magnetic balance is verified of a magnetically-levitated impeller of a centrifugal pump with a pump housing having levitation magnets. The impeller includes embedded magnets and is movable within a chamber in the pump housing between first and second sides of the chamber. The centrifugal pump is mounted on an acceleration fixture while the impeller is held against a predetermined one of the first and second sides by the levitation magnets. A plurality of predetermined accelerations are applied to the acceleration fixture to exert a plurality of different forces of acceleration on the impeller. A determination is made whether the impeller detaches from the predetermined side as a result of each different force of acceleration to identify adjacent forces for which a transition occurs between detaching and not detaching. The transition is compared with a desired retention force to determine whether the pump achieves magnetic balance.

Abstract: A sunlight filter device for a helicopter blade tracker includes a filter housing, a filter assembly and a mounting system. The filter housing has a first opening, a second opening and a receiving cavity formed between the first opening and the second opening. The filter assembly is mounted in the receiving cavity of the filter housing, and is adapted to block sunlight. The mounting system extends from the filter housing to securely mount the filter housing on the helicopter blade tracker.

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: Methods and systems for determining a rebalancing strategy for trim balancing one or more rotational components of a gas turbine. One or more noise, acoustics or vibrational signals may be received at a control device of an aircraft comprising the gas turbine engine while the aircraft is in operation. The one or more noise, acoustics or vibrational signals may be used for determining a rebalancing strategy for one or more unbalanced rotational components.

Abstract: An exemplary clamp for clamping a bearing cartridge and shaft subassembly of a turbocharger includes an upper portion, a lower portion where the upper portion and the lower portion form a bore having a bore diameter sized to clamp a bearing cartridge and a fluid passage defined in part by the upper portion, the lower portion or the upper portion and the lower portion where the fluid passage includes an opening to the bore. Various other exemplary devices, systems, methods, etc., are also disclosed.

Abstract: A method of validating a wind turbine including a rotor includes intentionally inducing a loading imbalance to the rotor. The method also includes measuring the loading imbalance induced to the rotor, transmitting a signal representative of the measured loading imbalance to a calibration module, and at least one of detecting an error and calibrating at least one component of the wind turbine based on the signal.

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: Electrodymamic machine rotating mass, including for example induction motor rotors, stiffness tuning methods include selective orientation and compression of modular tie rod assemblies into through bores formed in the rotor lamination core outboard of the rotor shaft during motor manufacture, repair or refurbishment. Stiffness tuning enables a motor manufacturer to tune a rotor's rotordynamic stability, and hence the assembled motor's critical vibration speed. Electrodynamic machine rotating mass tuning can be adjusted in response to machine physical design, operational application and manufacturing variation attributes that impact the assembled machine's critical vibration frequency. Thus the present invention offers a systematic, holistic approach to motor vibration refinement through use of a simple kit of modular tie rod assemblies oriented and tightened in a selected array. Rotor stiffness tuning can be tested virtually on computer work stations.

Abstract: The invention discloses a novel method and apparatus to determine the degree of residual mass unbalance and a corrective balance solution for a rotating assembly having a non-vertical axis of rotation. When the center of mass of the rotating assembly is not concentric with the axis of rotation, the condition of unbalance exists. When the rotating assembly is driven by a motor or drives a generator, fluctuations in power are produced proportional to the degree of unbalance. The method and apparatus to determine the degree of mass imbalance consists of measuring the average instantaneous real power over an interval of time, calculating the Fourier Transform of the demodulated signal, establishing the peak amplitude and phase associated with the angular velocity of the rotating assembly and calculating the amount of unbalance.

Abstract: A wind of the type having a tower and a nacelle with a rotor rotatably connected to the nacelle for rotating about a rotor axis and having a plurality of equally spaced blades has the rotor balanced by firstly taking a measurement of torsional vibration and then by using photographic techniques to analyze dynamic imbalance caused by differences in the angle of attack of the blades. The torsional vibration is detected using two sensors at positions mirrored exactly in distance to the left and right of the rotor axis and detecting vibration in the axial direction. The angle of attack is measured by analyzing images of the tip of the blade where, during the analysis, distortion in angles at different locations in the image are corrected, in dependence upon a prior analysis of an image taken by the camera relative to a known image.

Abstract: It is described a method for balancing a rotor mounted on a hub of a wind turbine. The method includes measuring a parameter value of a parameter being indicative of the revolution frequency components of the rotor and/or of a generator of the wind turbine during operation of the wind turbine, calculating a change of the spatial mass distribution of the rotor based on the parameter value of the parameter, which change is needed for balancing the rotor, and balancing the spatial mass distribution of the rotor by using at least one balancing weight element being attachable to at least one blade of the rotor based on the calculated change of the spatial mass distribution. It is further described a system for balancing a rotor, a wind turbine, a computer program and a computer-readable medium, which are all adapted for carrying out the above described balancing method.

Abstract: In one aspect, a method for the determination of a nacelle-inclination is provided. A first difference-signal is formed from the difference of a measured nacelle acceleration and an offset-value from a calibration. A second difference-signal is formed from a difference of the first difference-signal and a feedback signal. A first sum-signal is formed from adding an integrated second difference-signal with the product of the second difference signal and a factor. A second sum signal is formed from adding an integrated first sum-signal with the product of the first-sum-signal and the factor. A corrected signal is formed by a product of the second sum-signal and an equivalent tower height. A first nacelle-signal is formed by the arc-tangent of the corrected signal. A nacelle inclination is obtained from filtering the first nacelle-signal by a low-pass-filter. The feedback-signal is formed by multiplying the acceleration of gravity with the sine of the first nacelle-signal.

Abstract: A method for detecting an unusual operational condition of a wind turbine is provided. The method includes measuring an actual imbalance of a rotor of said wind turbine, determining an imbalance deviation of the measured actual imbalance from an imbalance reference, and evaluating whether the imbalance deviation is above a predetermined imbalance threshold value.

Abstract: A method for predicting initial unbalance in a component comprising one or more elements, the method comprising: defining a statistical distribution of a mass moment weight of each of the one or more elements; restricting the statistical distribution to a selected range; and calculating an initial unbalance of the component for the restricted distribution of the one or more elements.

Abstract: A rotation is corrected by rotationally driving a supercharger rotor (a turbine impeller (2), a compressor impeller (6) and a shaft (12)) by an electric motor (18) in a state of detaching a turbine housing (4) and a compressor housing (8), and detecting data necessary for correcting the rotation inbalance of a motor-driven supercharger (10). Further, the electric motor (18) is driven by using a dedicated motor driver (27) supplying a larger electric power than a power supply of an acceleration assisting motor driver.

Abstract: A method for determining an imbalance of a propeller shaft assembly can include establishing balancing planes relative to certain areas of the propeller shaft assembly and identifying each component of the propeller shaft assembly that could have a potential imbalance condition due to a tolerance variation. The method can also include determining the potential imbalance condition for each identified component, and determining a contribution of each determined potential imbalance condition to a respective pair of the established balancing planes. The method can further include determining a total magnitude of imbalance at the respective pair of established balancing planes based on the determined contributions of each potential imbalance condition, and determining a statistically representative value of the determined magnitude of imbalance.

Abstract: Described are techniques for selecting options used with current sensor data characterizing vibration caused by rotating blades. Sets of other sensor data are evaluated to determine a first of the sets of other sensor data that is a best match for said current sensor data. Each of the sets of other sensor data is associated with one of a plurality of option sets. Each option set includes options used in determining one or more adjustments that may be applied to the blades to reduce vibration. The one or more sets of other sensor data are evaluated to determine a first of the sets of other sensor data that is a best match for said current sensor data. A first of the plurality of option sets associated with said first set of sensor data is used in determining adjustment(s) that may be applied to the blades.

Abstract: The invention discloses a novel method and apparatus to determine the degree of residual mass unbalance and a corrective balance solution for a rotating assembly having a non-vertical axis of rotation. When the center of mass of the rotating assembly is not concentric with the axis of rotation, the condition of unbalance exists. When the rotating assembly is driven by a motor or drives a generator, fluctuations in power are produced proportional to the degree of unbalance. The method and apparatus to determine the degree of mass imbalance consists of measuring the average instantaneous real power over an interval of time, calculating the Fourier Transform of the demodulated signal, establishing the peak amplitude and phase associated with the angular velocity of the rotating assembly and calculating the amount of unbalance.

Abstract: A method for determining an imbalance of a propeller shaft assembly can include establishing balancing planes relative to certain areas of the propeller shaft assembly and identifying each component of the propeller shaft assembly that could have a potential imbalance condition due to a tolerance variation. The method can also include determining the potential imbalance condition for each identified component, and determining a contribution of each determined potential imbalance condition to a respective pair of the established balancing planes. The method can further include determining a total magnitude of imbalance at the respective pair of established balancing planes based on the determined contributions of each potential imbalance condition, and determining a statistically representative value of the determined magnitude of imbalance.

Abstract: A system and method can be utilized to determine an out of balance condition of a rotor having a plurality of blades. The system monitors a clearance between the blades and an associated housing. By looking at a center of that clearance information, a determination can be made of the magnitude of imbalance of the rotor.

Abstract: Apparatus for measuring rotational imbalance of a turbocharger core assembly, comprising a base frame (30) having a housing (31) in the form of an exhaust duct. Attached by leaf springs (33) to the housing (31) is a support part (35) and a co-axial adaptor (36) to which a turbocharger core assembly (38) is removably attached by quick-release clamps (37). An air inlet (40) receives air to drive the turbocharger core assembly via a volute within the adaptor (36), and any imbalance of the turbocharger core assembly, causing oscillatory vibration via the leaf springs (33) is measured by an accelerometer (40) mounted on the support part (35).

Abstract: A system and method can be utilized to determine an out of balance condition of a rotor having a plurality of blades. The system monitors a clearance between the blades and an associated housing. By looking at a center of that clearance information, a determination can be made of the magnitude of imbalance of the rotor.

Abstract: The invention discloses an improved method and apparatus to statically equalize the span wise and chord wise moments of a detached plurality of radial projections. These detached radial projections are associated with a rotating assembly and constitute the majority of its rotating mass. When installed on the rotating assembly, the balanced radial projections will necessarily produce a center of rotating mass approximately concentric with its axis of rotation, thereby minimizing vibrations associated with its rotation. The method to statically equalize the span wise moments of the radial projections comprises first determining the span wise moment by finding the center of gravity and multiplying the distance from the center of gravity to the plane of attachment of the radial projection to the rotating assembly by its total weight.

Abstract: One embodiment of a propeller tuner assembly formed in accordance with the present disclosure includes a frame and a bearing assembly having a coupler adapted to selectively couple a propeller to the frame. The coupler is selectively movable from a first position where at least a portion of the coupler is substantially isolated from tuning loads applied to the bearing assembly.

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 particle filling line comprises a vertically-oriented conduit that includes a conduit hollow. The conduit includes a conduit top and a conduit bottom. The conduit bottom defines an outlet. The conduit is arranged so that particles supplied to the conduit top flow through the outlet to be received by one or more containers disposed on a movable conveyor belt. The conduit hollow includes one or more conduit hollow elements disposed therein. The one or more conduit hollow elements include any of a plurality of agitators and an auger. The particle filling line is arranged for determining a resistance that is based on the spacing between the one or more conduit hollow elements and the conduit inner walls. When the resistance is determined to be less than a threshold resistance value, the particle filling process ceases.

Abstract: A rotatably supporting device for correcting balance of a rotating body includes a journal supporting part having a mandrel that rotatably supports the rotating body in a floating state about a vertical axis, a thrust supporting part that is provided at a lower end portion of the mandrel and supports a bottom part of the rotating body in the floating state, a first fluid supply passage that supplies a fluid for floating between the mandrel and a rotation support hole of the rotating body, an annular groove provided in the thrust supporting part so as to face the bottom part of the rotating body, and a second fluid supply passage that communicates with the annular groove to supply a fluid thereto for floating the rotating body.

Abstract: A system for balancing an aircraft propeller system receives a vibration signal from the aircraft propeller system and determines whether the vibration signal indicates a transient vibration condition. If it is determined that the vibration signal does not indicate a transient condition, the system enables a balance correction controller. The controller generates a balance correction signal based on the vibration signal, and balances the aircraft propeller system in response to the balance correction signal if the balance correction controller is enabled.

Abstract: A method and system of determining an imbalance of a wind turbine is provided.

Abstract: One embodiment of a propeller tuner assembly (10) formed in accordance with the present disclosure includes a frame (12) and a bearing assembly (64) having a coupler (90) adapted to selectively couple a propeller (20) to the frame (12). The coupler (90) is selectively movable from a first position where at least a portion of the coupler (90) is substantially isolated from tuning loads applied to the bearing assembly (64).

Abstract: One embodiment of a propeller tuner assembly formed in accordance with the present disclosure includes a frame and a bearing assembly having a coupler adapted to selectively couple a propeller to the frame. The coupler is selectively movable from a first position where at least a portion of the coupler is substantially isolated from tuning loads applied to the bearing assembly.

Abstract: A particle filling line comprises a vertically-oriented conduit that includes a conduit hollow. The conduit includes a conduit top and a conduit bottom. The conduit bottom defines an outlet. The conduit is arranged so that particles supplied to the conduit top flow through the outlet to be received by one or more containers disposed on a movable conveyor belt. The conduit hollow includes one or more conduit hollow elements disposed therein. The one or more conduit hollow elements include any of a plurality of agitators and an auger. The particle filling line is arranged for determining a resistance that is based on the spacing between the one or more conduit hollow elements and the conduit inner walls. When the resistance is determined to be less than a threshold resistance value, the particle filling process ceases.

Abstract: A system and method can be utilized to determine an out of balance condition of a rotor having a plurality of blades. The system monitors a clearance between the blades and an associated housing. By looking at a center of that clearance information, a determination can be made of the magnitude of imbalance of the rotor.

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: Disclosed is a method of reducing a structural unbalance in a wind turbine rotor with pitch control and a control device for performing the method are provided. The method comprises the steps of: detecting a magnitude of the structural unbalance and its phase in relation the rotor's azimuth (?) on the basis of a measurement of the rotor's azimuth (?) and a measurement of the rotor speed or the generator speed (?), establishing individual pitch angle offsets for each blade of the rotor on the basis of the magnitude and the phase, and adding the individual pitch angle offsets to the respective pitch angles of the blades of the rotor.

Abstract: An exemplary method for balancing a rotating assembly of a turbocharger, where the rotating assembly includes a shaft rotatably supported by a bearing cartridge, includes loading the rotating assembly to introduce a tilt between the rotational axis of an inner race of the bearing cartridge and a bore axis of an outer race of the bearing cartridge, rotating the inner race with respect to the outer race at a rotational speed less than approximately 5,000 rpm while maintaining the tilt at substantially constant angle and measuring dynamic unbalance of the rotating assembly. Various other exemplary devices, systems, methods, etc., are also disclosed.

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 of balancing a rotor (10), the said method comprising the steps of determining the position of the center of mass of a rotor (10) to be balanced prior to the rotor (10) being machined to its final dimensions, and machining the rotor (10) to its final dimensions by removing material substantially along the length of the rotor (10). The material is removed in the direction of its axis such that the center of mass of the rotor is adjusted to be substantially co-incident with its axis of rotation (22).

Abstract: The present invention provides a system and method for using the external accelerometer in an aircraft engine configuration as a backup accelerometer, in the event the internally located production accelerometer fails. The sensor location of the external accelerometer has an acceptable sensitivity to fan imbalance, similar to the location of the former alternate accelerometer. The signal from this external accelerometer is duplicated using software in the signal conditioning hardware, creating the second, alternate signal. As an alternative embodiment, the signal may be duplicated by simply teeing or branching the original signal, using hardware rather than software.

Abstract: A helicopter blade tracking system including an apparatus and method having a self-contained light unit on each blade; each light unit being of similar construction and matched in size and weight. Rings of light formed by the light units during blade rotation are observed by the operator during hover and blade angular position is changed to bring the rings of light into one multi-colored ring of light.