1607 results about "Turbine rotor" patented technology

An aircraft engine (10) has: a turbine (15) including a turbine rotor (15C) rotatable about a central axis (A); a scroll case (20) having an inlet (22) fluidly connected to a source of combustion gases and an outlet (23) fluidly connected to the turbine (15), and a conduit (21) extending around the central axis (A) from the inlet (22) to the outlet (23), the conduit (21) spiraling towards the central axis (A); a bearing housing (30) extending around the central axis (A); an exhaust case (15B) disposed downstream of the turbine (15); and a turbine support case (40) secured to the bearing housing (30; 130) and to the exhaust case (15B), the turbine support case (40) having spokes (44) distributed around the central axis (A) and extending along a direction having an axial component relative to the central axis (A), the spokes (44) extending through the conduit (21) of the scroll case (20) and radially supported by the bearing housing (30).

An aircraft engine, has: a turbine including a turbine rotor rotatable about a central axis; a scroll case having an inlet fluidly connected to a source of combustion gases and an outlet fluidly connected to the turbine, and a conduit extending around the central axis from the inlet to the outlet, the conduit spiraling towards the central axis; a bearing housing extending around the central axis; an exhaust case disposed downstream of the turbine; and a turbine support case secured to the bearing housing and to the exhaust case, the turbine support case having spokes distributed around the central axis and extending along a direction having an axial component relative to the central axis, the spokes extending through the conduit of the scroll case and radially supported by the bearing housing.

The invention discloses a hoisting tool for a steam turbine rotor, and belongs to the technical field of hoisting equipment, the hoisting tool for the steam turbine rotor comprises a cross beam and two groups of hoisting frames, the two groups of hoisting frames are symmetrically arranged on two sides of the cross beam, the hoisting frames are slidably connected to the cross beam, and hoisting parts are connected below the hoisting frames. Longitudinal beams are symmetrically and fixedly connected to the two ends of the cross beam, adjusting components are slidably connected to the tops of the longitudinal beams, auxiliary mooring ropes are hung at the bottoms of the longitudinal beams, and traction ropes are arranged at the tops of the longitudinal beams. The lifting belt is used for lifting the steam turbine rotor, compared with cable lifting, the lifting belt is more stable, stress of the lifting belt can be adjusted, accidents caused by uneven stress are avoided, meanwhile, the cable is assisted to lift the steam turbine rotor together, it is guaranteed that the steam turbine rotor is stably lifted, the steam turbine rotor is prevented from falling off when the lifting belt breaks down, and serious accidents are avoided.

A controller for a wind turbine having three rotor blades is provided for controlling activation of individual pitch control of the rotor blades. The controller is configured to receive a flapping load signal from the flapping load sensor of each of the three rotor blades, the flapping load signal indicating a flapping load on each of the respective rotor blades. The controller is configured to determine a statistical discrete parameter of the flapping load of each rotor blade based on the received flapping load signal, the statistical discrete parameter being indicative of a wind event in a wind farm in which the wind turbine operates. The controller is configured to control activation of the individual pitch control based on the respective statistical discrete parameters.

The invention discloses a creep test system of a turbine rotor blade film hole simulation piece and a test method of the creep test system. Comprising a clamping assembly used for fixing a test piece, a loading assembly used for applying a load to the test piece, a strain measuring assembly used for measuring the strain rate of the test piece, a heating assembly used for covering the test piece to form a heating channel, and a cooling assembly used for manufacturing and conveying cooling airflow to flow through the interior of the test piece, the strain measurement assembly is used for measuring the external temperature of the test piece and the internal temperature of the test piece, the control assembly is connected with the strain measurement assembly, the heating assembly, the cooling assembly and the temperature measurement assembly, and the heating assembly is used for manufacturing and conveying high-temperature airflow to flow through the heating channel so as to heat the outside of the test piece to a first set temperature; the cooling assembly is used for cooling the interior of the test piece to a second set temperature, and the heating assembly and the cooling assembly are used for forming a dynamic convection environment around the test piece.

An assembly is provided for an aircraft powerplant. This assembly includes a differential geartrain, a first rotating assembly, a second rotating assembly, a first actuator and a second actuator. The differential geartrain includes a sun gear, a ring gear, a plurality of intermediate gears and a carrier. The first rotating assembly is coupled to the differential geartrain through the carrier. The first rotating assembly includes a first turbine rotor. The second rotating assembly is coupled to the differential geartrain through the ring gear. The second rotating assembly includes a second turbine rotor. The first actuator is coupled to the differential geartrain through the ring gear. The second actuator is coupled to the differential geartrain through the sun gear.

The invention discloses a balance correction method of a wind driven generator rotor, relates to the technical field of balance correction of wind driven generator rotors, and aims to solve the problem of dynamic imbalance caused by blade mass distribution difference. A traditional static correction method cannot meet the real-time adjustment requirement of a large-size turbine, and the real-time adjustment requirement of the large-size turbine is met by collecting spindle vibration, blade root strain and pitch angle signals, constructing a real-time rotational inertia vector, calculating mass inertia change and a pneumatic cycle lag index and inputting a graph neural network to determine an unbalance coefficient and type. Generating a correction instruction for movable counterweight and pitch adjustment; the correction process is synchronously executed under rated conditions, and coordination of mechanical compensation and pneumatic compensation is ensured. After correction, the evaluation effect is compared through a vibration vector, and the result is stored in a self-adaptive database to optimize subsequent circulation; low-load operation can be maintained, the maintenance cost is reduced, and the service life of key parts is prolonged.

The invention relates to the technical field of wind driven generator driving control, and discloses a wind driven generator rotor turning-over driving control method based on torque and rotating speed cooperation, which comprises the following steps: before operation, controlling a motor to execute forward and reverse quasi-static micro-motion, and collecting an average electromagnetic torque; pure gravity and friction components are separated by using torque arithmetic sum and difference, gravity model gain is corrected, and friction compensation is configured; a feed-forward torque is calculated in combination with a real-time angle, and friction compensation and speed loop feedback are superposed to generate a current instruction; according to the method, gravity and friction are decoupled through physical symmetry, model parameter errors are eliminated, hidden dangers of integral lag and out-of-control rotating speed when the variable polarity load passes through a dead point are avoided, and stability and safety of the turnover process of the hundred-ton rotor are ensured.

The invention relates to the technical field of turbine rotor balance debugging, in particular to a balancing machine special for a turbine rotor and a balance debugging method. Comprising a vacuum chamber, the vacuum chamber and the platform form a sealed space, a vacuum adjusting device connected with a processing and control unit is installed in the vacuum chamber, and a motor, a drilling weight removing device, a vibration detecting device and a clamp are all arranged in the vacuum chamber; the vacuum adjusting device comprises a sensor and a vacuum pump, and the vacuum pump is communicated with the vacuum chamber through a pipeline; and the sensor and the vacuum pump are respectively connected with the processing and control unit. The vacuum degree in the vacuum chamber can be adjusted by arranging the vacuum pump and the sensor, balance debugging can be carried out under high rotating speed and high vacuum and low rotating speed and low vacuum, and the balance debugging is not influenced by airflow when the balance debugging is carried out under the high rotating speed.

The invention belongs to the technical field of aero-engine high-temperature part test, and particularly relates to a thermal mechanical composite fatigue test device in a turbine blade rotation environment, which comprises a high-temperature gas system, a stator system, a rotor system, a support system, a test system, an auxiliary system and a turbine rotor blade test piece, the high-temperature fuel gas system is used for providing a fuel gas environment for a turbine rotor blade test piece and controlling the high-low temperature circulation state of fuel gas, a combustion chamber is arranged at the front end of the high-temperature fuel gas system and provided with a double-oil-way nozzle, a fuel gas flowing system is arranged at the rear end of the high-temperature fuel gas system, and a blade grid structure is designed for the fuel gas flowing system according to the geometrical shape of a turbine rotor blade. And a spray cooling section is arranged at the rear part of the test section. The device is composed of six core systems including a high-temperature fuel gas system, a stator system, a rotor system, a supporting system, a testing system and an auxiliary system, all the systems work cooperatively, and integrated simulation of the high-temperature fuel gas environment, rotating centrifugal loads and heat-force synchronous circulation is achieved.

The invention relates to the technical field of steam turbines, in particular to a turbine moving blade capable of strongly turning along the flow direction, a blade body part of the turbine moving blade is formed by twisting and overlapping a plurality of two-dimensional blade profiles according to a certain rule, and the blade body part has a characteristic parameter blade body height H; the contour molded line of the two-dimensional blade profile is defined by an inner arc curve and a back arc curve and has a characteristic parameter flow direction turning angle theta and the height h in the height H direction of the blade body; according to the overlapping rule of the two-dimensional blade profile, continuous and smooth transition is conducted from the root end to the top end along the blade body height H, the relative value of the blade body height H is monotonically increased to 1.0 from 0.0, and correspondingly, the absolute value of the flow direction turning angle theta is monotonically decreased to 75 degrees from 135 degrees; and in the whole blade body height H range of the blade body part, the average flow direction turning angle is 100-105 degrees. Flow direction turning angle changes of two-dimensional blade profiles with different heights are controlled, so that flow field distribution is optimized, the efficiency of a turbine stage is improved, and loss and strength are distributed along the height of a blade body in a self-adaptive mode.

The invention describes a testing apparatus (1) for use in a wind turbine rotor blade manufacturing facility, comprising a pulling means (10) adapted to pull an adherent strip (3T) from a surface of a rotor blade (2); a positioning arrangement (11) configured to maintain a predetermined pull angle (x) between the adherent strip (3T) and the surface of the rotor blade (2) during a test procedure; and a support frame (12) for holding the pulling means (10) and positioning arrangement (11), which support frame comprises a clamping arrangement (14) adapted to clamp about the leading edge (2LE) of the rotor blade (2). The invention further describes a method of performing a test procedure on a wind turbine rotor blade (2) using the inventive testing apparatus (1).

The invention discloses an aero-engine turbine rotor robot assembly point cloud feature recognition method and system, and the method comprises the steps: calculating a rotation matrix of a point cloud according to the coordinate pose of the tail end of a robot and the hand-eye relation of the robot; extracting a first point cloud in a height range where the point cloud features are located, and solving normal vector information of the processed first point cloud; according to the solved normal vector information, establishing a boundary point judgment model and judging whether the to-be-monitored point is a boundary point to obtain an extracted second point cloud; performing three-dimensional circle model fitting on the second point cloud in combination with normal vector information, extracting fitted inner points, and gradually extracting a plurality of three-dimensional circle structures in the point cloud; and fitting the three-dimensional circle to obtain circle center, radius and axis information of a large circle with small circular holes, and obtaining an aero-engine turbine rotor robot assembly point cloud feature image. According to the method disclosed by the invention, accurate matching and attitude adjustment of the parts are realized by utilizing the high-resolution characteristic of the point cloud data, and the assembly precision is greatly improved.

A hybrid-electric aircraft propulsion system includes a gas turbine engine and an electrical assembly. The gas turbine engine includes a first rotational assembly. The first rotational assembly is rotatable about a rotational axis of the gas turbine engine. The first rotational assembly includes a first shaft, a bladed first compressor rotor, and a bladed first turbine rotor. The first shaft interconnects the bladed first compressor rotor and the bladed first turbine rotor. The electrical assembly includes a first motor-generator, a first motor control unit, a motor-generator (MG) cooling system, and a motor control unit (MCU) cooling system. The first motor-generator is coupled to the first shaft. The first motor control unit is electrically connected to the first motor-generator. The MG cooling system is connected in fluid communication with the first motor-generator. The MCU cooling system is connected in fluid communication with the first motor control unit. The MCU cooling system is independent of the MG cooling system.

Disclosed in the present invention are a control method and system capable of providing frequency support for a flexible interconnected power distribution network. The method comprises: using a permanent-magnet direct-drive wind turbine connected to a flexible interconnected power distribution network to provide frequency support, measuring a direct-current voltage of a grid-side converter of the wind turbine, calculating a per-unit value and the phase of the direct-current voltage, and calculating the amplitude of a modulation voltage; generating a trigger pulse signal; monitoring the rotation speed of a wind turbine rotor and the rotor position angle of a synchronous generator, and acquiring a per-unit value of optimal power; calculating an active power reference value; on the basis of active power control and current control, outputting a d-axis component and a q-axis component of a modulation voltage of a generator-side converter, and by means of rotating coordinate transformation, generating a three-phase modulation voltage in a stationary coordinate system; and generating a trigger pulse signal by means of a pulse width modulation stage. The present invention enables wind turbines to provide quick response for power distribution networks in a frequency support stage, and prevent rotation speed stalling and suppress secondary frequency drop in a rotation speed recovery stage, thereby improving the support capability of the wind turbines for power grids.

The invention relates to the technical field of machine vision and wind power detection, and discloses a surface defect identification method and system for a rotor core of a wind driven generator, and the method comprises the steps: collecting an original image of the surface of the rotor core, and carrying out the gray mapping, and obtaining a single-channel gray image; carrying out frequency domain periodic texture suppression and local histogram equalization processing with contrast limitation on the single-channel grayscale image to obtain an enhanced feature image; constructing a background fitting model for the enhanced feature image and performing differential operation to obtain a background differential image; performing adaptive segmentation and morphological refining based on a texture direction according to the background difference image to obtain a refined defect connected domain; local gray level distribution is extracted, sub-pixel-level geometric feature calculation is carried out, and defect geometric attribute data are obtained; and spatial clustering and grading evaluation are carried out according to the data, and a final defect distribution map is determined. According to the method, periodic texture interference can be effectively suppressed, and sub-pixel-level precise positioning and intelligent grading of the tiny defects are realized.

A turbine moving blade according to at least one embodiment of the present disclosure includes: a second cooling flow path; and a first cooling flow path that extends in the blade height direction, is formed on the leading edge side relative to the second cooling flow path, and is connected to the second cooling flow path at a first folded section on the base end side of an airfoil section. The first folded section includes an upstream-side region extending along the extension direction of the first folded section, from the inlet section at a position in the same blade height direction as the base end of the airfoil section to the central position in the wall thickness direction of the first partition wall when viewed from the blade height direction. The upstream-side region has, in at least a part of the blade height direction, a region in which an inner wall surface of a back-side blade wall and a partition wall surface on a leading edge side of a second partition wall is connected by a curved surface that protrudes outward from the inside of the airfoil section when viewed from the blade height direction, the region having a radius of curvature of the curved surface that increases from the tip end side toward the base end side of the airfoil section.

The present invention discloses a static calibration device and method for a thin film strain gauge deposited in situ on the surface of an aircraft engine turbine rotor blade. The present invention belongs to the field of high temperature strain testing technology. It is used to calibrate a thin film strain gauge deposited in situ on the surface of a rotating component in a high temperature zone such as an aircraft engine turbine rotor blade. The calibration device consists of a resistance wire heater, a turbine engine rotor, a thin film strain gauge deposited in situ on the surface of a turbine engine rotor blade, a thin film thermocouple, and a capacitive distance sensor. The strain of the thin film strain gauge is introduced by the centrifugal force caused by high-speed rotation, and the strain size is calibrated by a capacitive distance sensor; by calibrating the strain sensitivity coefficient of the thin film strain gauge at different temperatures, the decoupling of temperature and strain is achieved. The present invention provides an effective experimental platform and method for the calibration of thin film strain gauges deposited in situ on the surface of rotating components in a high temperature zone of an aircraft engine.

The disclosure relates to monitoring blades of a wind turbine rotor shaft. Example embodiments include a computer-implemented method of monitoring blades of a wind5 turbine (100), the wind turbine (100) having a plurality of blades (103a, 103b) mounted to a hub (102), each blade (103a) comprising one or more strain sensors (109a1-3) mounted to the blade (103a) at corresponding respective distances from the hub (102, 201) along the blade (103a), the method comprising: i) recording (1301) strain measurements from the strain sensors (109a1-3) on each of the plurality of blades10 (103a); ii) recording (1302) a rotor speed of the wind turbine (100); iii) calculating (1303) a statistical measure of each of the recorded strain measurements; iv) calculating (1304) a difference in the statistical measure for strain sensors at corresponding positions on each of the plurality of blades over a range of rotor speeds; and v) identifying (1305) the presence or absence of damage in one of the plurality of blades15 based on the calculated difference.

A gas turbine engine includes a compressor section. A combustor is configured to receive compressed air from the compressor section. A turbine section is positioned downstream of the combustor and configured to receive an exhaust flow from the combustor. The turbine section includes a turbine rotor configured to drive a compressor rotor. An open pusher rotor system is mounted downstream of the turbine section, and driven by a propulsor turbine rotor in the turbine section. An exhaust duct is downstream of the propulsor turbine rotor. The exhaust duct extends to an exhaust exit such that a flow path of the exhaust flow leaving the exhaust exit is directed away from the open pusher rotor system. A propulsion system is also disclosed.

The invention discloses a turbine disc baffle structure optimization method and device, equipment, a medium and a product and relates to the field of turbine rotors, and the method comprises the steps that actual structure information of a turbine disc-baffle rotor system is obtained; performing finite element modeling on the actual structure information to obtain a finite element model; transient thermal analysis and transient stress analysis are sequentially carried out according to the finite element model, and the most dangerous time step where the maximum equivalent stress and the maximum contact stress are located is obtained; establishing a response surface model based on a Kriging model according to the most dangerous time step where the maximum equivalent stress and the maximum contact stress are located and actual structure information; according to the response surface model, a multi-target genetic algorithm is used for optimization, and optimized turbine disc baffle structure information is obtained. Stress concentration is effectively reduced, and the fatigue life is prolonged.

A system is provided for an aircraft. This aircraft system includes a propulsor rotor and a powerplant configured to drive rotation of the propulsor rotor. The powerplant includes a turbine section, a flowpath, a first fuel system and a second fuel system fluidly independent of the first fuel system. The turbine section includes a turbine rotor. The flowpath extends through the turbine section from an inlet into the flowpath to an exhaust from the flowpath. The first fuel system is configured to direct first fuel into the flowpath between the inlet and the turbine rotor. The second fuel system is configured to direct second fuel into the flowpath between the inlet and the turbine rotor.

The invention relates to the technical field of aero-engine turbine rotor blade fatigue life design, in particular to a multistage turbine rotor blade fatigue life analysis method and device. The method comprises the following steps: based on material fatigue performance data of turbine rotor blades and a three-dimensional finite element model of the turbine rotor blades, obtaining a target test temperature and a target test rotating speed of a multi-stage turbine rotor blade group in a low-cycle fatigue test and a stress coefficient of each assessment part of each stage of turbine rotor blades; and obtaining an actual fatigue test cycle number analysis result of each stage of turbine rotor blade based on the target test temperature and the target test rotating speed of the low cycle fatigue test of the multi-stage turbine rotor blade group and the stress coefficient of each assessment part of each stage of turbine rotor blade. According to the method, the function of carrying out fatigue life test on multiple groups of turbine rotor blades is realized, the test efficiency is effectively improved, the test period is shortened, and the economic cost is reduced.

The embodiment of the invention provides a rotor fatigue loss online detection method and device based on a full convolutional neural network. The method comprises the following steps: constructing a turbine rotor geometric model; determining a temperature monitoring point in the rotor geometric model through a finite element analysis tool; performing stress prediction according to the temperature parameters of the temperature monitoring points through a pre-constructed rotor stress field reconstruction model, and generating a rotor equivalent stress; the method comprises the following steps: generating rotor fatigue loss according to rotor equivalent stress through a pre-constructed online calculation model of the fatigue loss of the steam turbine rotor, and directly predicting stress distribution of the rotor according to temperature results of a small number of measuring points in a peak shaving process of the rotor through a rotor stress field reconstruction model of a deep full convolutional neural network. According to the method, high-precision and high-efficiency stress prediction can be provided for the steam turbine under different peak regulation working conditions, so that the fatigue loss of the rotor is accurately detected in real time, and safe operation of the steam turbine is guaranteed.

A structure for assembling turbine blade seals, which includes a turbine blade including an airfoil, a platform, and a root, a turbine rotor disk to which the root of the turbine blade is mounted, a seal plate mounted between the platform and one side of the turbine rotor disk to seal a cooling channel defined within the root and the platform, and an insertion pin inserted through the turbine rotor disk to fix the seal plate to the turbine rotor disk by supporting the seal plate, wherein the turbine rotor disk has a mounting groove into which a radially inner end of the seal plate is inserted, and the seal plate has a jaw portion radially supported by a stepped portion of the mounting groove.

A propulsion system for an aircraft includes an engine assembly and a turbocompressor. The engine assembly includes an engine and an interburner. The engine includes an engine output shaft. The engine is configured to drive rotation of a propulsor with the engine output shaft. The interburner is configured to mix and burn an exhaust gas from the engine with fuel to form a combustion gas. The turbocompressor includes a turbine and a compressor. The turbine and the compressor form a rotational assembly. The rotational assembly includes a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor. The turbine is connected in fluid communication with the interburner to receive the combustion gas. The compressor is connected in fluid communication with the engine to direct a compressed air to the engine. The rotational assembly is mechanically independent of the engine output shaft.

The invention belongs to the technical field of aero-engines, and provides a turbine rotor blade tenon flow guiding device which comprises a blade tenon and a high-pressure backflow cavity communicated with the blade tenon, a plurality of channels are formed in one plane of the blade tenon and communicated with the high-pressure backflow cavity, a flow guiding table is arranged on one plane of the blade tenon, and a flow guiding groove is formed in the other plane of the blade tenon and communicated with the high-pressure backflow cavity. The flow guide table is close to the corresponding channel, an air inlet face and a flow guide face are arranged on the two adjacent side faces of the flow guide table respectively, the air inlet face is close to the air inlet of the blade tenon, and the flow guide face is located above the corresponding channel. Resistance and vortex can be reduced through the flow guide tables, so that the cold air flow of the corresponding channels is increased, the cold air flow of the corresponding channels flowing into the high-pressure backflow cavity is increased, the flow speed is increased, and the front ends of the blades are prevented from being violently impacted. A large vortex system is formed at the position of the channel far away from the flow guide table, so that the flow speed of cold air at the inlet of the channel is reduced, reasonable distribution of airflow in each channel is achieved, and the problem that the performance of an engine is affected due to excessive cold air consumption is avoided.

The invention discloses a wide-adaptability variable-geometry turbine of a variable-cycle aero-engine and a flow adjusting structure of the wide-adaptability variable-geometry turbine of the variable-cycle aero-engine, a turbine guider in the structure is integrally arranged at the upstream position of a turbine rotor and is provided with a plurality of guider blades, each blade is provided with a front cavity and a rear cavity, the cavities are connected with the last stage of an air compressor through an air entraining connector, and the air entraining connector is connected with the tail stage of the air compressor. And high-pressure airflow is guided in. The suction face front airflow nozzle and the pressure face tail airflow nozzle are used for jetting airflow to the main flow channel, the pneumatic blocking effect with the local flow speed reduced is formed, and the throat area and the airflow angle characteristic of the guider are adjusted. The airflow adjusting device comprises a flow adjusting valve and a pressure adjusting valve, the flow and pressure of airflow are controlled, the airflow injection characteristic is accurately adjusted, and the turbine flow and efficiency are optimized. The turbine flow adjusting precision can be effectively improved, the mechanical complexity is reduced, the turbine efficiency is improved, the service life of an engine is prolonged, the requirements under different flight working conditions are met, and the important application value is achieved.

To provide an axial flow turbine which can be improved in the overall efficiency.SOLUTION: An axial flow turbine includes: a turbine shaft; a turbine rotor blade row; and a turbine housing having an exhaust chamber on a downstream side of the turbine rotor blade row. The turbine housing includes a flow guide portion having an inner peripheral-side wall surface forming a diffuser flow path for guiding the working fluid that has passed through the turbine rotor blade row to the gap from an inner wall of the exhaust chamber in a radially outward side. When a minimum distance between a rear edge end and a negative pressure surface of the other adjacent turbine rotor blade is denoted as throat s, a pitch of the plurality of turbine rotor blade is denoted as t, a blade height position at a blade root is 0%, and the blade height position at the blade tip end is 100%, a distribution of throat / pitch ratio in a blade height direction having a throat / pitch ratio at the 25% blade height position is smaller than a line segment between the blade root portion and a center portion in the blade height direction, and a throat / pitch ratio at the 75% blade height position is smaller than a line segment between the center portion and the blade distal end portion.SELECTED DRAWING: Figure 3

The invention provides for controlling a wind turbine comprising pitch-adjustable rotor blades. The invention involves determining, based on detected wind conditions, wind turbine control parameters for controlling the wind turbine in accordance with a defined wind turbine control strategy, where the control parameters include a reference pitch angle for the rotor blades. The invention involves obtaining bearing control parameters each indicative of a parameter for controlling pitch bearings of the wind turbine that is for adjusting pitch of the rotor blades. The invention involves determining whether a defined set of operational parameters of the wind turbine, including the bearing control parameters, in combination correspond to a combination of operational parameters defined to be indicative of a level of wear above a threshold wear level. The pitch bearings are then controlled based on the reference pitch angle and on the threshold determination.