Abstract: A turbine engine having a drive shaft rotatable about an axis, a multi-stage compressor, a turbine section, a thrust bearing, and a balance cavity. The thrust bearing being provided between the drive shaft and at least a portion of the multi-stage compressor section and rotationally supporting the drive shaft. During operation of the turbine engine, a first axial force is applied to the thrust bearing by the drive shaft and a second axial force is applied to the thrust bearing in an opposite direction of the first axial force by the balance cavity.

Abstract: A bearing arrangement for a wind turbine includes a bed frame, a shaft configured for connecting a rotor with a generator of the wind turbine, a front bearing and a rear bearing both supporting the shaft rotatably around a shaft axis, a front bearing housing supporting the front bearing, the front bearing housing including one or more feet connected to the bed frame, a rear bearing housing supporting the rear bearing, the rear bearing housing including one or more feet connected to the bed frame, and a stiffening element connecting one of the feet of the front bearing housing and one of the feet of the rear bearing housing. Having the stiffening element allows a reinforcement of the connection between the front bearing housing, the rear bearing housing and the bed frame. The stiffening element reduces the deformation of the bearing housings and the bed frame.

Abstract: A steam turbine plant includes high-pressure gland portions, low-pressure gland portions, a gland regulator line, and a rotor-driving steam supply line. The high-pressure gland portions supply gland steam to gaps of ends of a high-pressure turbine rotor, and thereby seal the gaps. The low-pressure gland portions supply the gland steam to gaps of ends of a low-pressure turbine rotor, and thereby seal the gaps. The gland regulator line guides the gland steam from the high-pressure gland portion to the low-pressure gland portion. The rotor-driving steam supply line branches off from the gland regulator line, and supplies some of the gland steam to a main steam flow passage in a low-pressure casing.

Abstract: A turbo compressor is provided that may include an impeller housing having an impeller accommodation space, an inlet formed at a first side of the impeller accommodation space, and an outlet formed at a second side of the impeller accommodation space that communicates with the inlet; an impeller accommodated in the impeller accommodation space of the impeller housing, rotated together with a rotary shaft by being coupled to the rotary shaft, and configured to centrifugally-compress a fluid suctioned through the inlet of the impeller housing and discharge the compressed fluid outside of the impeller housing through the outlet; a back pressure space formed between a rear surface of the impeller and the impeller housing; a back pressure passage connected between the outlet of the impeller housing and the back pressure space; and a back pressure control valve installed between the back pressure passage and the back pressure space, and configured to selectively open and close a region therebetween.

Abstract: A vertical tower fan may include a control unit, a fan unit having a shaft, a shell assembly and a main body. A securing unit supporting by a number of resilient units is disposed underneath the control unit. When the user wants to remove the fan unit from the fan, he/she can simply lift the securing unit, and the top portion of the shaft can be separated from the securing unit. Meanwhile, the bottom portion of the shaft can be removed from a protrusion, so the entire fan unit can be separated from the fan for cleaning or repairing without using any tools.

Abstract: A compressor system having a centrifugal compressor, controller and an interface is disclosed. The compressor includes adjustable guide vanes and a variable geometry diffuser. The controller is in electrical communication with each of the guide vanes and diffuser so as to monitor and adjust positions thereof in accordance with a predetermined control algorithm. The control algorithm is implemented in accordance with a method of controlling the centrifugal compressor. The method adjusts the position of the diffuser based on the actual lift, guide vane position and predetermined relationships between diffuser position and reference lift.

Abstract: The present invention relates to a rotor arrangement for a turbomachine, having a rotor with a first rotor stage, a shaft, and a first hub for joining the first rotor stage to the shaft. The first hub has a balancing device for balancing the first rotor stage. In addition, the present invention relates to a compressor.

Abstract: An adjusting mechanism, adaptive to a main body of a centrifugal compressor, comprises a diffuser channel width adjusting assembly and a gas bypass assembly. The diffuser channel width adjusting assembly comprises a width adjusting annular plate and a first valve stem. The width adjusting annular plate is movably disposed in a diffuser channel of the main body. The first valve stem is connected to the width adjusting annular plate, and configured for driving the width adjusting annular plate to move to adjust the width of the diffuser channel. The gas bypass assembly comprises a gas bypass valve and a second valve stem. The gas bypass valve is movably disposed in a gas bypass passage of the main body. The second valve stem is connected to the gas bypass valve, and configured for driving the gas bypass valve to move to adjust the opening of the gas bypass port.

Abstract: A centering arrangement includes a ring-like inner part and a ring-like outer part, whereby the outer part surrounds the inner part in a concentric arrangement and with an interspace established between the outer part and the inner part, and whereby the outer part and the inner part are subject to a differential radial expansion. A centering contact element, procures a centering mechanical contact between the outer part and the inner part at a plurality of circumferentially distributed contact points, and is able to deform in order to compensate for differential radial expansion.

Abstract: A system and method for controlling the acoustic signature of a turbomachine having a plurality of valves wherein an operating load is identified and an arc of admission across a plurality of nozzles is associated therewith. A valve sequencing scheme is selected and implemented to activate the arc of admission for a particular operating load so as to minimize valve noise by adjusting valves simultaneously rather than consecutively.

Abstract: An assembly can include a compressor housing, an adjustable wall disposed within the compressor housing that defines an air inlet to an inducer portion of a compressor wheel, and an adjustment mechanism to adjust the wall and thereby adjust at least a diameter of the air inlet. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Abstract: A compressor comprises a housing defining an inlet, a volute, an outlet, and a compressor chamber between the inlet and the outlet within which a compressor wheel is rotatably mounted. The housing has discrete attached first and second housing portions, the first housing portion defining at least part of the inlet and the second housing portion defining at least part of a volute of the outlet. The first housing portion has a conductive element for conducting an electric signal and a second sensor arrangement in sensing communication with the inlet. The compressor further comprises a first sensor arrangement, the first sensor arrangement being configured such that it is in sensing communication with the volute or outlet and such that it is electrically connected to the conductive element.

Abstract: An active clearance control system for a gas turbine engine includes a structural member that is configured to be arranged near a blade tip. A plenum includes first and second walls respectively providing first and second cavities. The first wall includes impingement holes. The plenum is arranged over the structural member. A fluid source is fluidly connected to the second cavity to provide an impingement cooling flow from the second cavity through the impingement holes to the first cavity onto the structural member. A method includes the steps of providing a conditioning fluid to an outer cavity of a plenum providing an impingement cooling flow through impingement holes from an inner wall of the plenum to an inner cavity, directing the impingement cooling flow onto a structural member, and conditioning a temperature of the structural member with the impingement cooling flow to control a blade tip clearance.

Abstract: A method for optimizing performance of a compressor by adjusting the position of an inlet guide vane and the speed of a drive unit. In one embodiment, the method can compare measured values for operating flow rate and operating pressure for a combination of operating settings for the position and the speed against threshold values for each of these measured values. In this way, the method can identify “how” the compressor is operating and equate such operation to one of a plurality of operation scenarios. In turn, the method can provide an adjustment to one or both of the speed and the position that corresponds with such operating scenario. The method can also vet the selected adjustment to avoid operation of the compressor outside of its safe operating configurations, as defined for example by minimum and maximum values for the position of the inlet guide vane and the speed of the drive unit.

Abstract: A system for operating a turbine includes a rotating component and a non-rotating component separated from the rotating component by a clearance. A first actuator is connected to the non-rotating component, and the first actuator comprises a shape-memory alloy. A method for operating a turbine includes sensing a parameter reflective of a clearance between a non-rotating component and a rotating component and generating a parameter signal reflective of the clearance. The method further includes generating a control signal to at least one actuator based on the parameter signal and moving at least a portion of the non-rotating component relative to the rotating component to change the clearance.

Abstract: A machine includes a rotor supported to rotate about a rotational axis and an actuator arranged to act on the rotor and control a position of the rotor about the rotational axis. A bladed turbomachine wheel is coupled to the rotor and has blade tips that pass closely to an adjacent, non-rotating surface. A sensor is adjacent to the turbomachine wheel and arranged to sense the blade tips and output a position signal representative of the position of blade tips relative to the sensor. A controller is coupled to the sensor and the actuator and is adapted to receive the position signal from the sensor and generate and send a control signal to the actuator to control the position of the rotor based on the position signal from the sensor.

Abstract: An apparatus and a process for measuring rotor creep values for a monolithic rotor of an industrial gas turbine engine in order to determine when creep growth of the rotor has exceeded an allowable limit. One or more critical locations of the rotor are measured for real-time radius, and a CPU having rotor creep deflection model is used to compare the real-time data and determine if the rotor creep is within safe and allowable limits. If the creep is determined to exceed allowable values, then an alarm in initiated or engine shutdown occurs.

Abstract: An axial compressor comprising liquid drop feed means for feeding liquid drops to an operating fluid of the compressor, a casing for forming a flow path through which the operating fluid flows down and a plurality of stages, each of which is composed of one continuous rotor blade row and one continuous stator vane row, the axial compressor being structured so that the liquid drops evaporate inside the compressor, characterized in that: the casing is provided with a cavity therein, and the cavity is formed by an outer casing and an inner casing which is enclosing a periphery of the rotor blade rows at the plurality of stages and forming internally a flow path of the operating fluid, and a flow path is provided for feeding the operating fluid to the cavity on a downstream side of a region forming the cavity of the inner casing.

Abstract: An arrangement for optimizing the running clearance for turbomachines of the axial type, such as turbocompressors, gas turbines, and steam turbines, in particular for compressors of stationary gas turbines, by controlling the inner diameter, which is relevant to the running clearance, of at least one stator structure that surrounds a rotor blade ring, including: the stator structure has a closed, circular inner ring, a circular outer ring that is situated concentric to the inner ring at a radial distance therefrom, and a plurality of links that integrally connect the inner ring to the outer ring, the links being circumferentially inclined at a defined angle (?) to the radial direction and distributed around the circumference of the stator structure, and the arrangement includes an adjustment device for rotating the inner ring relative to the outer ring with elastic modification of the running clearance-relevant inner diameter (D) of the inner ring.

Abstract: The present invention relates to a wind turbine comprising a nacelle (1) installed on a tower (2) supported by a floating support. The nacelle is articulated with respect to the tower in a vertical plane, and it comprises means (12, 16) for correcting the nacelle tilt, means for automatically adjusting the correction means in accordance with sensors detecting the correction values, the adjustment means being synchronous with the movements of the floating support.

Abstract: A regulating system for a gas turbine, in particular an aircraft engine, has devices for blade-tip injection for increasing the compressor stability, these devices being activated as needed. The regulating system has devices for active clearance control, preferably in the high-pressure compressor, with which the radial clearance in the high-pressure compressor is kept in an optimum operating range, and the regulating system has a shared engine regulator for both devices. The technical problems of the prior art are avoided through the present invention, and an improved regulating system for a gas turbine, in particular an aircraft engine, is made available for active stabilization of the compressor.

Abstract: It is intended to provide a single-casing steam turbine and a single-shaft combined-cycle power plant using the steam turbine that are capable of suppressing the performance decline of the high-pressure blade rows. A steam turbine 3 is a single-casing steam turbine having high-pressure blade rows 22 and low-pressure blade rows 26 and includes a high/intermediate-pressure chamber 10 housing the high-pressure blade rows 22, a low-pressure chamber 12 housing the low-pressure blade rows 26, and an expansion joint 30 for connecting the high/intermediate-pressure chamber 10 and the low-pressure chamber 12 and for sealing an interior space 31 of the high/intermediate-pressure chamber 10 and the low-pressure chamber 12.

Abstract: A device and method for axially displacing at least one turbine rotor relative to at least one corresponding turbine stator in a multistage axial turbine is disclosed. The turbine shaft is provided with a split design and has a first axially displaceable shaft half, which is connected via a turbine disc to the turbine rotor and via a torque coupling to the second shaft half. By axially displacing the turbine rotor relative to the turbine stator and by controlling this axial displacement, the operation of the turbine is held in its possible optimum of efficiency.

Abstract: A system for detecting loads in a wind turbine is disclosed. In one aspect, the system may generally include a shaft and first and second pillow blocks receiving portions of the shaft. The second pillow block may be spaced axially apart from the first pillow block. Additionally, the system may include at least one sensor configured to indirectly detect loads transmitted through at least one of the first pillow block and the second pillow block.

Abstract: A turbomachine has a housing, a rotor shaft extending along and rotatable about an axis in the housing, and a pair of axially spaced axial-thrust bearings in the housing carrying the shaft and normally only permitting a predetermined small axial displacement of the shaft in the housing. An impeller is rotationally fixed on the shaft. An axially fixed transmission gear is rotationally coupled to the shaft and has an axially directed gear face. A collar fixed axially on the shaft has an axially directed collar face confronting the gear face and normally spaced from the gear face by a clearance equal to more than the predetermined axial displacement. Thus on failure of one of the bearings and axial overtravel of the shaft the gear face and collar face engage each other and limit axial movement of the shaft.

Abstract: A steam turbine 20 is provided with a casing 109, a turbine rotor 25 disposed through the casing 109, and labyrinth portions 50, 55 which are disposed at the boundary between the casing 109 and the turbine rotor 25. The steam turbine 20 is further provided with a sealing steam pipe 65 for supplying sealing steam to the labyrinth portions 50, 55 and a gas supply pipe 60 for supplying the labyrinth portions 50, 55 with a cooling gas for cooling the turbine rotor 25 or a heating gas for heating the turbine rotor 25.

Abstract: A turbomachine has a housing, a rotor shaft centered on an axis, and a plurality of bearings supporting the shaft in the housing for rotation about the axis. At least one of the bearings is an active magnetic bearing. An impeller is fixed on the rotor shaft. A copper layer is fixed to a surface of the rotor shaft and rotatable therewith. A sensor fixed in the housing adjacent the shaft surface can detect the copper layer and generate an output corresponding to a position of the layer from the sensor fixed in the housing. A controller connected between the sensor means and the active magnetic bearing shifts the rotor in the housing in accordance with the output.

Abstract: Systems, methods, and apparatus for monitoring clearance in a rotary machine are provided. According to one embodiment of the invention, there is disclosed a method for monitoring clearance between a rotatable member and a stationary member in a rotary machine. The method may include providing a flex circuit capacitance sensor. The flex circuit capacitance sensor may include at least one capacitance sensing layer, at least one shielding layer adjacent to the capacitance sensing layer, at least one ground layer adjacent to the shielding layer, and a set of conducting leads connected to the capacitance sensing layer. Further, the method may include mounting the capacitance sensor between a portion of the rotatable member and a portion of the stationary member. Clearance may be determined between the rotatable member and the stationary member based at least in part on a capacitance indication from the capacitance sensor.

Abstract: The present invention relates to a control method for the operation of a fan equipping an electronic device. A determination step detects the vertical or horizontal position of the electronic device. The fan is not started up during the powering up of the device while the device is in a vertical position. The flow of air produced by the “fireplace” effect in the device in a vertical position suffices to ensure correct ventilation. According to an improvement the device has a sensor measuring the internal temperature of the device, whatever the position of the device, the fan being started up from a determined temperature. The present invention relates also to a device implementing the method.

Abstract: A wind energy systems includes a shroud for each turbine. The shroud is adapted to direct and accelerate wind towards the turbine. A strong adaptable support assembly is provided for securing turbines to a structure. An air glide yaw assembly facilitates rotational movement of the structure allowing the turbines to face oncoming wind. The turbine blades are optimized for use with a shroud.

Abstract: A method of detecting rubs during operation of a turbomachine comprising at least one rotating object having a tip and a shelf is provided. The method includes generating signals representative of a sensed parameter and processing the signals to generate height versus time data for the tip. The height of the tip corresponds to the distance between the tip and the shelf. The method further includes monitoring the height versus time data, in order to determine whether a change in the height data exceeds a threshold value, and detecting a rub of the rotating object(s) on a second object, when the change in the height data exceeds the threshold value. A rub detection system for a turbomachine and a turbine engine system with rub detection are also provided.

Abstract: A gas turbine with an active clearance control system includes a plurality of actuators circumferentially spaced between an inner shroud and an outer casing. The actuators are configured to eccentrically displace the shroud relative to the outer casing. A plurality of sensors circumferentially spaced around the shroud detect a parameter that is indicative of an eccentricity between the rotor and shroud as the rotor rotates within the shroud. A control system in communication with the sensors and actuators is configured to control the actuators to eccentrically displace the shroud to compensate for eccentricities detected between the rotor and shroud.

Abstract: Methods and devices for performing a low torque low speed test to determine whether a rotor of a turbomachinery is free to rotate are provided. A method includes automatically applying a torque to the rotor, the torque gradually increasing up to a predetermined torque value. The method further includes monitoring the speed of the rotor while the torque is gradually increased. The method also includes outputting an indication that the rotor is free to rotate after the speed of the rotor becomes positive, or outputting an indication that the rotor is locked when the speed of the rotor remains zero and the applied torque has reached the predetermined torque value.

Abstract: Disclosed is a seal for a turbomachine including at least one fixed component located proximate to a rotating component of the turbomachine defining a clearance therebetween. At least one magnet is located at the at least one fixed component. The at least one magnet is, when activated, capable of moving the at least one fixed component thereby adjusting the clearance between the fixed component and the rotating component. Further disclosed is a turbomachine utilizing the seal and a method for adjusting a position of at least one fixed component of a turbomachine.

Abstract: A turbine for use with a turbine generator, the turbine including at least one turbine blade for positioning in a flowpath, a hub mounting the at least one turbine blade, and a rotatable shaft in operational communication with the hub via a hinge assembly, an axis of the hub being independent of an axis of the shaft. The hinge assembly is disposed between the shaft and the hub and configured to adjust an angle therebetween. A controller assembly is configured to adjust at least one operational characteristic of the hinge assembly during turbine operation. In one embodiment the operational characteristic is a teeter angle of the hinge assembly. In one embodiment operational characteristic is a stiffness or damping force. Methods for using and controlling a fluid turbine are also disclosed.

Abstract: An electrode (54) in the tip (31) of a turbine or compressor blade (30), and a series of electrodes (68) in a shroud (36, 64) that surrounds a rotation path (33) of the blade tip. As the blade tip reaches each shroud electrode, a controller (74) activates an electrical potential between them that generates a plasma-induced gas flow (76) directed toward the pressure side (PS) of the airfoil. The plasma creates a seal between the blade tip and the shroud, and induces a gas flow that opposes a leakage gas flow (52) from the pressure side to the suction side (SS) of the blade over the blade tip (31).

Abstract: Sensors (32, 52, 72) for determining a gap between a conductive member (34, 54, 74) such as a blade in a gas turbine engine and a seal segment (31, 51) are known to use capacitive variants in order to create an electrical signal indicative of the gap width. Thermal disparities can create problems with regard to sensor aging and accuracy. By creating a sensor incorporating a metal rod (33, 53, 74) typically integrally formed or associated with the seal segment (31, 51) and coupled through inductive coupling loops (35, 36; 55, 56; 75) it is possible to create a tuned circuit with a Q value which is more stable and therefore acceptable with regard to producing more accurate results at elevated temperatures with less problems with regard to thermal disparities.

Abstract: A steam turbine comprises a rotor with moving blades attached thereto; diaphragms which surround the rotor from an outer periphery side of the rotor; a casing which encloses the diaphragms and the rotor and has an upper half and a lower half clamped together through respective flanges; a displacement detector for measuring a difference d in thermal expansion in the rotor axis direction between the casing and the rotor; heating/cooling devices attached to the flanges respectively to heat and cool the flanges; and a controller which makes control so that the flanges are heated or cooled by the heating/cooling devices until a measured value obtained by the displacement detector reaches a preset value M or S in unsteady operation.

Abstract: A device for determining distance between a rotor blade and a wall of a gas turbine surrounding the rotor blade is provided. A waveguide guides and emits electromagnetic waves of at least one frequency in the direction of the rotor blade through a waveguide opening facing the rotor blade. The electromagnetic waves are injected into the waveguide and reflected portions of the electromagnetic waves are received. An evaluation unit compares the phase of the electromagnetic waves to be injected with the phase of the reflected portions of the electromagnetic waves and determines phase comparison values for every frequency and the distance is determined based on the phase comparison values. The waveguide comprises a sealing element which is configured to be transmissible for the electromagnetic waves of the frequency and which has two opposite surfaces in the direction of guidance of the electromagnetic waves.

Abstract: An embodiment of the present invention provides a system for controlling the overall thrust extorted on a rotor. The system includes a chamber that encloses a portion of the rotor. A seal system may seal the chamber and the rotor. A fluid system may provide a pressurized fluid to the chamber and the fluid may oppose the thrust exerted by the rotor. The system may also include a control system configured for monitoring the position of the rotor; and utilizing the pressurized fluid to reduce the overall thrust load.

Abstract: A gas turbine with an active clearance control system includes a plurality of actuators circumferentially spaced between an inner shroud and an outer casing. The actuators are configured to eccentrically displace the shroud relative to the outer casing. A plurality of sensors circumferentially spaced around the shroud detect a parameter that is indicative of an eccentricity between the rotor and shroud as the rotor rotates within the shroud. A control system in communication with the sensors and actuators is configured to control the actuators to eccentrically displace the shroud to compensate for eccentricities detected between the rotor and shroud.

Abstract: An arrangement is provided for detecting a shaft break on a rotor of a first turbine, especially a medium pressure turbine, of a gas turbine machine, especially an aircraft engine. A second turbine (11), especially a low pressure turbine, is positioned downstream from the first turbine. An actuating element (18) is positioned lying radially inwardly relative to a flow channel, between the rotor of the first turbine and a stator of the second turbine. A transmission element (22) is guided in the stator of the second turbine (11), in order to transmit a shaft break detected by the radially inwardly positioned actuating element (18) to a switching element (23) positioned radially outwardly relative to the flow channel on a housing (14) of the gas turbine.

Abstract: A regulating system for a gas turbine, in particular an aircraft engine, has devices for blade-tip injection for increasing the compressor stability, these devices being activated as needed. The regulating system has devices for active clearance control, preferably in the high-pressure compressor, with which the radial clearance in the high-pressure compressor is kept in an optimum operating range, and the regulating system has a shared engine regulator for both devices. The technical problems of the prior art are avoided through the present invention, and an improved regulating system for a gas turbine, in particular an aircraft engine, is made available for active stabilization of the compressor.

Abstract: A gas turbine machine includes a second turbine (11), e.g. a low pressure turbine, positioned downstream from a first turbine (10), e.g. a medium pressure turbine. An arrangement for detecting a shaft break of a rotor shaft includes an operator element (16) positioned between the rotor of the first turbine (10) and a stator of the second turbine (11) radially inwardly relative to a flow channel, and a sensor element (21) guided in the stator of the second turbine (11), to convert a shaft break, detected by the radially inwardly positioned operator element (16), into an electrical signal and to transmit this electrical signal to a switching element which is positioned radially outwardly relative to the flow channel on a housing of the gas turbine machine.

Abstract: An apparatus for sealing a turbine against leakage of a working fluid comprising at least one radially displaceable sealing ring, coaxially disposed about a rotating member of the turbine from a stationary member of the turbine, which sealing ring undergoes radial displacements that are coupled to radial displacements of the rotating member, such that a design radial clearance is substantially maintained without damage to the apparatus.

Abstract: A gas turbine, such as an aircraft engine, has at least one compressor, at least one turbine, a combustion chamber, and a fuel pump to supply fuel to the combustion chamber. Upon identification of a break of a shaft that couples a compressor with a turbine, the gas turbine is shut off. For this purpose, at least one electrical current conductor is arranged on the shaft, whereby this current conductor is a component of a current supply for the fuel pump or for a fuel pump regulation. When the integrity of the current conductor is disrupted, thereby the current supply of the fuel pump or of the fuel pump regulation is interrupted in order to automatically shut off the gas turbine.

Abstract: A system for measuring clearance between a first object and a second object is provided. The system includes a sensor configuration to generate a first signal representative of a first sensed parameter and a second signal representative of a second sensed parameter. The system also includes a clearance measurement unit configured to process the first and second signals based upon a ratiometric technique to calculate clearance between the first and second objects.

Abstract: A turbomachine has a housing, a rotor shaft extending along and rotatable about an axis in the housing, and a pair of axially spaced axial-thrust bearings in the housing carrying the shaft and normally only permitting a predetermined small axial displacement of the shaft in the housing. An impeller is rotationally fixed on the shaft. An axially fixed transmission gear is rotationally coupled to the shaft and has an axially directed gear face. A collar fixed axially on the shaft has an axially directed collar face confronting the gear face and normally spaced from the gear face by a clearance equal to more than the predetermined axial displacement. Thus on failure of one of the bearings and axial overtravel of the shaft the gear face and collar face engage each other and limit axial movement of the shaft.

Abstract: An apparatus and method for controlling a blade tip clearance for a compressor of a turbo-engine, in particular of an aircraft engine, is disclosed. A blade tip clearance control device, which has a rotor and a housing surrounding the rotor forming a blade tip clearance, includes a sealing element that is movable into the blade tip clearance and an actuator unit, where the sealing element is designed as a circumferential shroud liner made of a flexible rubbery material in which at least one tubular diaphragm that is also circumferential is arranged. The diaphragm is acted upon with hydraulic fluid via the actuator unit. This makes it possible to counteract degradation that occurs during operation due to erosion, aging, etc. As a result, efficiency is maintained and the pump limit interval is retained.

Abstract: A wind turbine generator includes at least one rotating member, at least one stationary member, and a clearance gap control system. The stationary member is positioned such that a clearance gap is defined between a portion of the rotating member and a portion of the stationary member. The clearance gap is configured to facilitate transmitting a controllable magnetic flux therethrough. The control system includes at least one clearance gap measurement assembly, at least one power converter, and at least one controller. The controller is coupled in electronic data communication with the assembly and the converter and is configured to modulate a dimension of the gap by modulating the flux.