Abstract: A method for cooling a compressor section of a gas turbine engine includes sensing, via at least one first temperature sensor, a first temperature at the first location on a stationary assembly of the compressor section. The method also includes sensing, via at least one second temperature sensor, a second temperature at a second location on the stationary assembly of the compressor section. The second location is spaced apart from the first location. The method also includes determining, via a controller, a delta between the first temperature and the second temperature. Further, the method includes operating, via the controller, at least one cooling element when the delta exceeds a predetermined threshold, the at least one cooling element provided at the first location of the stationary assembly of the compressor section.

Abstract: An engine control system may be configured to perform a method of controlling thermal bias in a turbomachine. An exemplary method may include determining a thermal bias-value for the turbomachine, and performing a cooling treatment based at least in part on the thermal bias-value. The thermal bias-value may include a difference between an upward temperature-value corresponding to a first one or more temperature measurements of an upward portion of the turbomachine and a downward temperature-value corresponding to a second one or more temperature measurements of a downward portion of the turbomachine. The cooling treatment may include at least one of: circulating air through at least a portion of the turbomachine, and rotating a shaft of the turbomachine with a motoring system.

Abstract: An automated method to determine modal characteristics of a wind turbine tower at an offshore location in a continuous manner includes reading one or more sensor data signals, prefiltering the one or more sensor data signals to divide the signals into a plurality of time segments, obtaining a frequency domain representation of each of the plurality of time segments by computing a Power Spectral Density (PSD) of each of the time segments to identify one or more frequency peaks in each of the time segments, assigning a probability to each of the frequency peaks in the PSD of each of the time segments, combining all assigned probabilities and determining the likelihood of the one or more frequency peaks. Also disclosed is an offshore wind turbine tower having a turbine control system utilizing the automated method to determine modal characteristics of the wind turbine.

Abstract: A system for measuring pump efficiency includes a pump configured to pump a fluid, a suction pipe disposed upstream of a suction side of the pump, a discharge pipe disposed downstream of a discharge side of the pump, a first pipe section disposed between the suction pipe and the suction side of the pump, and a second pipe section disposed between the discharge pipe and the discharge side of the pump. Each of the first pipe section and the second pipe section includes a temperature sensing pipe liner configured to measure a temperature of the fluid in the first pipe section, and a thermal insulator disposed radially outward of the temperature sensing pipe liner.

Abstract: A pump assembly includes an electrical drive motor (2) and an impeller which is connected to the drive motor (2) via a shaft (14). The shaft extends between the drive motor (2) and the impeller, through a seal arrangement with a fluid reservoir (22). A method is provided for detecting a concentration change in a fluid reservoir in the seal arrangement in the pump assembly. A concentration sensor (30) detects a concentration change in the fluid reservoir (22), and a second sensor (32) detects at least one further parameter of the fluid reservoir (22). The sensors are arranged on the fluid reservoir (22). The sensors are connected to an evaluation device (22). The evaluation device (34) is configured to carry out an evaluation of at least one reading of the concentration sensor (30), taking into account at least one reading which is detected by the second sensor (32).

Abstract: There is provided a combustor including a nozzle main body (16) that includes a shaft body (24) which extends along an axis and has, inside the shaft body (24), a purge air flow path (29), which extends along the axis to a tip portion of the shaft body (24) and into which compressed air is introduced, and an air spraying hole (39), which is formed in the tip portion of the shaft body (24) and connects the purge air flow path (29) to an outer surface of the shaft body (24), a swirling blade (26), which overhangs from an outer circumferential surface of the shaft body (24) in a diameter direction of the axis and swirls a fluid flowing to a downstream side of an axial direction around the axis, and a fuel spraying hole (38), and a sealing member (40) that seals the air spraying hole (39) and is formed of a metal having a melting point lower than a melting point of a metal forming the nozzle main body (16).

Abstract: A method for selectively modulating bleed air used for cooling a downstream turbine section in a gas turbine engine. The method including: measuring an engine and/or aircraft performance parameter by an engine sensor device; comparing the engine and/or aircraft performance parameter to a performance threshold; determining a bleed trigger condition, if the engine and/or aircraft performance parameter crosses the performance threshold; determining a non-cooling condition, if the engine and/or aircraft performance parameter is below the performance threshold; actuating a flow control valve to an open position, in response to the bleed trigger condition, so that bleed air is extracted from the compressor section and flowed to the downstream turbine section; and terminating, in response to the non-cooling condition, the flow of the bleed air to the downstream turbine section of the engine by actuating the flow control valve to a closed position.

Abstract: An anti-icing system for a turbine engine vane extending between an outer casing and an inner casing defining a passage, the system includes an injector device for injecting a jet of air into the passage upstream from the vane, the injector device including a first injection orifice for injecting the jet of air, the first orifice passing through one member selected from the outer casing and the inner casing, and being located in such a manner that, at a first speed of the engine wherein a stream of air flows generally in the passage along a first direction, the first orifice and a leading edge of the vane are substantially in alignment along the first direction, the first orifice is spaced apart from the junction between the leading edge of the vane and the member through which the first orifice passes by a distance of at least 10 mm, and preferably of about 15 mm.

Abstract: A hydraulic system includes a circulation pump assembly (2) provided with a speed controller (4, 26), a hydraulic circuit (A, B) connected to the circulation pump assembly (2) as well as a mechanical switch device (86, 88; 120, 122; 120?, 122?) which is subjected to pressure from a fluid in the hydraulic circuit (A, B) and which can be moved into at least two different switch positions. The mechanical switch device (28; 86, 28; 120, 122) can be moved by the circulation pump assembly (2) by way of a hydraulic coupling via the fluid. The speed controller is configured to initiate a movement of the switch device (86, 88; 120, 122; 120?, 122?) by way of at least one hydraulic force acting thereon and causing a movement of the switch device (86, 88; 120, 122; 120?, 122?), produced via the hydraulic circuit, via a speed adaptation of the circulation pump assembly.

Abstract: A motor drive control apparatus is mounted on a fan having a motor and an impeller coupled to the motor. The motor drive control apparatus includes a temperature sensor for measuring a temperature correlated with a temperature of the impeller, a temperature comparing portion for comparing a detected temperature based on a measurement result of the temperature sensor with a first temperature higher than a highest value of a design temperature of the fan, a rotation speed setting portion for setting an upper limit value of the rotation speed of the motor based on a comparison result the temperature comparing portion, a PWM command portion for controlling such that the rotation speed of the motor does not exceed the upper limit value set by the rotation speed setting portion.

Abstract: A centrifugal compressor is disclosed. The compressor includes an impeller, an electromagnetic actuator, and a flow control insert. The flow control insert is selectively moveable in response to the electromagnetic actuator to regulate a flow of fluid expelled by the impeller.

Abstract: A turbo-molecular pump comprises: a rotor; stationary blades; a stator; a plurality of spacers; a heater disposed on the base; a temperature sensor for detecting a temperature of the stator; and a temperature regulation section for on/off controlling the heater based on a temperature detected by the temperature sensor to regulate the temperature of the stator so as to be a reaction product accumulation prevention temperature. At least one spacer arranged on a base side of the plurality of spacers is cooled by coolant, and the turbo-molecular pump further comprises a heat insulation member disposed between the base and the spacer arranged on the base.

Abstract: A housing unit (22) for a heating device with two heating circuits, one for space heating and another for service water heating, includes a pump housing (23) for a recirculation pump (8). The housing unit (22) encompasses a switching valve for switching the heating circuits, and in its rear installation position exhibits at least one port to directly connect a plate heat exchanger (6) for heating service water. An opening (29) for the return of the space heater is arranged on one side of the housing unit. The housing unit incorporates an inlet chamber (28), which is adjoined by the inlet mouth (26) of the pump (8), and into which two channels empty, of which one or the other can be optionally closed by a valve body (32), and of which one channel leads to the line port (30) for the return, and the other channel leads to a port of the plate heat exchanger (6).

Abstract: A turbine engine shutdown temperature control system configured to foster consistent air temperature within cavities surrounding compressor and turbine blade assemblies to eliminate turbine and compressor blade tip rub during warm restarts of gas turbine engines is disclosed. The turbine engine shutdown temperature control system may include one or more casing temperature control housings extending along an inner surface of a casing at an outer diameter of the casing and at an upper side region of the casing. The upper side region may be positioned above a horizontally extending centerline of the casing. Fluids may be exhausted from one or more exhaust slots in the casing temperature control housing to isolate the upper side region of the casing from buoyancy effects of hot gases within the casing after shutdown of the gas turbine engine.

Abstract: A seal assembly provided between a hot gas path and a disc cavity in a turbine engine includes an annular outer wing member extending from an axially facing side of a rotor structure toward an adjacent non-rotating vane assembly, and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly. The fins are arranged such that a space having a component in a circumferential direction is defined between adjacent fins. Rotation of the fins during operation of the engine effects a pumping of purge air from the disc cavity toward the hot gas path to assist in limiting hot working gas leakage from the hot gas path to the disc cavity by forcing the hot working gas away from the seal assembly.

Abstract: A connector for connecting an impeller to a shaft is provided. The connector is formed as a unitary body. The connector has a sleeve portion which is frictionally connected on a radially outer surface of a shaft-side hub extension of the impeller. The connector further has a threaded portion carrying a thread which screws onto a corresponding threaded portion of the shaft, such that the connector provides a rotationally fixed connection between the impeller and the shaft. The hub extension has a central recess, and a part of the connector is inserted into the recess. The frictional connection between the sleeve portion and the radially outer surface of the hub extension transmits, in use, substantially all of the torque between the shaft and the impeller.

Abstract: Systems for thermally regulating portions of a steam turbine are disclosed. In one embodiment, a thermal control system for a rotor bearing support includes: a housing fluidly connected to an inlet and adapted to substantially enclose the rotor bearing support, the housing defining a first annular cavity adapted to receive a fluid from the inlet; and an outlet fluidly connected to the housing, the outlet adapted to receive the fluid from the annular cavity.

Abstract: The systems, methods, and computer-readable media set a gas turbine firing temperature to maintain gas turbine metal surface temperatures. In certain embodiments, a method of setting a gas turbine firing temperature is disclosed that may comprise determining a critical temperature at which ash from ash bearing fuels becomes unremovable by conventional water wash procedures, determining hot gas path component metal surface temperatures, and adjusting the gas turbine firing temperature to maintain the metal surface temperatures below the critical temperature. Determining the metal surface temperatures may be based at least in part on measured gas turbine parameters, gas turbine performance models, and empirical models.

Abstract: According to one embodiment, an electronic device includes a fan, a temperature sensor and a controller. The temperature sensor is configured to output a value indicative of a detected temperature. The controller is configured to control a rotational speed of the fan. The controller is configured to keep the rotational speed of the fan constant when the value is within a first temperature zone or to change the rotational speed of the fan when the values is within a second temperature zone.

Abstract: A method for adjusting a barometric cell may include coupling the barometric cell to a control device via an actuating rod. The actuating rod may be movably mounted on a charging device in any desired position. The method may include applying a freely selectable pressure to the barometric cell so as to bring the actuating rod into contact with a stop, adjusting the barometric cell until a sensor registers a predefined value, and fixing the barometric cell on the charging device.

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 turbo-molecular pump comprises: a rotor having a plurality of stages of rotor blades and a cylindrical section; a plurality of stages of stationary blades alternately arranged with respect to the rotor blades; a stator arranged with a gap from the cylindrical section, the stator together with the cylindrical section constituting a screw groove pump section; a plurality of spacers stacked on a base, the spacers including at least one cooling spacer having a cooling section; a heater heating the stator; a temperature regulation section controlling the heater to regulate the temperature of the stator so as to be a reaction product accumulation prevention temperature; and an auxiliary ring for reaction product accumulation prevention at least a part of which is located in a space between the spacer facing a bottom step rotor blade, and the bottom step rotor blade.

Abstract: A water pump (30) includes an impeller chamber (32) formed in a housing (31), a swirl chamber (40) formed in the housing (31) to communicate with a coolant passage (8) and the impeller chamber (32), and an impeller (33) that is supported to be free to rotate in the impeller chamber (32) and rotates in conjunction with an engine (2) so as to take in a coolant and discharge the coolant into the coolant passage (8) via the swirl chamber (40). The swirl chamber (40) is formed to be divided into a first swirl chamber (41) that communicates with the coolant passage (8) at all times, and a second swirl chamber (42) and a third swirl chamber (43) respectively connected to the coolant passage (8) via thermostats (S1, S2) respectively having switch valves that can be opened and closed. The thermostats (S1, S2) are operated to open and close, thereby connecting and cutting off the swirl chambers (42, 43) and the coolant passage (8), in accordance with a temperature of the coolant.

Abstract: A temperature detection device that detects a temperature of a rotor of a motor. The temperature detection device has a current detection unit configured to detect a current value of a current flowing through a winding with which any one of a stator and the rotor of the motor is provided, an iron loss estimation unit configured to estimate an iron loss of the rotor using the current value, and a rotor temperature estimation unit configured to estimate the temperature of the rotor using the iron loss.

Abstract: A fan control system for processor is provided. The system has: a fan, configured to cool the processor; a power measurement module, coupled between the processor and a power supply of the processor, configured to measure the power of the processor; and a control module, coupled between the fan and the power measurement module, configured to control a speed of the fan according to the power of the processor, wherein when the power is higher than a predetermined power upper limit, the control module control the fan to increase the rotation speed.

Abstract: A turbine vane cooling system operably coupling a cooling fluid source to a turbine vane assembly is disclosed herein. A plurality of turbine vanes having an airfoil shaped surface forming a substantially hollow body is connected to the turbine vane assembly. An inlet can be operably connected to each turbine vane to form a fluid communication path between a cooling fluid source and an interior of the hollow body of each turbine vane. At least one outlet fluidly communicating with the interior of said hollow body can be formed in the vane. A regulating member can variably block a portion of an inlet of each of the turbine vanes in response to a temperature of each turbine vane.

Abstract: A turbocharger of a supercharging apparatus includes a turbine impeller, which is rotatable by exhaust gas discharged from an internal combustion engine of a vehicle. An electric heater is placed in an exhaust passage, which extends from an exhaust outlet of the internal combustion engine to the turbine impeller. The electric heater generates a heat when the electric heater is energized.

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: A verification method for a rotation speed value of a fan includes steps of receiving a predictive rotation speed value of the fan, an input environmental temperature value and a plurality of temperature values of components, sending the received environmental temperature value and a plurality of temperature values of components to the control unit to control the fan to rotate on the condition of the input temperature values; acquiring the actual rotation speed value of the fan on the condition of the input temperature values; detecting whether the actual rotation speed value of the fan is consistent with the predictive rotation speed value of the fan; and outputting information of showing that the actual rotation speed value of the fan does not match the predictive rotation speed value of the fan if not.

Abstract: A guide vane of a condensation turbine steam turbine is provided, wherein the guide vane includes a heating resistor. The guide vane includes fiber composite material at least in some regions. The heating resistor may be embodied as a heating wire or as a heating film. A condensation steam turbine having a guide vane as described above is also provided.

Abstract: The disclosure relates to a method for determining a temperature in a pressurized flow path of a gas turbine comprising the steps of sending an acoustic signal from an acoustic signal emitting transducer across a section of the pressurized flow path, detecting the acoustic signal with a receiving transducer, measuring the time needed by the acoustic signal to travel from the acoustic signal emitting transducer to the receiving transducer, calculating the speed of sound, and calculating the temperature as a function of the speed of sound, the heat capacity ratio (?) and a specific gas constant (Rspec) of the gas flowing in the pressurized flow path. Besides the method, a gas turbine with a processor and transducers arranged to carry out such a method is disclosed.

Abstract: A cooling system includes: a cooling fan configured to take in air through an air filter and to send the air to one or more electronic components; one or more first temperature detectors configured to detect temperatures of the one or more electronic components; a revolution controller configured to control a number of revolutions of the cooling fan on basis of the temperatures detected by the one or more first temperature detectors; and a clogging detector configured to, when the number of revolutions of the cooling fan controlled by the revolution controller is greater than a reference number of revolutions of the cooling fan that makes the temperature of the one or more electronic components less than upper-limit temperatures of the one or more electronic components, detect a clogging condition for the air filter.

Abstract: A turbine engine includes a turbine, a compressor for compressing air and a combustor for receiving the compressed air through an inlet passage and operable to burn fuel therewith to deliver hot exhaust gas to the turbine. Also included is a wheel space defined proximate to the combustor. Further included is a cooling air passage extending between the compressor and the wheel space. Yet further included is a valve assembly having a valve member disposed in the cooling air passage and operable to admit a cooling air to the wheel space in response to a condition therein.

Abstract: A system includes a radiation detector array directed toward a fluid flow into a compressor. The radiation detector array is configured to output a signal indicative of a two-dimensional temperature profile of the fluid flow. The system also includes a controller communicatively coupled to the radiation detector array. The controller is configured to detect a temperature variation across the fluid flow based on the signal, and to adjust a parameter of a temperature control device to compensate for the detected temperature variation.

Abstract: Embodiments of the invention can provide systems and methods for determining a target exhaust temperature for gas turbines. In one embodiment of the disclosure, there is disclosed a method for determining a target exhaust temperature for a gas turbine. The method can include determining a target exhaust temperature based at least in part on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based at least in part on steam humidity; and changing the target exhaust temperature based at least in part on the temperature adjustment.

Abstract: Cooling system for a data center includes at least one air-conditioner, at least one air-guiding fan, a first temperature sensor, a second temperature sensor, and a control unit. The air-guiding fan exchanges air between the data center and an external environment of the data center. The first temperature sensor senses an interior temperature of the data center. The second temperature sensor senses an environmental temperature outside of the data center. The control unit controls operating state of the air-conditioner, the first air-guiding fan, and the second air-guiding fan. When the environmental temperature is lower than the interior temperature, the control unit turns off the air-conditioner and the air-guiding fan.

Abstract: A method for controlling at least two turbocompressors (1.1, 2.1), each having a control device (1.2, 2.2) for maintaining a distance relative to a surge limit curve (P1, P2) of the respective turbocompressor; wherein a first distance (A1.1, A2.1) is determined for each turbocompressor from its surge limit curve; wherein the distance to be maintained can be trimmed relative to this first distance in the control devices; and wherein the distance (A2.2) of a control device (2.2) to be maintained is trimmed relative to its first distance (A2.1) based on a trimming (A1.1?A1.2) of another control device (1.2) in such a way that a total process variable (dV/dt) remains substantially constant.

Abstract: A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. The supported structure includes a hook providing an annular recess. A support ring is received in the recess. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure.

Abstract: A system and method thereof is provided for electrically heating a component. The system includes at least one heating element adapted to be adhesively bonded to a surface on the component and means for controlling flow and duration of an electrical current to the heating element from a power supply. The controlling means comprises a first heating cycle for curing an adhesive to bond the heating element to the surface and has a second heating cycle for providing ice protection to the surface.

Abstract: A system for a turbofan has a variable outer air seal, an actuator coupled to the variable outer air seal, a sensor positioned inside the turbofan for sensing an engine parameter, and a flight controller connected to the turbofan for receiving the parameter from the sensor. The flight controller directs the actuator to regulate the position of the actuator based on the flight condition resulting form the received parameter.

Abstract: An exemplary flow control device assembly for a turbomachine includes a flow control device configured to move between a first position and a second position. The flow control device in the first position forces more flow through a plurality of cooling holes than the flow control device in the second position. The plurality of cooling holes are upstream the flow control device relative a direction of flow through the turbomachine.

Abstract: A method controlling a clearance between tips of blades of a turbine rotor of a gas turbine aircraft engine and a ring-shaped turbine shroud of a housing surrounding the blades, the method including: controlling flow and/or temperature of air directed toward the housing according to an estimate of the clearance, the estimate of the clearance is determined upon start-up of the aircraft engine, according to a temperature measured by a temperature sensor including a sensitive element positioned in a free space of the aircraft engine.

Abstract: A fan control system and a fan controlling method thereof are disclosed. The fan control system is used to an electronic apparatus for controlling an air pump fan device. The fan controlling method includes following steps: setting a plurality of vibrating working periods of the air pump fan device; setting a plurality of vibrating frequencies of the air pump fan device, wherein each vibrating frequency has a different vibrating frequency value; detecting a temperature of the electronic apparatus; determining whether the temperature of the electronic apparatus exceeding a first setting temperature; and if yes, controlling the air pump fan device to vibrate according to the plurality of vibrating frequencies during the plurality of vibrating working periods, wherein adjacent vibrating working periods of the plurality of vibrating working periods correspond to different vibrating frequency values.

Abstract: Various systems for processing air are disclosed. In one embodiment, an air processing system includes: an inlet manifold adapted to receive compressor discharge air from multiple turbine compressors; an air processing system fluidly connected with the inlet manifold, the air processing system adapted to process the compressor discharge air to provide a processed working fluid; an outlet manifold adapted to provide the processed working fluid to multiple turbine inlet filtration system; and a control system operably connected to the inlet manifold, the air processing system and the outlet manifold, the control system configured to control flow of the compressor discharge air from the multiple turbine compressors to the inlet manifold.

Abstract: A motor is provided which can detect a rotor temperature with high precision with a simple configuration not taking an influence on a temperature caused by circulation of a cooling oil into account. In a motor including a rotor, a stator arranged around the rotor, and a temperature sensor, the rotor includes an oil reservoir unit that reserves an oil on a rotating shaft line in an interior thereof, and the temperature sensor detects a temperature of the oil reserved in the oil reservoir unit.

Abstract: A system for controlling a centrifugal gas compressor (108) in an HVAC, refrigeration or liquid chiller system (100) in which flow of gas through the compressor is automatically controlled to maintain desired parameters within predetermined ranges so as to prevent stall and surge conditions within the system. A variable geometry diffuser (119) in the compressor controls the refrigerant gas flow at the discharge of the compressor impeller wheel (201). This arrangement reduces mass flow, decrease/eliminate flow-reducing stall, and increases the operating efficiency of the compressor at partial load conditions. The variable geometry diffuser control in combination with a variable speed drive (VSD) (120) increases the efficiency of the compressor at partial system loads, and eliminates the need for pre-rotation vanes at the inlet of the centrifugal compressor.

Abstract: A metallic seal assembly, a turbine component, and a method of regulating flow in turbo-machinery are disclosed. The metallic seal assembly includes a sealing structure having thermally-responsive features. The thermally-responsive features deploy from or retract toward a surface of the sealing structure in response to a predetermined temperature change. The turbine component includes the metallic seal assembly. The method of regulating flow in turbo-machinery includes providing the metallic seal assembly and raising or retracting the thermally-responsive features in response to the predetermined temperature change.

Abstract: A cooling system for a turbine engine, as well as a methodology for controlling the cooling system, is described. A valve member is disposed between a cooling fluid passage and a wheel space of the turbine engine and operates to admit cooling fluid to the wheel space for cooling thereof. The valve assembly is responsive to a condition in the wheel space and varies the flow of additional cooling fluid to the wheel space based on that condition.

Abstract: A mechanical coolant pump for an internal combustion engine includes a main pump body configured to be stationary. A pump wheel is rotatably supported by the main pump body. The pump wheel comprises a central axial inlet opening. The pump wheel is configured to pump a coolant from the central axial inlet opening radially outwardly. A valve disk configured to be axially shiftable is arranged in the pump wheel. An actuator is configured to actuate the valve disk so as to close the central axial inlet opening in a closed position of the valve disk.

Abstract: An electric device has a casing with an air-inlet and an air-outlet, a main unit disposed inside the casing, a first temperature sensor for detecting the temperature inside the casing, a second temperature sensor for detecting the temperature outside the casing, an electric fan, and a control unit. The control unit rotates the electric fan at the time of the low-temperature startup such that the temperature detected by the first temperature sensor is lower than a preset first threshold value, while the temperature detected by the second temperature sensor is higher than the temperature detected by the first temperature sensor.