Abstract: A method of operating a variable guide vane assembly of an aircraft engine, the variable guide vane assembly including guide vanes rotatable about respective spanwise axes and circumferentially distributed about a central axis, the method comprising: obtaining a target exit flow angle defined between a direction of a flow exiting the guide vanes and the central axis; predicting an exit flow angle as a function of at least a geometric angle, the exit flow angle defined between the direction of the flow exiting the guide vanes and the central axis, the geometric angle defined between the guide vanes and the central axis; and when a difference between the exit flow angle and the target exit flow angle is above a threshold, modulating the guide vanes to modify the geometric angle until the difference between the exit flow angle and the target exit flow angle is at or below the threshold.

Abstract: A method and apparatus for maintaining integrally bladed rotors (IBR) includes using first vibration data from a IBR vibration apparatus of a first IBR to determine a set of values for a corresponding set of inherent vibratory properties based on a reduced order model for an IBR type to which the first IBR belongs. Shape data indicating an initial shape of a surface of a first blade is used, with repair data that indicates a candidate repair to form a restored shape, to determine a change in a value of an inherent blade section vibratory property of the set of inherent vibratory properties. A condition of the first IBR is determined based at least in part on the change in the value of the inherent blade section vibratory property. The first IBR is maintained based on the condition.

Abstract: A turbofan gas turbine engine having a bypass duct, and a bypass airflow measurement system. The bypass airflow measurement system comprises: at least one acoustic transmitter configured to transmit an acoustic waveform across the bypass duct of the gas turbine engine though which a bypass airflow passes to at least one acoustic receiver; where the at least one acoustic transmitter and the at least one acoustic receiver are located on an axial plane that is substantially perpendicular to the bypass flow. A method of measuring bypass airflow properties of a turbofan gas turbine engine is also described.

Abstract: This invention regards a hydraulic turbine (1) to operate in pressure circuits, where there is a flow of a fluid, to control the flow and pressure downstream the installation point. Even so, said turbine (1) can generate power for itself based on the difference of pressure and flow, as the remaining power can be used in public power networks or isolated. Its application field comprises sanitation companies, beverage industries, paper and cellulose industries, petrochemical companies or any places, where it is needed to control the flow and pressure in supply networks.

Abstract: A variable diffuser includes a backing plate, a shroud, a first divider between the backing plate and the shroud, a first diffuser channel between the backing plate and the first divider, a second diffuser channel between the first divider and the shroud, the second diffuser channel, and a valve controlling flow through the second diffuser channel. The valve moves between a first position and a second position. The first diffuser channel includes a first channel inlet and a first outlet. The second diffuser channel includes a second channel inlet adjacent to the first channel inlet and a second outlet adjacent to the first outlet.

Abstract: A method determines a thrust force of an aircraft engine that is attached to an aircraft by a force transferring element having a strain gauge for determining its strain state and a temperature sensor for measuring a surface temperature of the force transferring element adjacent to the strain gauge. The method includes: determining the surface temperature; determining a strain of the force transferring element; determining the strain state of the force transferring element based on the determined strain and compensating for temperature effects by taking into account the surface temperature, the compensation of the temperature effects taking into account both static and transient influences; and calculating the thrust force of the aircraft engine from the determined strain state.

Abstract: A temperature prediction device includes an application voltage specifying unit which specifics a voltage value applied to an electromagnetic coil based on a distance from a distance detection unit provided in the electromagnetic coil to an output shaft, a coil current detection unit which detects a current value flowing when a voltage is applied to the electromagnetic coil on the basis of the voltage value specified by the application voltage specifying unit, and a coil temperature estimation unit which estimates a temperature of the electromagnetic coil on the basis of the voltage value specified by the application voltage specifying unit, the current value detected by the coil current detection unit, and a relational expression between the voltage value applied to the electromagnetic coil, the current value flowing when a voltage is applied to the electromagnet coil on the basis of the voltage value applied to the electromagnetic coil, and the temperature of the electromagnetic coil.

Abstract: A wet-gas centrifugal compressor is disclosed. The compressor comprises a compressor casing and at least one impeller arranged in the compressor casing for rotation around a rotation axis. A stationary diffuser is arranged in the compressor casing and extends around the impeller. The diffuser has a curved end portion with a radially inner curved wall and a radially outer curved wall. A plurality of dry-gas extraction holes is provided, ending at a plurality of respective inlet ports arranged around the rotation axis and on the inner curved wall of the curved end portion of the diffuser. Each dry-gas extraction hole extends from the respective inlet port towards the rotation axis and is inclined over a radial direction, such that each dry-gas extraction hole is oriented in a counter-flow direction with respect to a direction of the gas flow in the curved end portion of the diffuser.

Abstract: There is provided a steam turbine startup support system capable of easily selecting a proper startup transition pattern from various startup transition patterns. In a steam turbine startup support system of the embodiment, an economic efficiency evaluation device performs economic efficiency evaluation regarding the various startup transition patterns recorded in a startup transition pattern recording device based on parameters recorded in a parameter recording device and information relating to a rotor lifetime recorded in a rotor lifetime recording device. Besides, a screen display device displays a result of the economic efficiency evaluation performed by the economic efficiency evaluation device.

Abstract: An exhaust-gas turbocharger, preferably for a passenger vehicle, including a turbine having a turbine wheel and a turbine housing. A number of S?2 of channels are formed in the turbine housing and are intended for guiding the exhaust gas onto the turbine wheel. Each channel directs flow against the turbine wheel over the entire width of the latter, as seen in the axial direction, and over a segment, as seen in relation to the circumferential direction. The turbine wheel has a number of Z?10 turbine blades. The turbine blades are defined in the form of main blades and intermediate blades. The intermediate blades, at least at their hub-side ends, do not extend as far toward the turbine outlet, as seen in the axial direction, as the main blades.

Abstract: Methods and apparatus to determine airflow conditions at an inlet of an engine are disclosed herein. An example method disclosed herein includes providing a frame having an inner surface and an opening therethrough to define a passageway; and mounting laser sensors to the inner surface of the frame, the laser sensors to measure a characteristic of a fluid that is to flow through the passageway of the frame.

Abstract: An improvement to a turbocharger having a housing (10) with a slot (25) located along a mid-line of the housing (10) above the turbine wheel (29) and a tongue (15) defining the end of an initial inlet throat area (11) of the housing (10), the slot (25) permitting inlet exhaust gas which flows past the tongue (15) to flow into the turbine wheel (29), the improvement being a pivoting vane (50) aligned with the slot (25) and having an upstream end (55) located at a downstream end (57) of the tongue (15). When the vane (50) is in its fully closed position (60), the inlet exhaust gas is prevented from flowing into the slot (25) and, therefore, the turbine wheel (29), until the inlet exhaust gas passes the downstream end (57) of the vane (50). The vane (50) effectively extends the tongue (15) to define a revised inlet throat area (12). The A/R ratio of the housing (10) progressively varies as the vane (50) pivots between the fully opened (70) and fully closed (60) positions.

Abstract: A turbine and method of operating the same a turbine includes a housing having a volute, an inlet and an outlet an impeller rotatable coupled to the housing, a first shroud disposed within the housing comprising a plurality of nozzle vanes and a second shroud disposed within the housing adjacent to the first shroud so that a nozzle area is formed between the first shroud and the second shroud, said nozzle area having a variable width. The second shroud is movable relative to the first shroud to vary the width so that fluid flow from the inlet to the outlet is variable.

Abstract: An electric actuator for control of an engine includes an electric motor coupled to a drive shaft that extends to align a gear interface of the electric actuator with a variable geometry adjustment interface of the engine. A position feedback shaft extends coaxially with respect to the drive shaft. The position feedback shaft is coupled to an output shaft of the gear interface at a gear interface end of the position feedback shaft. A rotational position sensor is coupled to a motor end of the position feedback shaft proximate the electric motor. The drive shaft and the position feedback shaft are sized to position an output ring gear of the output shaft in contact with the variable geometry adjustment interface within a casing of the engine and to further position the electric motor and the rotational position sensor external to the casing of the engine.

Abstract: An exhaust-gas turbocharger (1) having a turbine housing (2) which has a turbine inlet (3) and a turbine outlet (4) and which connects a wastegate duct (5) between the turbine housing inlet (3) and the turbine housing outlet (4), which wastegate duct can be opened and closed via a shut-off element (6). The shut-off element is in the form of a piston (6) which is guided in a longitudinally displaceable manner in an interior space (14) of a guide (7), and the wastegate duct (5) opens into the interior space (14) transversely with respect to the longitudinal central line (L) of the guide (7).

Abstract: The invention relates to a method for operating a wind turbine comprising an aerodynamic rotor that has at least one rotor blade. Said method comprises the steps of operating the wind turbine at an operating point that depends on the wind speed, detecting an operating parameter of the operating point, comparing the detected operating parameter with a predetermined reference quantity, and heating the at least one rotor blade when the detected operating parameter exceeds a predetermined variation from the reference quantity, the operation of the wind turbine being continued.

Abstract: A fan motor drive device configured to drive a fan with a motor includes a position speed estimating calculator configured to calculate estimated values of a rotation angle and a rotation speed of the motor, a multiplier configured to calculate a control target value by multiplying the rotation speed calculated in the position speed estimating calculator and a flow coefficient, and a current vector controller configured to control a drive current of the motor by feedback control based on the control target value. A rotor magnetic flux intensity of the motor is calculated based on at least a drive current obtained by a current sensor and the rotation angle obtained from the position speed estimating calculator, and a control value used in driving the motor is changed by the rotor magnetic flux intensity thus calculated.

Abstract: A blocker door actuation system for use in an aircraft thrust reverser is provided. The blocker door actuation system may comprise a rack, a gear, a gear housing, a screw shaft, and a link. The blocker door actuation system may be mounted to a translating sleeve in an aircraft nacelle. In response to the thrust reverser being activated and the translating sleeve moving aft, the blocker door actuation system may move the blocker door from a stowed position to a deployed position in a fan air duct.

Abstract: A turbine device, including: a turbine housing including an inlet, a flow channel, an outlet, a middle partition, an arced partition; a turbine impeller; a gas outlet; and an exhaust manifold. The turbine impeller and the gas outlet are arranged inside the turbine housing. The exhaust manifold is connected to the inlet. The flow channel is arranged inside the turbine housing. The outlet is arranged on the flow channel close to the turbine impeller. The middle partition is disposed inside the flow channel and divides the flow channel into a left flow channel and a right flow channel. The arced partition is arranged in both the left and right flow channels. One end of the arced partition is in a rigid connection with the middle partition, and the other end of the arced partition is close to the outlet of the turbine housing.

Abstract: A Method that consists of changing power of the payload and moment of resistance on the shaft of the wind generator in proportion to current wind speeds, and reduce speed of an air flow at meeting with blades of the wind engine of proportionally angular speed of a rotor. Wind generator for realization of the above Method contains blades formed by crossing of sectors of cavity cylinders under sharp corners to a direction of an air flow, and the depth of a cavity formed by crossing of sectors, exceeds distance between their forward borders, the internal surface of a cavity is executed with high frictional properties, and the outside surface of blades is executed with the minimal frictional properties. Wind generator for realization of the above Method must contain at least two electric generators, mechanical transmission and an automatic control system. Electric generators can be used from automobile industry.

Abstract: The invention relates to a method for controlling a turbine which is characterized by a hidden state at each point in time of the control. The dynamic behavior of the turbine is modeled using a recurrent neural network comprising a recurrent hidden layer. The recurrent hidden layer is formed by vectors of neurons which describe the hidden state of the turbine at the points in time of the control. For each point in time, two vectors are connected chronologically to a first connection which bridges one point in time, and two vectors are additionally connected chronologically to a second connection which bridges at least two points in time. Short-term effects can be corrected by means of the first connections, and long-term effects can be corrected by means of the second connections. Emissions and occurring dynamics can be minimized in the turbine by means of the latter. The invention further relates to a control device and a turbine comprising such a control device.

Abstract: An electro-pneumatic actuator for a waste gate includes an electric actuator to impart linear motion to an actuator shaft, and a pneumatic chamber defining a passage extending therethrough, the actuator shaft extending through the passage, the pneumatic chamber being sealed with respect to the actuator shaft. A piston is disposed in the pneumatic chamber and arranged for movement in the pneumatic chamber, the piston being affixed to the actuator shaft such that the actuator shaft and the piston move together as a unit. There is a port into the pneumatic chamber for feeding a gas into the pneumatic chamber or exhausting the gas therefrom so as to exert a pressure force on the piston and thereby provide a pneumatic assist to the force exerted on the actuator shaft.

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: Disclosed is a turbo pump in which a pump impeller is connected to one end of a rotary shaft and a turbine is connected to the other end of the rotary shaft. The turbo pump is designed such that an equivalent region, between a turbine efficiency curve obtained on the basis of a conditional expression where the number of rotations of the rotary shaft is maintained constant regardless of a pump flow rate and a turbine efficiency curve of an actual machine, becomes an operation region.

Abstract: A centrifugal refrigerant compressor system includes an impeller connected to a shaft. A diffuser is arranged on a downstream side of the impeller and is configured to regulate refrigerant flow exiting the impeller. A magnetic bearing supports the shaft. A sensing element is configured to produce an output relating to a shaft condition. A controller is configured to receive the output and determine an undesired impeller operating condition based upon the shaft condition. The controller is configured to command the diffuser to a desired state in response to the undesired impeller operating condition.

Abstract: An example variable vane scheduling method includes adjusting variable vanes from a position based on a first schedule to a position based on a different, second schedule in response to a control feature. An example method of controlling flow through a compressor of a turbomachine includes moving variable vanes to positions that allow more flow into the compressor in response to bleed air being communicated away from the compressor.

Abstract: A rotary feedthrough for a compressed air supply system is provided between a stator and a rotor rotating relative to this stator. A compressed air channel disposed in the stator is connected to a compressed air line and leads into an annular chamber formed in the rotor, from which at least one working channel leading to a consumer proceeds. The stator is connected in the region of the rotary feedthrough to a control line. A moment of friction occurring in the region of the rotary feedthrough resulting in premature wear is reduced by providing a switchable non-return valve in the annular chamber. Blocking elements which extend within the annular chamber concentrically to the rotational axis of the rotor are moveable into an open position by an actuating element, which is displaced from the stator in the direction of the blocking elements.

Abstract: An aircraft propulsion power plant for use in an aircraft includes one or more core engines housed in an airframe of the aircraft, one or more secondary propulsion units, each of the one or more secondary propulsion units being removably attached to the airframe, and one or more power transmission means, each of the one or more power transmission means being configured to transmit mechanical power from the or each core engine to a corresponding one of the or each secondary propulsion unit when the or each secondary propulsion unit is attached to the airframe.

Abstract: Gas turbine inlet guide vane ice detection and control systems and methods that utilize active infra-red monitoring of inlet guide vanes, detection of ice formation on the guide vanes and elimination of the ice by altering properties of the gas turbine inlet intake airflow, such as by introducing compressed and/or heated air bled from the turbine. Ice has lower detectable emissivity intensity in the infra-red spectrum than ice-free inlet guide vane surfaces. Ice formation is inhibited by direct monitoring of inlet guide vane icing conditions, rather than by indirect empirical assumptions of ice formation based on atmospheric condition monitoring. Direct monitoring mitigates ice formation in real time without reliance on excessive use of gas turbine compressed or heated air bleed, which enhances turbine operational efficiency.

Abstract: It is provided in the present invention a method for synchronously inhibiting subcritical vibrations of magnetic levitation molecular pump rotor, by means of synchronously sampling signals of subcritical vibrations of the rotor generated after the rotor of the magnetic levitation molecular pump touches down so as to obtain the amplitude and the phase of subcritical vibrations of the rotor, based on which outputting a compensation force for inhibiting subcritical vibrations of the rotor. Through using the present method, it is achieved of accurate synchronous for signals of subcritical vibrations and fast inhibition for subcritical vibrations of the rotor.

Abstract: A method and system for power generation including a turboexpander with at least two expansion stages, the turboexpander being connected to a power generation unit, is provided. The system includes a controller configured to control (i) an angle of a first inlet guide vane provided at an inlet of a first expansion stage of the turboexpander for maintaining an inlet pressure of the first expansion stage in a predetermined range, and (ii) an angle of a second inlet guide vane provided at an inlet of a second expansion stage of the turboexpander. The controller is configured to determine a highest power from determined powers of the power generation unit and a corresponding angle of the second inlet guide vane and to adjust the angle of the second inlet guide vane independent of the angle of the first inlet guide vane to achieve the highest power.

Abstract: An improved variable geometry diffuser (VGD) mechanism for use with a centrifugal compressor. This VGD mechanism extends substantially completely into the diffuser gap so that the VGD mechanism may be used more fully to control other operational functions. The VGD mechanism may be used to minimize compressor backspin and associated transient loads during compressor shut down by preventing a reverse flow of refrigerant gas through the diffuser gap during compressor shutdown, which is prevented because the diffuser gap is substantially blocked by the full extension of the diffuser ring. During start-up, transient surge and stall also can be effectively eliminated as gas flow through the diffuser gap can be impeded as load and impeller speed increase, thereby alleviating the problems caused by startup loads at low speeds. The VGD mechanism can be used for capacity control as well so as to achieve more effective turndown at low loads.

Abstract: A control for a multi-shaft turbine engine system using electrical machines seeks optimal system performance while accommodating hard and soft component limits. To accommodate the component limits, the control may generate a number of possible operating point options reflecting potential trade-offs in performance, lifting, efficiency, or other objectives.

Abstract: Starter control valve failure prediction machines, systems, computer readable media, program products, and computer implemented methods to predict and trend starter control valve failures in gas turbine engines using a starter control valve health prognostic and to make predictions of starter control valve failures, are provided.

Abstract: A method for starting-up a wind turbine having a rotor with at least one rotor blade is provided. The method includes rotating the at least one rotor blade towards a main operating position using a pitch drive system including a pitch bearing supporting the at least one rotor blade, and a pitch-driving pinion meshing with the pitch bearing; and activating a pump to feed a lubricant to a lubrication pinion meshing with one of the pitch bearing and the pitch-driving pinion before the at least one rotor blade reaches the main operating position so that the lubricant is mainly transferred to a load portion of the pitch bearing and/or a load portion of the pitch-driving pinion. Further, a control assembly for use with the wind turbine is provided.

Abstract: The system for mitigating an overspeeding condition of a turbine engine can include a sensor for measuring an actual speed of a gas generator turbine of the turbine engine and a processor for deriving a delta, the delta being a comparison between the actual speed of the gas generator turbine and a predicted gas generator turbine speed. The system is configured for detecting the overspeeding condition when delta is higher than a predetermined threshold. A method of detecting an overspeeding condition during operation of a turbine engine can include measuring an actual speed of a gas generator turbine, then evaluating a delta between the actual speed of the gas generator turbine and a predicted speed of the gas generator turbine, then comparing the delta to a threshold value.

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: A heat-dissipation system includes a shell, a fan, a latch, and a micro-switch. The fan includes a first connector and a second connector. The first connector includes a number of signal pins, a zero line pin, and a live line pin. The signal pins are used to transmit signals between a motherboard and the fan. The zero line pin and the live line pin are connected to a power supply. The zero line pin of the first connector is connected to a zero line pin of the second connector. When the latch is engaged with the shell, the micro-switch is turned on and the power supply supplies power to the second connector through the micro-switch and the zero and live line pins of the first connector. When the latch is not engaged with the shell, the micro-switch is turned off and the power supply is disconnected from the second connector.

Abstract: The invention relates to a method for primary adjustment of a hydroelectric power plant comprising a dual adjustment turbine, at least one first actuator, and at least one second actuator, wherein the first and second actuators are reset depending upon an actual value of a network frequency of an electrical network which receives the generated electrical power for influencing the turbine output in order to achieve a target value of the network frequency. The invention is characterised in that the first actuators are only operated in predefined actuating steps, and then an adjustment to the target value of the network frequency is performed by resetting the second actuators.

Abstract: A turbocharger system comprises: a gas input for receiving exhaust gases from an engine; a first turbocharger comprising a first compressor driven by a first turbine, arranged to be driven by received exhaust gases and providing a compressed air output defining a boost pressure a second turbocharger, arranged to be driven by exhaust gases passing through the first turbocharger or exhaust gases received at the gas input and being coupled to an electrical generator operative to provide electrical power, the first turbine not being coupled to an electrical generator; and a controller. A diversion mechanism may be configured to affect the flow of exhaust gases between the gas input and the first turbocharger. The controller may be configured to adjust the operation of the electrical generator independently from the operating mode of the associated engine, to affect the boost pressure.

Abstract: A system configured to precisely control and/or modulate purge flow in a power plant system (e.g., a gas turbine) during operation is disclosed. In one embodiment, a system includes: at least one computing device adapted to control a purge flow in a gas turbine by performing actions comprising: obtaining operational data from the gas turbine; determining an inferred gas path pressure value for the gas turbine; determining an allowable purge flow for the gas turbine as a function of the operational data and the inferred gas path pressure value; and adjusting the purge flow based upon the allowable purge flow determination.

Abstract: A method of controlling the angular orientation of at least one variable fluidfoil. The method includes the steps of receiving detected fluidfoil angular orientation data for the at least one fluidfoil; receiving a fluidfoil angular orientation demand; generating a modified angular orientation demand by modifying the fluidfoil angular orientation demand before it is used to control adjustment of the at least one fluidfoil, the modification being performed using the detected fluidfoil angular orientation data; and outputting the modified demand and controlling the at least one fluidfoil angular orientation in accordance with the modified demand.

Abstract: A number-of-compressors controlling system which has a simple configuration and can produce compressed air by immediately following the load used of the compressed air is provided. The number-of-compressors controlling system has a plurality of compressors (2), a receiver tank (3) in which compressed air is supplied from these compressors (2) and is fed to a compressed air utilization device, a pressure sensor (4) provided on the receiver tank (3), and a number-of-compressors controller (5) which changes the number of compressors being operated based on the detected pressure of the pressure sensor (4). A number-of-compressors decreasing pressure as a threshold value whether or not the number of compressors being operated is decreased by the number-of-compressors controller (5) is set to be lower as the number of compressors being operated is larger.

Abstract: A capacitive sensor device and a method of manufacture are provided. The capacitive sensor device includes at least one sensor tip that includes an electrode positioned at a first end of the sensor tip, and a stem member coupled to the electrode and extending toward a second end of the sensor tip. The device also includes a coaxial cable including a center conductor, the center conductor coupled to the sensor tip at the second end, and an insulation layer supporting the sensor tip between the first and second ends. The insulation layer includes a metallization on a portion surrounding the second end of the sensor tip. The device further includes a casing surrounding a portion of the coaxial cable, the metallization, and the coupling of the center conductor and the sensor tip, wherein a braze joint is formed between the casing and the metallization to form a hollow, hermetic cavity.

Abstract: The invention relates to a centrifugal pump assembly with an electric drive motor and with a control device having a frequency converter, for the control of the rotational speed of the drive motor, wherein the control device is designed in a manner such that in at least one control region, a field weakening is produced in the drive motor, by way of which the rotational speed of the drive motor is increased.

Abstract: A kinetic hydropower generation system has a turbine and a generator coupled to the turbine. An underwater intake nozzle assembly is fluidly coupled to the turbine. For one embodiment, an underwater tower nozzle may be fluidly coupled between the turbine and the underwater intake nozzle assembly. The underwater intake nozzle assembly may include a collector and a converging nozzle.

Abstract: A gas turbine engine section has a rotor carrying a plurality of blades. The blades have airfoils which define a radially outer tip. A blade outer air seal is positioned radially outwardly of the tips of the blades. The blade outer air seal is provided by at least a plurality of circumferentially spaced segments, which slide circumferentially relative to each other to adjust an inner diameter of an inner surface of the blade outer air seal segments. An actuator actuates the blade outer air seal segments to slide towards each other to control a clearance between the inner periphery of the blade outer air seal segments and the radially outer tip of the blade airfoils. A gas turbine engine is also disclosed.

Abstract: A hydraulic engine which may generate rotational power by using environmentally friendly electric energy and have improved performance and a long life span, and more particularly, environmentally friendly hydraulic power units that that may extrude a working fluid to realize an engine and has a long life span. The hydraulic engine includes: a housing; a rotor that is rotatably supported in the housing and allows rotor blades to be disposed therearound; a plurality of hydraulic power units that are disposed around the rotor to be spaced apart from one another; and an output shaft that rotates as the rotor rotates and the output shaft protrudes beyond the housing, wherein a fluid extruded from hydraulic power units pressurizes the rotor blades and generates a rotational force of the output shaft.

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: The invention relates to a water turbine or water pump or other hydraulic machine that comprises a stationary and a revolving component. The invention also comprises a sealing gap that is disposed between the stationary and revolving components, which is sealed by a labyrinth seal and through which a leakage flow for cooling or lubricating the seal will flow during operation of the hydraulic machine. The invention also provides a connection on the sealing gap for its evacuation.