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 pressure sensor measures an organic Rankine cycle (ORC) working fluid pressure in front of a radial inflow turbine, while a temperature sensor measures an ORC working fluid temperature in front of the radial inflow turbine. A controller responsive to algorithmic software determines a superheated temperature of the working fluid in front of the radial inflow turbine based on the measured working fluid pressure and the measured working fluid temperature. The controller then manipulates the speed of a working fluid pump, the pitch of turbine variable inlet guide vanes when present, and combinations thereof, in response to the determined superheated temperature to maintain the superheated temperature of the ORC working fluid in front of the radial inflow turbine close to a predefined set point. The superheated temperature can thus be maintained in the absence of sensors other than pressure and temperature sensors.

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 power-producing device, such as a ram air turbine, includes a controller that is used to control operation of a turbine of the power-producing device. The controller uses an input based on an airspeed of the aircraft as part of a control mechanism in the controller for controlling the turbine. For example controller may be used to control backpressure of the turbine, for example by controlling the angle of doors of that are used to adjust backpressure of the turbine. The control mechanism may include a PID controller, with the gain of one or more of the values of the PID controller being a function of the airspeed of the aircraft. In addition the control mechanism may include manipulating a setpoint as a function of load on the power-producing device. The power-producing device may be part of a detachable pod that is installed on the aircraft.

Abstract: A steam turbine system including a steam turbine is provided. The steam turbine system includes a high-pressure side steam inlet device, a low-pressure side steam device, and a control device for controlling the steam turbine. An additional steam inlet device is also included arranged between the high-pressure side steam inlet device and the low-pressure side steam device. The control device control a supply of steam via the additional steam inlet device as a function of operating parameters detected at the steam turbine system.

Abstract: An apparatus for controlling the flow-rate of liquid of an electric pump and the temperature of the control and actuation electronics of a pumping device that carries the electric pump, the apparatus comprising, on a single monolithic segment of delivery duct, a flow-rate detector and a heat sink for a control and actuation unit, which is provided with temperature detection elements, the heat sink having a wet side that is exposed to the liquid and a dry side that is sealed from the liquid, with which the control and actuation unit is associated.

Abstract: A centrifugal compressor, the capacity of which can be increased with keeping the diameter of the impeller at minimum, is provided. The centrifugal compressor includes: a drive gear (11); a drive shaft (3) protruding from one side of the drive gear (11) in a central axis direction of the drive gear (11); a no. 1 driven pinion gear (12) configured for rotation of the drive gear (11) to be transmitted thereto; a no. 1 driven pinion shaft (5) protruding from both sides of the no. 1 driven pinion gear (12) in a central axis direction of the no. 1 driven pinion gear (12); and a couple of first stage compressor sections (7a, 7b), each of which is provided in each end of the no. 1 driven pinion shaft (5) and is configured to compress fluid by rotation of the no. 1 driven pinion shaft (5).

Abstract: Method for individuating the pumping conditions of the centrifugal blowers according to thermo-dynamic conditions (pressure and temperature) and to the gas composition in inlet, comprising the steps of: acquisition of the suction pressure, the suction temperature, the delivery pressure, the delivery temperature, the flow rate, the revolution number and the chemical composition of the gas mixture; calculation of the reduced conditions of the processed gaseous mixture by means of mixing equations; solution of the state equation of the real gases for the calculation of the thermo not dynamic properties of the gas mixture in the current conditions; acquisition of the performance non-dimensional curves of the blower, which express the value of the working coefficient of the blower and of the plytropic yield of the blower; calculation of the blower performance curves on the basis of the non-dimensional curves and according to the blower inlet parameters; determination of the pumping points, individuated as maximum

Abstract: A compressor variable stator vane arrangement comprises at least one stage of variable stator vanes. A speed sensor measures the rotational speed of the compressor rotor. A pressure sensor measures the outlet pressure of the compressor. A second pressure sensor, a temperature sensor and a third pressure sensor measure the total inlet pressure, the temperature and the ambient pressure at the inlet of the gas turbine engine. A processor determines a target operating line as a function of ambient pressure and total inlet pressure. The target operating line is defined to ensure the gas turbine engine operates simultaneously at both the minimum required compressor speed and the minimum required compressor outlet pressure when commanded to idle to minimize idle thrust and fuel burn. The processor determines if the operating point of the compressor, defined in terms of corrected outlet pressure and corrected rotational speed of the compressor rotor is above or below the target operating line of the compressor.

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: 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: Certain embodiments of the disclosure may include systems, methods and apparatus for operating and validating a compressor. According to an example embodiment of the disclosure, a method is provided for validating compressor operation. The method can include receiving compressor operating parameter data from a plurality of sensors; and adjusting a portion of a variable flow area downstream of a compressor discharge to achieve a desired compressor pressure ratio.

Abstract: A gas turbine engine comprises a compressor, a combustor, a turbine, and an electronic engine control system. The compressor, combustor, and turbine are arranged in flow series. The electronic engine control system is configured to generate a real-time estimate of compressor stall margin from an engine model, and command engine actuators to correct for the difference between the real time estimate of compressor stall margin and a required stall margin.

Abstract: A pressure and temperature actuation system is provided having a high-temperature low-pressure zone, a low-temperature high-pressure zone, a boundary, a pressure actuated mechanism, and a temperature mechanism. A gas located in the high-temperature low-pressure zone has a greater gas temperature than the gas located in the low-temperature high-pressure zone. The gas located in the low-temperature high-pressure zone has a greater gas pressure than the gas located in the high-temperature low-pressure zone. The boundary separates the high-temperature low-pressure zone from the low-temperature high pressure zone. The pressure actuated mechanism is located within the boundary and is configured for opening at a specified gas pressure in either the high-temperature low-pressure zone or the low-temperature high-pressure zone.

Abstract: Embodiments of a system and method can modify the position of diffuser vanes to improve performance of a compressor device, e.g., a centrifugal compressor. These embodiments include a feedback loop to manage the position of the diffuser vanes relative to one or more operating characteristics of an actuator that imparts movement to the diffuser vanes. In one embodiment, the system and method measure the operating characteristic for the actuator with the diffuser vanes at a first position and a second position. The system can compare values for the operating characteristics, wherein changes in the operating characteristic can identify other positions for the diffuser vanes to reduce input power the actuator consumes to move and/or maintain the position of the diffuser vanes. This feature can correlate with optimal performance of the compressor device and with peak compressor efficiency within the entire operating envelope of the compressor device.

Abstract: A method for controlling an automatic stall-prevention of a rotation-speed-regulated centrifugal fan. A control automatics is controlled by an automation system of the process wherein, the control automatics stalling is detected from a function of the electric current, voltage and frequency going to the motor of the centrifugal fan.

Abstract: A turbocharger having a turbine with a wastegate, and a compressor including a compressor housing, a compressor wheel, and a wastegate actuator. The turbine wheel includes blades defining an inlet. The compressor housing has an inlet wall leading to the inlet, and a shroud wall surrounding the blades. The actuator includes a base that is integral with the inlet wall, and an electric motor that is attached to the base. The shroud wall forms a first port that is in direct fluid communication with the actuator chamber, and the inlet wall forms a second port that is in direct fluid communication with the actuator chamber. Air from the first port to passes through the actuator housing and out the second port. This airflow convectively cools the working components of the actuator, while the connection of the motor to the inlet wall conductively cools the motor.

Abstract: Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller.

Abstract: A turbine assembly for generating electricity from kinetic energy of a moving fluid flow. The turbine assembly includes an elongated casing defining a fluid channel through which the fluid flow is allowed to travel, as well as an inlet and an outlet for respectively receiving and releasing the fluid flow to and from the fluid channel. The assembly also includes a main rotor contained within the casing and intersecting the fluid channel, the main rotor being rotatably moveable with respect to the casing via a pivoting component. The main rotor has a closed-loop arrangement provided with a plurality of rotor vanes each defining a neighbouring closed-loop rotor passage, the main rotor being rotatably driven via the passage of fluid flow through its closed-loop arrangement, and the closed-loop arrangement being further configured for imparting a forced rotational movement to the fluid flow exiting from the main rotor.

Abstract: The present invention relates to a method and control system to control the speed of a centrifugal compressor operating within a vacuum pressure swing adsorption process to avoid an operation at which surge can occur and directly driven by an electric motor that is in turn controlled by a variable frequency drive. In accordance with present invention an optimal speed for operation of the compressor is determined at which the compressor will operate along a peak efficiency operating line of a compressor map thereof. This speed is adjusted by a feed back speed multiplier when the flow or other parameter referable to flow through the compressor is below a minimum and a feed forward multiplier during evacuation and evacuation with purge steps that multiplies the feed back multiplier to increase speed of the compressor and thereby avoid surge.

Abstract: The invention relates to an axial flow turbine and method of operating thereof. The turbine comprises a last stage of rotating blades located towards a downstream end of the turbine having a distal region at an end of the airfoil of the blades. A monitoring control system has at least one sensor in the distal region of at least one last stage blade for measuring at least one physical property of the airfoil and a control element that is capable of influencing at least one physical property of the distal region. The control system further includes a controller that adjusts the control element based on at least measured physical property so by controlling the at least one physical property.

Abstract: A system, method and apparatus for monitoring the performance of a gas turbine engine. A counter value indicative of the comparison between the engine condition and the threshold condition is adjusted. The aircraft operator is warned of an impending maintenance condition based on the counter value and determines an appropriate course of action.

Abstract: A method and control system can implement a transient exhaust pressure protection logic to avoid a turbine exhaust vacuum trip due to a short duration turbine exhaust pressure transient that may be caused by a large reduction in turbine flow coupled with a transient increase in exhaust pressure, which specifically occurs during full load rejections. When full load rejection conditions are sensed by power load unbalance and confirmed by secondary indications, normal alarm settings and trip settings for turbine exhaust pressure are blocked for a delay period while transient operating limits are in place.

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 system for monitoring a turbomachine is provided. The system includes a turbomachine component having a variable geometry, a first sensor disposed to sense a condition of the turbomachine component, a second sensor disposed to sense an operational condition of the turbomachine, the operational condition being associated with an operation of the turbomachine component and a controller operably coupled to the first and second sensors, the controller being configured to execute a turbomachine process in accordance with a result of sensing by the second sensor with respect to the operational condition regardless of whether the first sensor detects the condition.

Abstract: A system and method are provided for controlling the temperature of engine bleed air from a turbofan gas turbine engine. The system includes a fan air valve and a fan air valve controller. The fan air valve is adapted to receive a flow of fan air from a turbofan gas turbine engine intake fan. The fan air valve is coupled to receive valve position commands and is configured, in response to the valve position commands, to move to a valve position to thereby control the engine bleed air temperature. The fan air valve controller is configured to implement a linear quadratic regulator (LQR) control. The fan air valve controller is adapted to receive a plurality of sensor signals, each sensor signal representative of one or more system parameters, and is configured, in response to the sensor signals, to supply the valve position commands to the fan air valve.

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: An axial-flow turbine assembly that includes one or more features for enhancing the efficiency of the turbine's operation. In one embodiment, the turbine assembly includes a turbine rotor having blades that adjust their pitch angle in direct response to working fluid pressure on the blades themselves or other part(s) of the rotor. In other embodiments, the turbine assembly is deployable in an application, such as an oscillating water column system, in which the flow of working fluid varies over time, for example, as pressure driving the flow changes. In a first of these embodiments, the turbine assembly includes a valve that allows the pressure to build so that the flow is optimized for the turbine's operating parameters. In a second of these embodiments, one or more variable-admission nozzle and shutter assemblies are provided to control the flow through the turbine to optimize the flow relative to the turbine's operating parameters.

Abstract: A method for the variation of at least one blade row of a fluid-flow machine, in which, in dependence of the actual operating point, in addition to an aerodynamic speed, at least one further quantity pertinent to the position of the operating point in the family of characteristics of the fluid-flow machine is employed for control.

Abstract: The present invention generally relates to a system for preventing surges in turbine engines and/or rotating compressors. Furthermore, some embodiments comprise sensors for monitoring engine operating characteristics and detecting surge and pre-surge conditions. Some embodiments also include means for adjusting engine operation in response to sensor data. Still other embodiments relate to methods of preventing surges in turbine engines and/or rotating compressors.

Abstract: A system includes a compressor and a control system. The control system includes a processor and associated memory. The control system is configured to receive feedback comprising a thermodynamic characteristic or a mechanical characteristic of the compressor. Also, the control system is configured to generate an indication of a surge event or a stall event in the compressor based on the feedback.

Abstract: A gas turbine engine system includes a fan and a fan bypass passage downstream of the fan for conveying a bypass airflow from the fan. A nozzle associated with the fan bypass passage includes a plurality of different positions that influence the bypass air flow. One or more sensors near the fan produce a signal representative of a foreign object near the fan. A controller commands the nozzle to move to a desired one of the plurality of different positions in response to the signal from the sensor to change a pressure ratio across the fan to thereby reduce a mechanical stress on the fan.

Abstract: A method for preventing a surge event prior to a first surge event occurring in an engine system including a turbocharger and a diesel engine operable at a plurality of discrete speeds, the method comprising sensing an operating parameter of the engine system that determines a surge margin, determining whether a change in the sensed operating parameter may result in exceeding the surge margin, and controlling an operating input to the engine system to prevent the surge event from occurring.

Abstract: The present disclosure provides a tuning system for tuning the operation of a gas turbine. The system comprises operational turbine controls for controlling operational control elements of the turbine, including at least one of turbine fuel distribution or the fuel temperature. The system also has a tuning controller communicating with the turbine controls. The tuning controller is configured to tune the operation of the turbine in accordance with the following steps: receiving operational data about the turbine, providing a hierarchy of tuning issues, determining whether sensed operational data is within predetermined operational limits and producing one or more indicators. If the operational data is not within predetermined operational limits, the tuning controller will rank the one or more indicators to determine dominant tuning concern, and tune the operation of the turbine based on dominant tuning concern. Also provided herein are a method and computer readable medium for tuning.

Abstract: A slide ring seal for high circumferential velocities for sealing liquids with little or no electrical conductivity, such as low-salt feed water for feed water pumps including a pair of slide rings, one of which is rotationally fixed and the other of which rotates with a rotating component. The slide rings have interacting sliding surfaces which form a region loaded with the liquid to be sealed relative to a sealing gap. One ring is formed of material with satisfactory electrical conductivity and the other of low conductivity material. The seal is arranged in a dead-end circuit of a rotating component to be sealed and is connected to a cooling system. A metering device is provided in the circuit for introducing a substance as a function of a slide ring seal leak to maintain the electrical conductivity of the liquid between 3 and 500 ?S/cm.

Abstract: A method and apparatus for determining a fluid level and/or output flow during operation of a centrifugal pump, are provided, which may be used for production of gas and/or oil from a well, and include a vector feedback model to derive values of torque and speed from signals indicative of instantaneous current and voltage drawn by the pump motor, a pump model which derives values of the fluid flow rate and the head pressure for the pump from torque and speed inputs, a pumping system model that derives, from the estimated values of the pump operating parameters, an estimated value of fluid level and other pumping system parameters. Controllers responsive to the estimated values of the pumping system parameters control the pump to maintain fluid level at the pump input, near an optimum level, or within a safe operating range and/or output flow from the pump.

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 method of establishing a wheel space temperature alarm in a turbomachine includes calculating an expected wheel space temperature based on operating conditions, measuring an actual wheel space temperature, and signaling an over temperature condition if the actual wheel space temperature exceeds the expected wheel space temperature.

Abstract: The present invention relates to a method of controlling a compressor and an apparatus therefor, the method, comprising at least the steps of: (a) providing a compressor feed stream (10); (b) passing the compressor feed stream (10) to an inlet (48) of the compressor (50) to provide a compressed stream (60) at an outlet (52) of the compressor (50); (c) calculating one or more controlled variables (CO1, CO2) that are invariant to compressor inlet conditions of the compressor feed stream (10), said inlet conditions comprising at least the ratio of specific heats (Cp/Cv) of the compressor feed stream (10), said one or more controlled variables comprising a surge controlled variable (CO1) representing the surge characteristics of the compressor (50); (d) providing one or more set points (SP1, SP2), that are invariant to the compressor inlet conditions of the compressor feed stream (10), said inlet conditions comprising at least the ratio of specific heats (Cp/Cv) of the compressor feed stream (10), said one or mor

Abstract: A gas turbine engine assembly has combustion gases flowing through a gas flow path. The gas turbine engine assembly includes a stator assembly comprising a stator vane that extends into the gas flow path; and a turbine rotor assembly downstream of the stator assembly and comprising a turbine platform and a turbine rotor blade extending from the turbine platform into the mainstream combustion gases flow path. The turbine rotor blade includes a pressure side and a suction side opposing the pressure side that extend from a leading edge to a trailing edge. The combustion gases form horseshoe vortices at a formation area adjacent the leading edge of the turbine rotor blade, and the turbine rotor assembly further includes a first set of holes in the turbine platform for directing first jets into the formation area of the horseshoe vortices.

Abstract: An internal combustion engine includes a block defining a plurality of combustion cylinders, an intake manifold fluidly coupled with at least one combustion cylinder, and an exhaust manifold fluidly coupled with at least one combustion cylinder. An EGR valve may be fluidly coupled between the exhaust manifold and the intake manifold. A turbocharger includes a turbine fluidly coupled with the exhaust manifold, and a compressor fluidly coupled with the intake manifold. A microphone is positioned at the compressor inlet or the compressor outlet provides an output signal. An ECU is coupled with the microphone, and controls operation of an actuatable element of a VGT, an EGR valve, and/or an injected fuel quantity, to prevent surge of the compressor, dependent upon the output signal from the microphone.

Abstract: A lubrication system for a wind turbine having a control system, the lubrication system including a sump configured to collect a lubrication fluid, and at least one heating unit configured to heat the lubrication fluid based on at least one forecasted condition.

Abstract: A method for determining total pressure distribution across a fan entry plane of a fan situated within a fan casing provided with struts which are positioned upstream of the fan, with respect to the normal air flow direction through the fan.

Abstract: A control system for mitigating the effects of a wind turbine on a radar system is disclosed. The control system includes a sensor configured to detect an operating condition of the radar system; a processor configured to receive an operating condition of the wind turbine and determine a rotation modification sequence based on the operating condition of the radar system and the operating condition of the wind turbine; and a controller configured to apply the rotation modification sequence to the wind turbine. A method of mitigating the effects of a wind turbine on a radar system is also disclosed.

Abstract: A gas turbine compressor presents a first fixed stage having a plurality of first adjustable vanes and a further fixed stage, which has an inner ring extending about a first axis; an outer ring arranged about the inner ring and coaxial with the inner ring; and a plurality of second adjustable vanes, each of which extends along a second axis in an essentially radial direction with respect to the first axis between the inner ring and the outer ring; and it is adjustable about the corresponding second axis independently from the first adjustable vanes.

Abstract: The invention relates to a wind turbine and a method for operating the wind turbine planted in the floor of a body of water. The wind turbine includes a support structure and a rotor, which is arranged on the support structure. The rotor has a rotor blade. The wind turbine operates in a trundle mode in order to reduce the oscillations in the support structure created through mechanical impacts on the support structure.

Abstract: Systems and methods for controlling the clearance in a gas turbine are provided. A temperature of a shaft of the gas turbine may be determined, and a desired temperature of an inner turbine shell of the turbine may be determined based upon the temperature of the shaft. The desired temperature of the inner turbine shell may be associated with a turbine clearance at which the gas turbine may be ignited. The temperature of the inner turbine shell may be altered by controlling the temperature of a gas that is circulated within the inner turbine shell, and a determination may be made that the temperature of the inner turbine shell exceeds the desired temperature. The gas turbine may be ignited subsequent to the determination that the temperature of the inner turbine shell exceeds the desired temperature.

Abstract: In an exhaust-gas turbocharger for an internal combustion engine comprising an exhaust-gas turbine arranged in an exhaust strand of the internal combustion engine and a compressor arranged in an intake tract and connected to the exhaust gas turbine so as to be driven thereby, the compressor including a compressor wheel and a compressor housing surrounding the compressor wheel and having an inlet duct, a dynamic pressure probe is provided upstream of the compressor wheel in the inlet duct for measuring at least the total pressure in the air flow into the compressor.

Abstract: A server management system is provided. The server management system includes a plurality of motherboards, a baseboard, a bus, a first and a second sensor. The baseboard comprises a central control chip to generate a specific instruction. The bus is positioned on the baseboard. The motherboards are connected to the baseboard. Each of the motherboards includes a baseboard management controller (BMC) having an instruction-processing module used to receive the specific instruction through the bus and executes the specific instruction. The first sensor is connected to the central control chip and the second sensor is connected to the BMC. The instruction-processing module retrieves a first state of the first sensor from the central control chip to the BMC and retrieves a second state of the second sensor from the BMC to the central control chip according to the specific instruction.