Abstract: In the operation of a refueling screw compressor, when load conditions constantly fluctuate or when the rotation speed control of a cooling fan is performed, it is difficult to accurately perform a diagnosis predicted from measurement results of devices inside the compressor, so a diagnostic mode stably creates an operating condition under which an accurate diagnosis can be performed. In the refueling screw compressor, a discharge electric valve is provided downstream of an air cooler, and an air release electric valve and a dedicated orifice are provided to connect an oil separator inner space and a suction throttle valve space. In the diagnostic mode, the discharge electric valve is closed, the air release electric valve is opened, and while an upstream pressure of the oil separator is maintained at a specified pressure, a rotation speed control operation of a compressor body and the diagnosis of internal devices are performed.

Abstract: The purpose of the present invention is to provide: fuel cell system that can further stabilize an operation of the system; and control method thereof. Fuel cell system comprises: fuel cell; a turbocharger; oxidizing gas supply line that supplies, to cathode, oxidizing gas compressed by a compressor; a heat exchanger that heats the oxidizing gas of the oxidizing gas supply line by means of exhaust gas discharged from a turbine, and flows the exhaust gas to combustion exhaust gas line; bypass lines each having one end connected to the upstream side of the heat exchanger in the oxidizing gas supply line and bypassing the oxidizing gas; flow rate regulating valves provided in the bypass lines; and a control unit that controls the flow rate regulating valves on the basis of the ambient air temperature, and controls the bypass flow rate of the oxidizing gas.

Abstract: A chiller assembly is provided. The chiller assembly includes a compressor (102), a condenser (106), an expansion device and an evaporator (108) connected in a closed refrigerant circuit. The chiller assembly further includes a motor (104) connected to the compressor to power the compressor, and a variable speed drive (110) connected to the motor to power the motor. The variable speed drive is operable to provide a variable voltage to the motor and a variable frequency to power the motor. The variable speed drive includes multiple sensors and an input current estimator that determines an estimated RMS input current based on sensor data received from the sensors. The chiller assembly further includes a control panel to control operation of the variable speed drive.

Abstract: A turbine wheel consists of a first shroud component and a second bladed disc component. The shroud component comprises a shroud structure, a hub structure and a spoke formed integrally therewith and extending between the shroud structure and the hub structure. The bladed disc component comprises a hub member having inner and outer rims, turbine blades disposed on the outer rim, and at least one receiving zone for receiving the spoke, said at least one receiving zone extending radially between the inner and outer rims. The shroud component and the bladed disc component are connected and thus provide the turbine wheel with a shrouded portion. A shrouded turbine wheel can therefore be conveniently assembled starting from at least two components. Further, these components have simplified geometries for easy manufacture, for example using a casting technique, while the overall mechanical performance of the turbine is preserved or improved.

Abstract: The invention relates to an air conditioning system for an aircraft comprising a turbine engine comprising at least one radial turbine and a compressor, said radial turbine extending along a central axis (10) and comprising a wheel (20) equipped with vanes (21) mounted so as to be able to rotate about said central axis (10), a nozzle (30) arranged at the periphery of said wheel (20) comprising a plurality of variable-pitch blades (31) arranged around said central axis (10), and a volute (12) comprising an air inlet (12a) and an air outlet (12b) opening onto said plurality of variable-pitch blades (31), characterized in that said variable-pitch blades (31) are arranged around said central axis (10) between two nozzle casing walls (11a, 11b) delimiting an air passage section of said nozzle between them, each variable-pitch blade (31) further comprising means for axial displacement of the blade between the two casing walls (11a, 11b).

Abstract: A control system is provided that can identify the occurrence of a single surge cycle in centrifugal compressor using various methods and devices. Once the occurrence of a single surge cycle is identified, the control system can take remedial action to respond to the surge cycle, such as by adjusting the position of a variable geometry diffuser, and restore the centrifugal compressor to stable operation.

Abstract: A twin-vaned nozzle ring for a turbine nozzle of a turbocharger nozzle ring is made by assembling the nozzle ring from three separately formed parts. A center part includes a first ring of circumferentially spaced first vanes and a second ring of circumferentially spaced second vanes, the first and second rings being axially spaced and integrally joined to each other. The first vanes are circumferentially offset from the second vanes, and exits from the first vane passages are radially aligned with and circumferentially interleaved with exits from the second vane passages. First and second side walls are provided as separate parts. Finally, the first side wall is joined to a distal or outer face of the first ring, and the second side wall is joined to a distal face of the second ring to complete the assembly.

Abstract: A compressor case for a gas turbine engine includes an annular body that extends circumferentially around a center axis and extends axially along the center axis. A first bleed manifold is formed on an outer surface of the annular body and encloses a first plenum. A second bleed manifold is formed on the outer surface of the annular body and is axially aft of the first bleed manifold. The second bleed manifold encloses a second plenum. A bleed inlet extends through the annular body and into the first bleed manifold. Cooling passages are formed in the annular body, and each of the cooling passages extends from the first plenum to the second plenum and fluidically connects the first plenum to the second plenum.

Abstract: A first actuator moves a compressor rotor and compressor blades along a rotational axis of the compressor rotor. A turbine rotor includes a plurality of turbine blades each extending radially outwardly from the turbine rotor to an outer tip. A turbine housing surrounds each of the turbine blade tips. The turbine housing has an inner surface, and a turbine tip clearance is defined between each of the turbine blade tips and the inner surface of the turbine housing. A second actuator moves the turbine rotor and the turbine blades along a rotational axis of the turbine rotor. A control controls the first actuator of the compressor rotor, and the second actuator of the turbine rotor to control the compressor tip clearance and the turbine tip clearance.

Abstract: Disclosed herein is an electric battery charger system and method which may be used with electrical equipment such as an electric vehicle to improve the efficiency of operation. The charger system includes a DC motor operated by a car battery or other power source and a generator (e.g., turbine generator) to power a traction battery of the electric vehicle for recharging. In one embodiment, the charger system may have a single shaft running between the motor and generator with blades on the shaft to cool the operation of the charger system. In another embodiment, a coupler assembly is located between the motor and generator to drive the shaft of the generator. In another embodiment, the charger system may include fans having interlocking, non-contact blades which are kept apart by magnets located on the blades. A first fan is turned by the DC motor and is configured to drive a second fan which turns a shaft of the generator to create power for charging the traction battery.

Abstract: In a gas turbine system which includes a compressor for sucking and compressing air and an air supplying means for supplying the compressed air from the compressor to a combustor and a turbine and which drives a power generator through rotation of the turbine, a control apparatus includes a sensing unit and a compressed air control unit. The sensing unit measures a turbine inlet temperature indicating a temperature of combustion gas introduced into the turbine and measures an exhaust gas temperature indicating a temperature of exhaust gas discharged from the turbine. The compressed air control unit control the air supplying means to adjust the amount of compressed air supplied to the turbine, based on the measured turbine inlet temperature and the measured exhaust gas temperature. The control apparatus allows the combustor to completely combust fuel even in a low load state, thereby reducing the amount of harmful exhaust gas discharged to the atmosphere.

Abstract: A control method and apparatus for startup of turbocompressors to avoid overpowering a driver of the turbocompressor. In a first embodiment, the control system monitors input signals from transmitters of various control inputs. When the input signals exceed threshold values, the control system begins to close the antisurge valve. In a second embodiment, the antisurge valve begins to close after a predetermined time measured from the time startup is initiated. In both embodiments, the antisurge valve continues to ramp closed until the compressor has reached its operating zone, or until the compressor's operating point reaches a surge control line, at which point the antisurge valve is manipulated to keep the compressor from surging.

Abstract: Controller, control actuator and bleed valve including a first chamber for the circulation of a discharge air stream when the valve is open and preventing it when the valve is closed, an inner housing, in which a mobile blocking unit is moved between a position for opening and a position for closing the valve, this unit delimiting, in the inner housing, two chambers, the second chamber including a mechanism for returning the blocking unit to the open position, and the third chamber, being used to be in fluidic connection with the control actuator in order to actuate the blocking unit against the return mechanism, the three chambers being isolated in a sealed manner from one another by way of the blocking unit. The device includes a regulation valve.

Abstract: A method for controlling an inlet-adjustment mechanism in an air inlet for a compressor so as to switch the mechanism in a binary fashion between open and closed positions for adjusting a flow area of the inlet. The method includes identifying a threshold line on a compressor map of pressure ratio versus corrected flow rate for the compressor, at which the inlet-adjustment mechanism is switched from one of its positions to the other. A fixed switch band straddling the threshold line can be used for determining when to initiate the switch of positions so as to time the switch to coincide with the operating point reaching the threshold line. Alternatively, a time to reach the threshold line can be instantaneously computed and compared to the actuator/mechanism response time.

Abstract: The present invention relates to a housing for a gas turbine compressor, having an operating duct for taking up several rows of rotating blades arranged one behind the other axially, wherein a wall of the operating duct has a first air bleed, wherein the housing has a cooling passage for cooling said operating duct wall by conveying air from the first air bleed to a first outlet passage for supplying at least one first bleed air consumer, wherein the first outlet passage is arranged downstream of the first air bleed, and wherein the operating duct wall has a second air bleed downstream of the first air bleed, and the housing has a discharge passage from said second air bleed to a second outlet passage for supplying at least one bleed air consumer.

Abstract: Systems and methods for compressor unloading detection are provided and include a compressor having a compression mechanism. A controller determines a predicted discharge temperature of the compressor, receives an actual discharge temperature of the compressor, and compares the predicted discharge temperature with the actual discharge temperature. The controller also compares a speed of the compressor with a speed threshold and detects unloading of the compression mechanism based on the comparison of the predicted discharge temperature with the actual discharge temperature and based on the comparison of the speed of the compressor with the speed threshold. The controller performs at least one of generating an alert and a remediating action in response to detecting the unloading of the compression mechanism.

Abstract: A centrifugal compressor for a chiller includes a casing, an inlet guide vane, an impeller downstream of the inlet guide vane, a motor and a diffuser. The casing has inlet and outlet portions with the inlet guide vane disposed in the inlet portion. The impeller is rotatable about a rotation axis defining an axial direction. A liquid injection passage is provided to inject liquid refrigerant into an area between the impeller and the diffuser. The motor rotates the impeller. The diffuser is disposed in the outlet portion downstream from the impeller with an outlet port of the liquid injection passage being disposed between the impeller and the diffuser. A controller is programmed to control an amount of the liquid refrigerant injected into the area between the impeller and the diffuser.

Abstract: A method of operating a gas turbine engine includes measuring an exhaust gas temperature of the gas turbine engine. A first stage turbine nozzle assembly of the gas turbine engine is adjusted to a first position. A firing temperature of the gas turbine engine is determined based on the exhaust gas temperature. The firing temperature is compared to a threshold value and a difference value is determined therefrom. If the difference value exceeds a threshold value, the first stage turbine nozzle assembly is adjusted to a second position such that the firing temperature is substantially equal to the threshold value.

Abstract: The occurrence of corrosion on the inner surfaces of pipes is to be minimized in a cooling air system of a gas turbine. Specifically, this gas turbine power generation equipment has: a gas turbine including a turbine connected to a generator, a combustor that supplies combustion gas to the turbine, and a compressor that supplies compressed air to the combustor; a cooling air system that supplies compressed air bled from the compressor to the turbine, the cooling air system being connected at a first end side to an intermediate stage or an outlet of the compressor and connected at a second end side to the turbine; and a drying air system that supplies drying air into the cooling air system when the gas turbine is stopped, the drying air system being connected to the cooling air system.

Abstract: In some aspects, a steam turbine system includes a high-pressure turbine section; a low-pressure turbine section; a high-pressure control valve operable to provide an adjustable flow of steam into the high-pressure turbine section; a low-pressure control valve operable to provide an adjustable flow of steam into the low-pressure turbine section; a controller associated with the high-pressure control valve and the low-pressure control valve. The controller is operable to: receive measurements of three or more different operating points of the steam turbine system, the measurements of each of the three or more different operating points including a position of the high-pressure control valve, a position of the low-pressure control valve, and two of process variables of the steam turbine system; calculate coefficients of a steam performance map of the steam turbine system based on the measurements; and generate the steam performance map based on the coefficients.

Abstract: A method for performing maintenance on an engine includes: providing an engine maintenance system including a database system having a database and a database management device: providing a first performance parameter stored in the database and characterizes an engine performance before an engine maintenance procedure; providing a maintenance parameter stored in the database and characterizes a scope of a maintenance measure performed on an engine during an engine maintenance procedure; providing a second performance parameter stored in the database and characterizes the engine performance after the engine maintenance procedure; determining, using the database management device, a functional relationship between the maintenance parameter and the contribution of the maintenance parameter to a difference between the first performance parameter and the second performance parameter; outputting the functional relationship via the engine maintenance system; and performing maintenance on the engine taking the functi

Abstract: Systems and methods are provided for a turbocharger compressor, where the system may comprise: an actuatable annular disk comprising choke slots therein; an outer annular disk comprising choke slots therein; and an actuator to rotate the actuatable annular disk relative to the outer annular disk to vary alignment of the choke slots of the actuatable annular disk and the outer annular disk. The actuator may be controlled by an engine controller responsive to operating conditions of the compressor and actuated to align choke slots. Alignment of the choke slots allows air to be drawn into the impeller effectively expanding the compressor flow capacity to prevent compressor choke.

Abstract: A computerized control is used in controlling a choke when drilling a wellbore with a drilling system. The computerized control obtains a measured value of a parameter in the drilling system and controls the parameter in the drilling system using the choke. The computerized control obtains indications of an error between a set point of the parameter and the measured value of the parameter in the drilling system, a flow coefficient character of the choke, and a current position of the choke. Based on these indications, the computerized control then determines a position adjustment for the choke and adjusting the parameter in the drilling system by applying the position adjustment to the choke.

Abstract: Disclosed herein is a method for producing cooling comprising evaporating a liquid refrigerant comprising (a) E-CF3CH?CHF and (b) at least one tetrafluoroethane of the formula C2H2F4; provided that the weight ratio of E-CF3CH?CHF to the total amount of E-CF3CH?CHF and C2H2F4 is from about 0.05 to 0.99, in an evaporator, thereby producing a refrigerant vapor. Also disclosed herein is a method for replacing HCFC-124 or HFC-134a refrigerant in a chiller designed for said refrigerant comprising providing a replacement refrigerant composition comprising (a) E-CF3CH?CHF and (b) at least one tetrafluoroethane of the formula C2H2F4; provided that the weight ratio of E-CF3CH?CHF to the total amount of E-CF3CH?CHF and C2H2F4 is from about 0.05 to 0.99.

Abstract: An internal combustion engine having intake and exhaust manifolds, a turbocharger with a compressor, and at least one of: an exhaust gas recirculation (EGR) valve and a variable geometry turbine (VGT). The system further includes a control computer configured to determine at least one of torque demand, pressure across the compressor, and pressure gradient ratio between the exhaust manifold and the intake manifold relative to one of exhaust manifold pressure, intake manifold pressure, and 1. The control computer performs at least one of: closing the EGR valve in response to the determined at least one of torque demand, pressure across the compressor, and pressure gradient ratio, and lessening restriction provided by the variable geometry turbine responsive to the determined at least one of torque demand, pressure across the compressor, and pressure gradient between the exhaust manifold and the intake manifold.

Abstract: A method is provided for operating a gas turbine plant including a compressor, which on an inlet side inducts intake air and compresses it, providing compressor exit air on a discharge side. The plant also includes a combustion chamber where fuel is combusted, using compressor exit air, forming a hot gas; and a turbine, where the hot gas is expanded, performing work. The method includes extracting compressed air from the compressor, directing it as cooling air flow into the combustion chamber and/or into the turbine for cooling thermally loaded components. The method also includes controlling at least one cooling air flow, for achieving specific operating targets, using a control element depending on an operating target. A gas turbine plant is also provided having at least one control element for cooling air flow control, and a gas turbine controller which controls the gas turbine plant based on selectable control parameter sets.

Abstract: A method of detecting that an aircraft is flying in icing conditions. A processor unit determines a real power developed by the turboshaft engine and a theoretical power that the engine can develop in theory, the theoretical power being determined using a theoretical model supplying a power as a function at least of a speed of rotation of a gas generator of the engine. The processor unit determines a difference between the real power and the theoretical power. The processor unit generates a warning to indicate the presence of icing conditions when the power difference is greater than a predetermined power threshold for a length of time longer than a time threshold, and when a temperature outside the aircraft lies between a low temperature threshold and a high temperature threshold.

Abstract: A compressor control method includes providing variable aerodynamic sizing of fluid flow through a compressor at multiple operating points of the compressor. A head is determined for an operating point, based on a process input at that operating point. Further, for that operating point, a control pressure number is determined as a function aerodynamic flow sizing at that operating point. The control pressure number is determined a function of the head divided by the square of a tip speed of the impeller of the compressor. An operating speed setpoint is determined based on the determined head and control pressure number.

Abstract: A wind turbine condition monitoring system and method are disclosed where the wind turbines include a tower, a gearbox coupled to the tower, and turbine blades coupled to the gearbox. The monitoring system includes blade sensors coupled to the blades, a hub node coupled to the gearbox and a controller. The controller is in communication with the hub node and blade sensors, and determines blade positions based on blade sensor readings. The blade sensors and hub node can include multi-axis accelerometers. The controller can wirelessly communicate with the blade sensors directly or through the hub node. Using position information, shadowing areas with obstructed communication can be avoided, node separation can be accounted for to reduce power requirements and/or interference from multiple transmitters can be avoided during node communications.

Abstract: Embodiments of the invention provide a condition-based maintenance tool that may be used to monitor, configure, and in some cases correct, problems experienced by a compressor in a pipeline system. The condition-based maintenance tool may evaluate data retrieved from a compressor status database to identify overconsumption events. In response, the maintenance tool may generate maintenance alarms, initiate work orders, and/or provide recommendations for action to an operator.

Abstract: A device comprising a combustion toroid for receiving combustion-induced centrifugal forces therein to continuously combust fluids located therein and an outlet for exhaust from said combustion toroid.

Abstract: A product for balancing a shaft and wheel assembly of a turbocharger is disclosed. A fixture may have an exterior surface, with an aperture extending through the exterior surface. A first conduit may extend through the fixture and may exit from the first conduit through the exterior surface. A second conduit may extend through the fixture and may exit into the aperture. A pressurized gas source may be connected to the first and second conduits. An electromagnet may be positioned in the fixture and may extend around the aperture. The pressurized gas source may be operated to apply pressurized gas through the first and second conduits and the electromagnet may be operated to apply a magnetic field to the aperture.

Abstract: Systems and methods of estimating an efficiency of a section of a steam turbine are disclosed. The systems and methods include determining a set of measurement data obtained directly from a set of sensors on the steam turbine, determining a set of derived data relating to measurements that cannot be obtained directly from the set of sensors, and estimating the efficiency of the section using the set of measurement data and the set of derived data. The systems and methods disclosed use physics-based models combined with nonlinear filtering techniques to estimate steam turbines' efficiencies when physical sensors are not available. These models capture the behavior of different components of the power plant, including all steam turbine sections, admission and crossover pipes, flow junctions, admission and control valves.

Abstract: A system includes a controller including a processor configured to execute a program stored in a memory of the controller to generate and transmit a first output comprising a total flow demand value to a plurality of valves communicatively coupled to the controller. Each of the plurality of valves is configured to receive a respective portion of the total flow demand value. The processor is configured to receive an input indicative of a decoupling of a first valve of the plurality of valves and to generate a second output based at least in part on the first output and a first operational characteristic of the first valve. The second output is configured to vary a second operational characteristic of a second valve of the plurality of valves to maintain the total flow demand value.

Abstract: The method for operating a power plant including a gas turbine and a steam power generation system that activate, or drive, at least one electric generator, wherein the gas turbine produces flue gases that are supplied into a boiler of the steam power generation system. In a steady operation, the gas turbine generates a first output power greater than zero, the steam turbine generates a second output power greater than zero, and a total generated power is a sum of the first and second output powers and is substantially equal to a house load of the power plant.

Abstract: A compressor has a hub-side wall of a hub-side wall plate, a shroud-side wall that faces the hub-side wall and forms a diffuser path between the shroud-side wall and the hub-side wall, vanes that protrude from the hub-side wall plate into the diffuser path, and an actuator capable of changing the distance between the vanes and the shroud-side wall in accordance with a flow rate of air in the diffuser path. Adjacent ones of the adjacent vanes do not overlap with each other when viewed from a center axis of the compressor. When the actuator maximizes the distance between the vanes and the shroud-side wall, the distance between the vanes and the shroud-side wall is smaller than the distance between the hub-side wall and areas of the shroud-side wall that face the vanes.

Abstract: A compressor airfoil tip clearance optimization system for reducing a gap between a tip of a compressor airfoil and a radially adjacent component of a turbine engine is disclosed. The turbine engine may include ID and OD flowpath boundaries configured to minimize compressor airfoil tip clearances during turbine engine operation in cooperation with one or more clearance reduction systems that are configured to move the rotor assembly axially to reduce tip clearance. The configurations of the ID and OD flowpath boundaries enhance the effectiveness of the axial movement of the rotor assembly, which includes movement of the ID flowpath boundary. During operation of the turbine engine, the rotor assembly may be moved axially to increase the efficiency of the turbine engine.

Abstract: A compressor tip clearance management system includes a compressor section having a low pressure compressor and a high pressure compressor arranged downstream from the low pressure compressor. A variable stator vane is arranged upstream from the high pressure compressor. The variable stator vane is connected to an actuator, and a controller is in communication with the actuator. The controller is configured to provide a command to the actuator to move the variable stator vane in response to a high pressure compressor clearance condition. A high pressure compressor rotor speed is altered, and the high pressure compressor clearance condition is changed to a desired clearance.

Abstract: An example method of thermal energy exchange within a turbomachine includes heating a liquid using thermal energy from compressed air, injecting the liquid into a first portion of a turbomachine, and using the compressed air to cool a second portion of the turbomachine.

Abstract: This gas turbine includes a turbine cooling structure of cooling a turbine by using cooling air and a filter that reduces dust in the cooling air on an upstream side of the turbine. Furthermore, the gas turbine includes a supply pipe for supplying the cooling air to the filter, a branch pipe that is branched from the supply pipe on an upstream of the filter, and a unit that calculates or estimates a circulation amount of dust in the cooling air. In this gas turbine, at a time of start-up of a turbine, the supply pipe is closed and the branch pipe is opened, and when the circulation amount of dust in the cooling air becomes equal to or less than a predetermined threshold, the supply pipe is opened and the branch pipe is closed.

Abstract: A system for testing a compressor is provided. The system comprises one or more compressors connected together in series to a test compressor wherein an output of the test compressor is connected to an input of a first compressor in the series, forming an overall loop, one or more process fluid coolers in the overall loop, one or more orifices in the overall loop, a control valve in the overall loop, and a first plurality of sensors configured adjacent to a process fluid input of the test compressor and a second plurality of sensors configured adjacent to a process fluid output of the test compressor.

Abstract: Provided is a compressor control device configured to control a flow rate of a compressor having a plurality of impellers connected to an outlet port-side flow path in parallel and a flow rate regulation unit configured to regulate a flow rate of each of the impellers, the compressor control device including a pressure detection unit configured to detect a pressure of the outlet port-side flow path, a flow rate detection unit configured to detect the flow rate of each of the impellers, and a control unit configured to output a flow rate regulation command of each of the impellers to the flow rate regulation unit and control the flow rate regulation unit based on the detection result of the pressure detection unit.

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 Rankine cycle apparatus (1A) of the present disclosure includes a main circuit (10), a heat exchange portion (HX), a bypass flow path (20), a flow rate-adjusting mechanism (3), and a pair of temperature sensors (7A). The main circuit (10) is formed by an expander (11), a condenser (13), a pump (14), and an evaporator (15) that are circularly connected in this order. The heat exchange portion (HX) is located in the main circuit (10) at a position between an outlet of the expander (11) and an inlet of the pump (14). The bypass flow path (20) branches from the main circuit (10) at a position between an outlet of the evaporator (15) and an inlet of the expander (11), and joins to the main circuit (10) at a position between the outlet of the expander (11) and an inlet of the heat exchange portion (HX). The flow rate-adjusting mechanism (3) adjusts the flow rate of the working fluid in the bypass flow path (20).

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 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 turboexpander-compressor system includes an expander configured to expand an incoming gas, a first set of moveable inlet guide vanes configured to control a pressure of the incoming gas, a compressor configured to compress a gas received from the expander, a shaft configured to support and rotate an expander impeller and a compressor impeller, a second set of moveable inlet guide vanes attached to the compressor and configured to control a pressure of the gas input into the compressor, and a controller configured to acquire information about a rotating speed of the shaft, a pressure and a temperature of the incoming gas, a pressure and a temperature of the gas output from the expander, and to control the second set of moveable inlet guide vanes to maximize a ratio between the rotating speed of the shaft and a drop of an enthalpy across the expander, in off-design conditions.

Abstract: A method for operating a multistage compressor is provided. The method includes monitoring the pump limit, wherein at least a first measurement parameter measured during operation is compared to a reference parameter. The reference parameter is characteristic of reaching the surge limit or a specific distance of the operating point from the surge limit. A multistage compressor is also provided. In order to enlarge the operating range without risking safety, it is proposed that each stage to be monitored individually for the onset of the surge.

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: An omni-directional air flow device, for example, a fan or a vent associated with a fan, comprises a swivel control point providing almost a spherical range of motion of the air flow device so that air may flow in any direction. The omni-directional air flow device may comprise a user input device for receiving a program for controlling movement of the air flow device through a pre-determined path within the spherical range of motion and for controlling air flow velocity as the air flow device follows the pre-determined path. Moreover, the device may further comprise a controller and memory for storing data representing the pre-determined path and varying air flow velocities along the path. When provided with temperature and humidity sensors coupled to the processor, the processor may calculate a comfort index and adjust the pre-determined path or air flow velocity accordingly.