Abstract: Systems and methods for stable operation of a compressor of a gas turbine engine include axial stages, each including a series of rotor blades. A centrifugal stage has a centrifugal impeller disposed downstream from the axial stages. Air flows through the compressor first through the axial stages and then through the centrifugal stage. Each respective axial stage includes mechanisms for the avoidance of certain operating conditions of the compressor such as surge. The mechanisms include variable vane sets disposed upstream from a series of the rotor blades or a bleed port or ports around the respective axial stage downstream from the series of rotor blades to selectively extract air from the respective axial stage.

Abstract: A method of operating a chiller system includes receiving an input from at least one sensor associated with a compressor of the chiller system, determining that the compressor is experiencing a surge or rotating stall event, adjusting at least one operating parameter associated with a heat rejection heat exchanger of the chiller system in response to determining that the compressor is experiencing the surge or rotating stall event, and reducing a condenser saturation temperature by adjusting the at least one operating parameter.

Abstract: A centrifugal compressor for a chiller includes an impeller, a motor, a diffuser, and at least one injection port. The impeller is attached to a shaft rotatable about a rotation axis. The motor is arranged and configured to rotate the shaft in order to rotate the impeller. The diffuser is disposed downstream from the impeller. The at least one injection port is located within the diffuser. The at least one injection port is configured and arranged to supply liquid refrigerant into the diffuser from a condenser or an economizer of the chiller.

Abstract: A system and a method for configuring at least one variable geometry mechanism (VGM) of an aircraft engine are provided. Pass-off testing data for the aircraft engine is obtained, the pass-off testing data indicative of an actual value of at least one operating parameter of the aircraft engine. Based on the pass-off testing data, at least one trim value to be used to adjust a setting of the at least one VGM to bring the actual value of the at least one operating parameter towards a target value is determined, a running line of the aircraft engine being substantially constant when the actual value of the at least one operating parameter is at the target value. The setting of the at least one VGM is adjusted, during pass-off testing of the aircraft engine, using the at least one trim value.

Abstract: A system includes a dynamic compressor and a controller. The dynamic compressor includes a motor having a driveshaft rotatably supported within the dynamic compressor and a compression mechanism connected to the driveshaft and operable to compress a working fluid upon rotation of the driveshaft. The controller is connected to the motor and includes a processor and a memory. The memory stores instructions that program the processor to operate the motor to compress the working fluid at a motor speed greater than a predicted minimum surge speed plus a control margin, determine when surge events have occurred, store, in the memory, an indication of each surge event that the processor determined to have occurred, and determine whether or not to take a protective action when the processor determines that a surge event has occurred.

Abstract: A pump, in particular for a fluid circuit in a vehicle, for example a coolant pump with a multi-part housing that has a pump chamber, wherein an impeller is arranged in the pump chamber, wherein the pump chamber is bounded by a pump housing and a further housing part of the multi-part housing, wherein the pump housing and the further housing part each have a flange surface that rest against one another, and wherein one of the two flange surfaces has at least one annular groove and the other of the two flange surfaces has at least one circumferential web which engages in the annular groove.

Abstract: A turbine exhaust unit supporting device that supports a turbine exhaust unit is provided. The turbine exhaust unit supporting device installed at a rear side of a turbine casing to support a turbine exhaust unit through which exhaust gas passing through a turbine is discharged, the supporting device includes a casing supporting block unit installed on an outer circumferential surface of the turbine casing, an exhaust unit supporting block unit spaced apart from the casing supporting block unit and installed on an outer circumferential surface of the turbine exhaust unit, and a rotary coupler including a first end rotatably coupled to the casing supporting block unit and a second end rotatably coupled to the exhaust unit supporting block unit.

Abstract: A system for controlling gas turbine engine rotor blades tip clearance is described. A rotor is mounted to an engine shaft, supported by a thrust bearing, for rotation within a gas path shroud circumscribing blades of the rotor, the gas path shroud having a non-cylindrical shape in the vicinity of the rotor blades. A rotary actuator is associated with the thrust bearing and configured for axial translation of the thrust bearing, to thereby axially translate the engine shaft and the rotor blades relative to the gas path shroud. This translation is configured to vary the blade tip clearance of the rotor.

Abstract: A variable geometry assembly for modulating a fluid flow in a turbomachine is disclosed. The assembly comprises a first ring having a plurality of first wedge-shaped elements and having an axis, and a second ring having a plurality of second wedge-shaped elements and having an axis. The second ring is substantially coaxial to the first ring. The second wedge-shaped elements co-act with the first wedge-shaped elements. Flow passages are defined between pairs of sequentially arranged first wedge-shaped elements and second wedge-shaped elements. The first ring and the second ring are angularly displaceable one with respect to the other. Moreover, the first ring and the second ring are configured to move axially with respect to one another when the first ring and the second ring are angularly displaced one with respect to the other.

Abstract: A coolant pump for an internal combustion engine. The coolant pump includes a delivery duct, a drive shaft, a coolant pump impeller arranged on the drive shaft to rotate therewith and to convey a coolant, and an adjustable control slide which controls a throughflow cross-section of an annular gap arranged between an outlet of the coolant pump impeller and the surrounding delivery duct. The control slide comprises a first pressure chamber arranged on a side of the control slide facing away from the coolant pump impeller and a second pressure chamber arranged opposite thereto. A control pump includes a control pump impeller arranged at the drive shaft to rotate therewith. A connecting duct fluidically connects the flow duct to the second pressure chamber. A pressure duct fluidically connects the flow duct outlet to the first pressure chamber. A valve opens and closes a throughflow cross-section of the pressure duct.

Abstract: A method for operating a gas turbine plant having a compressor and a turbine, where a limit value of a guide blade adjustment for the compressor of the gas turbine is identified depending on at least one drive shaft speed of the gas turbine plant. For the at least one drive shaft speed, a maximum allowable turbine entry temperature corresponding to the limit value of the guide vane adjustment for the compressor or a maximum allowable temperature for the turbine of the gas turbine, which is dependent on the turbine entry temperature, is identified. The gas turbine is operated in consideration of the identified maximum allowable turbine entry temperature or the identified maximum allowable temperature.

Abstract: A system includes a gas turbine engine, which includes a compressor configured to generate compressed air and a turbine. The turbine includes a stationary component and a conduit configured to convey the compressed air from the compressor to the stationary component in a forward direction. The gas turbine engine also includes a flow control device coupled to the conduit. The conduit is configured to convey a gas path air from the stationary component in a reverse direction opposite from the forward direction when the flow control device is in a startup mode. The gas turbine engine also includes a shaft coupled to the compressor and the turbine.

Abstract: A turbomachine, particularly a steam turbine, is provided. The turbomachine includes a machine housing and a shaft, which is guided through and guided out of the machine housing, at least on one side, wherein at least one annular gap present between the shaft and the machine housing is sealed by way of a shaft sealing assembly, wherein the shaft sealing assembly includes at least one radial double seal having two pairs of sealing surface pairs, which are spaced apart substantially radially and between which an annular sealing liquid chamber is formed, which can be supplied with sealing liquid via a sealing liquid feed line, wherein each sealing surface pair has an annular rotating sealing surface and an annular non-rotating sealing surface, which are arranged substantially axially opposite of each other and prestressed with respect to each other.

Abstract: A turbocharger, comprising: at least one of a turbine housing, a bearing housing and a turbine wheel, wherein the turbine wheel is rotatably mounted about an axis and includes a guide apparatus with a plurality of guide vanes rotatably mounted in pivot bearings on a guide vane support, wherein the guide vanes influence the flow in a flow channel of the turbine housing; and a spring element, which moveably loads the guide apparatus in an axial direction against a wall of the turbine housing, and wherein the disc springs seal a displacement chamber provided with a displacement mechanism of the guide apparatus against the flow channel.

Abstract: According to an aspect of the disclosure, an annular seal generally includes a hollow member having two ends and an inner surface. The hollow member has a number of depressions formed in and extending around its inner surface. Each of the depressions having a depth that is a function of its distance from one of the two ends.

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

Abstract: A fan frame and a fan having temperature detecting element are provided. The fan frame includes a body and a circuit board. The body includes an inlet. The circuit board is installed around the inlet of the body. The temperature detecting element traverses the inlet. The first wire electrically connects the first contact end and the first external contact terminal. The second wire electrically connects the second contact end and the second external contact terminal. At least one of the first wire and the second wire includes a plurality of bending sections. By utilizing the bending sections of the first wire or the second wire, the length of the first wire or the second wire can be increased. Therefore, the influence in the temperature detecting element caused by the circuit board can be lowered and the error of the detecting temperature can be decreased.

Abstract: A compression system includes a compressor with adjustable inlet guide vanes (IGVs) and variable stator vanes (VSVs) that are adjustable independently of each other. IGV and VSV control units produce respective IGV and VSV reference commands responsive to respective first and second inputs that may be responsive to measured properties of the compression system. The second input may be provided by a model of the compressor or of the compression system responsive to measured properties. The second input may particularly be an estimate of a property not directly observable, such as stall margin or efficiency.

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.

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 feathering device for the fan blades of a turboprop engine that includes at least one set of fan blades with adjustable orientation is provided. The assembly is attached in rotation to a rotating cowling connected to a turbine rotor. Each blade is coupled, for the adjustment of its orientation, to a control ring that is movable between two extreme positions, one of which corresponds to feathering of the blades. Mechanical parts are able to extend elastically as a result of a rise in their temperature, these mechanical parts being positioned facing the control ring so as to be able to exert a thrust force on the ring in order to put it in a position to feather the blades when they expand. A device to cause a rise in the temperature of the mechanical parts so as to expand them is also provided.

Abstract: A centrifugal compressor is provided with: a housing which houses a compressor wheel therein; a spiral scroll arranged in an outer periphery of the compressor wheel; and a diffuser portion provided as a path space communicating with the scroll from an outlet side of the compressor wheel and formed by a compressor housing and a center housing. The centrifugal compressor is also provided with a movable vane which is movable between a projecting position where the movable vane projects from the compressor housing and a housing position where the movable vane houses in a housing portion provided in compressor housing, and an actuator which drives the movable vane between the projecting position and the housing position. The actuator is provided in the center housing.

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 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: 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: The present invention relates to a submersible centrifugal pump assembly comprising an impeller suspended in the end of a drive shaft, and driven in rotation relative to an impeller seat which is stationary in normal operation and which defines an axial intake for liquid to be transported by the impeller in rotation. The pump assembly is characterized in that the impeller seat is journalled in a pump housing for limited rotational movements in opposite directions of rotation relative to the pump housing, and in rotation controlled in guide means for limited linear displacements in opposite axial directions relative to the impeller.

Abstract: A fluid turbine apparatus for use with a turbine comprising a convergent section, a fluid turbine section adjacent to an outlet of the convergent section, and a divergent section adjacent to the fluid turbine section. The fluid enters through the convergent section and exits through the divergent section. The convergent and divergent sections are constructed using a modular grid-like structure supporting retractable wall panels. The internal vacuum created by the diffuser and the wind shear stresses on the convergent and divergent sections can be limited. Configurations of the convergent and divergent sections can be adjusted to suit prevailing wind velocities. Barriers of rotating deflectors are used to increase the effective area of the convergent and divergent sections during low wind conditions. Horizontally mounted aerodynamic deflectors may be used to decrease wind shear and drag on the divergent section, the turbine section, and on side walls of the convergent section.

Abstract: A turbine is operatively connected to load structure, to transmit rotary drive thereto, with two-phase flow nozzle receiving pressurized flow to rotate the turbine, the nozzle structure configured to expand flow consisting of two or more of the following phases: i) gas ii) liquid iii) gas and liquid mixture iv) supercritical gas and liquid mixture, and with efficient conversion of enthalpy.

Abstract: A self-adjusting device (25) for controlling the clearance (C), especially in the radial direction, between rotating and stationary components (21, 23) of a thermally loaded turbo machine, changes clearance (C) in a linear and/or non-linear way during transition of the machine between standstill and steady-state operation. Simple and effective control can be achieved, even in the case of a nonlinear variation of the clearance during transitional operation, by the self-adjusting device (25) including at least two different driving elements (A, B) to move the rotating and fixed components (21, 23) relative to each other in order to change the clearance (C) between them, and by the different driving elements (A, B) being configured to be activated at different times during the transition of the machine.

Abstract: A system adjusts positions of gas turbine inlet guide vanes (IGVs) and variable stator vanes (VSVs). The system includes a hydraulic power unit providing a supply of hydraulic fluid, an IGV servo in fluid communication with the hydraulic power unit, and a VSV servo in fluid communication with the hydraulic power unit. An IGV cylinder set is provided in fluid communication with the hydraulic power unit via the IGV servo and is connected to the IGVs. The IGV cylinder set effects displacement of the IGVs between a closed position and a fully open position. A VSV cylinder set is provided in fluid communication with the hydraulic power unit via the VSV servo. The VSVs include multiple stages linked together with a torque shaft. The VSV cylinder set is connected to the torque shaft, and the VSV cylinder set effects simultaneous displacement of the stages of the VSVs between a closed position and a fully open position.

Abstract: A gas-turbine engine includes stator vanes (1) angularly variable about their longitudinal axes by actuating elements in order to control airflow supplied to downstream rotor blades (6). The actuating elements are arranged in the most confined downstream stages of the compressors and/or turbines, with these stages being exposed to high temperatures, so that stable and efficient operation is ensured. The actuating elements (8) fixed to the inner or the outer casing (4, 12) are made of a material expanding, contracting or deforming in dependence of the temperature and transmit the respective deformation to the swivellably borne stator vanes (1).

Abstract: A method, system and computer program product for operating a wind turbine is disclosed. For operating the wind turbine a set of operational data points are sensed via a sensing module. The set of operational data points may include bending stress values. Based on the bending stress values, a load scenario indicator value may be computed. Further, based on the set of operational data points a loading threshold value may be obtained. At least one operating parameter of the wind turbine is changed if the load scenario indicator value exceeds the loading threshold.

Abstract: A system, in certain embodiments, includes a magnetic actuator configured to adjust a radial clearance between a housing and rotary blades via translational movement along a rotational axis. The system includes a controller configured to engage the magnetic actuator to adjust the radial clearance in response to feedback.

Abstract: Operations of a turbine to generate energy from a relatively slow fluid flow, such as wind and water, are described. The turbine has a plurality of foils rotating about a central axis at a rotational velocity, each of the foils having a length and a foil axis parallel to the length and the central axis with each of the foils rotatable about its foil axis. From determinations of a velocity of the fluid flow, and angular location of each foil and the rotational velocity about the central axis, an attack angle of each foil is controlled with respect to the direction of fluid flow about the foil axis responsive to the velocity of the fluid flow, the angular location of the foil and the rotational velocity as the foil rotates about the central axis.

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

Abstract: Actuators utilising shape memory alloy materials are known with regard to gas turbine engines. Such shape memory alloys have been used with respect to deformation provided in vanes and blades as well as nozzle elements in order that variations can be made in engine configuration dependent upon thermal cycling. Unfortunately, pedestals in order to provide spacing between the shape memory alloy and an antagonistic bias has resulted in uneven stress distribution as well as a higher thermal mass for the shape memory alloy. An uneven stress distribution will limit operational life whilst a higher thermal mass will result in slower reaction times. By separation of the shape memory alloy or material from its antagonistic bias through use of a slide element, a reduction in thermal mass is achieved and, more importantly, stress differentiation across the actuator is reduced.

Abstract: A monitoring system for a wind turbine includes at least one acoustic sensor configured to measure an acoustic emission generated by at least one component of the wind turbine, and a control system configured to calculate at least one wear characteristic of the component based on the measured acoustic emission. The wear characteristic includes at least one of a current amount of wear on the component, a rate of wear on the component, and a predicted amount of wear on the component.

Abstract: A pressure activated flow path seal for a steam turbine is disclosed. In one embodiment a gap closure component is located about a rotary component and the stationary component of the steam turbine. A pressure differential activates the gap closure component to seal or reduce the radial clearance of a steam leakage path between the rotary component and the stationary component.

Abstract: A wind turbine unit for generating electricity in a confined space includes a pair of sails carried at either end of a pair of spaced, axially aligned rotatable arms mounted to the drive shaft of an electrical generator. As the prevailing wind strikes the sails in opposite directions, one of the sails is moved to a vertical position while the other sail is moved to a horizontal position. The wind incident on the then vertical sail causes the arms to rotate about the longitudinal axis of the generator and the sails are alternatively raised and lowered between a vertical and a horizontal position so that one of the sails is vertical while the other is horizontal.

Abstract: A wind guiding cover, mounted on a fan, includes a rotating ring and a plurality of slats. The rotating ring is pivoted to the fan, and has an opening for an air flow generated by the fan to pass through. The rotating ring has a weight portion for offsetting the center of gravity of the rotating ring and normally maintaining the rotating ring at a static equilibrium position. The slats are pivoted to the rotating ring and arranged at the opening. When the fan operates, the slats are lifted by the air flow to open the opening. When the fan stops operating, the slats cover the opening under the gravity.

Abstract: A system and method provide a proactive mechanism to control pitching of the blades of a wind turbine to compensate for rotor imbalance during normal operation by pitching the blades individually or asymmetrically, based on turbulent wind gust measurements in front of the rotor, determined before it reaches the rotor blades.

Abstract: A pump/motor includes a stator (10) having an interior profile surface and a rotor having an exterior profile surface. The stator tube is formed from the sheet metal spiral round to generate an interior profile, with an adjacent edge of the spiral wound sheet being secured together. Substantially uniform thickness elastomeric layer (20) form down interior surface of the stator tube. A rotor (30) is rotatable within the stator tube and the elastomeric layer of an operation of pump/motor.

Abstract: A turbine-intake tower for delivering wind to a turbine has a hollow support column, an intake nozzle assembly rotatably coupled to the support column, and a tower nozzle disposed within the support column. The intake nozzle assembly is configured to receive and to accelerate wind. The tower nozzle is configured to receive the wind from the intake nozzle assembly and to further accelerate the wind received from the intake nozzle assembly for delivery to the turbine.

Abstract: A vertical-axis wind turbine which has a central rotary tower upon which are fixed substantially vertical blades. The blades are capable of rotating and moving radially relative to the central tower, the movement of each blade being independently controlled based on the conditions to which it is constantly subjected so as to optimize the overall performance of the wind turbine.

Abstract: Variable phase turbine apparatus comprising, in combination a rotatably driven load structure, defining an axis, confinement means forming a fluid flow passage extending generally axially and adjacent said load structure, a turbine operatively connected to said load structure, to transmit rotary drive thereto, two-phase flow nozzle means receiving pressurized flow via said passage, and directing flow of fluid from said passage, expanded in the nozzle means, at the turbine to rotate the turbine, the nozzle means configured to expand flow consisting of two or more of the following phases: v) gas vi) liquid vii) gas and liquid mixture viii) supercritical gas and liquid mixture, and with efficient conversion of enthalpy.

Abstract: A thermally-activated flow clearance reduction for a steam turbine is disclosed. In one embodiment a gap closure component is located about a rotary component and a stationary component of the steam turbine. A temperature differential activates the gap closure component to seal or reduce the radial clearance of the steam flow path between the rotary component and the stationary component.

Abstract: A pump for the drawing-in of a fluid, including at least one centrifugal wheel having a fluid inlet edge and a fluid outlet edge, the pump further including an axial balancing system with a high-pressure flow space defined between the housing and an upstream face of the centrifugal wheel. The axial balancing system further includes a device for substantially increasing the hydrostatic pressure of the fluid circulating in the high-pressure flow space during operation of the pump.

Abstract: A wind power installation module comprising wind turbines arranged on a support body, each of the wind turbines comprises a rotor with a certain number of blades, a stator supporting the rotor in such a way that the rotor may rotate on the turbine axis for generating electric energy and a shroud extending circumferentially around the stator and the rotor and supporting the stator so as to define an air channel of a certain air channel diameter at an inlet portion of the shroud. The shroud has a maximum outer diameter such that the air channel diameter is comprised in the range from 0.82 to 0.9 times the maximum outer diameter. Furthermore, the shroud has a length in direction of the turbine axis that is comprised in the range from 0.1 to 0.25 times the outer diameter.

Abstract: (A1) A turbofan engine control system is provided for managing a fan operating line. The engine (10) includes a spool having a turbine housed in a core nacelle (12). A turbofan (20) is coupled to the spool (14). A fan nacelle (34) surrounds the turbofan and core nacelle and provides a bypass flow path having a nozzle exit area (40). A controller (50) is programmed to effectively change the nozzle exit area in response to an undesired turbofan stability margin which may result in a stall or flutter condition. In one example, the physical nozzle exit area is increased at the undesired stability condition in which the airflow into the engine creates a destabilizing pressure gradient at the inlet side of the turbofan. A turbofan pressure ratio, turbofan pressure gradient, low spool speed and throttle position are monitored to determine the undesired turbofan stability margin.

Abstract: A system and method are provided for effectively removing ice that may have formed on gas turbine engine compressor inlet guide vanes and/or preventing, or at least inhibiting, reformation of ice on gas turbine engine compressor inlet guide vanes after the ice has been removed. A determination is made as to whether flow through the compressor is below a predetermined flow value. If the flow through the compressor is below the predetermined flow value, then the inlet guide vanes are repeatedly moved between at least two predetermined positions to remove ice and/or prevent, or at least inhibit, reformation of ice on the inlet guide vanes.