Abstract: A system and method for sensing level of a fluid associated with a submersible pump having an impeller driven by an associated motor include a fluid level sensor having a probe with a plurality of discrete resistive elements each having an associated contact pair substantially evenly spaced along a length of the probe and an associated switch powered by an induced voltage or current generated by power provided to the submersible pump motor and activated by the fluid conducting across the contact pair to shunt the associated discrete resistive element.

Abstract: An exemplary turbocharger assembly includes a housing with a through bore having a central axis extending between a compressor end and a turbine end of the housing and a bearing, configured for receipt by the through bore, where the bearing includes an inner journal configured to rotatably support a turbocharger shaft and where the inner journal includes a central axis, an axial length, a lubricant opening, an axially confined lubricant well, a lubricant ramp, and a lubricant channel that spans the axial length of the inner journal. Various other exemplary devices, systems, methods, etc., are also disclosed.

Abstract: An engine has a blade stage and a circumferential array of blade outer air seal segments. A support ring carries the blade outer air seal segments. The support ring has a low-CTE member and a high-CTE member intervening between the blade outer air seal segments and the low-CTE member.

Abstract: An oil cooling arrangement includes a first manifold and a second manifold, each configured to route an oil. Further included is a first tube having a first end proximate the first manifold and a second end proximate the second manifold, wherein the first tube is configured to receive the oil and route the oil toward the second manifold. Yet further included is a second tube having a third end proximate the second manifold and a fourth end proximate the first manifold, wherein the second tube is configured to route the oil from the second manifold toward the first manifold. Also included is a turbine exhaust path configured to route an exhaust flow, wherein the first tube and the second tube are disposed along the turbine exhaust path, wherein the oil is cooled upon passage of the exhaust flow over the first tube and the second tube.

Abstract: Embodiments of the present application include a variable stator vanes control mechanism for a gas turbine engine. The control mechanism includes a moveable actuation rod in operative communication with a first unison ring such that movement of the actuation rod drives the first unison ring. The control mechanism also includes a bell crank mechanism in operative communication with the first unison ring and a second unison ring such that movement of the first unison ring drives the second unison ring.

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

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

Abstract: An energy diffusion sealing ring [872] for use with a hydrocyclone or pump is provided. The energy diffusion sealing ring [872] comprises a sacrificial suspension matrix [872A] comprised of a polymer, elastomer, or combination thereof, and a number of packed inserts [872B] suspended in the matrix [872]. The matrix [872] serves as delivery means for the inserts [872B] into one or more recessed portions [833, 841]. The inserts [872B] comprise a hard material (e.g., ceramic or carbide) and form wear bodies which slow and dissipate kinetic energy of escaping slurry by way of creating paths of resistance. As the suspension matrix [872A] erodes over time, a plurality of interstices [872C] between the inserts [872B] are formed. Escaping slurry [852] slows as it traverses three-dimensional serpentine paths defined by said interstices [872C], thereby reducing its potential to wear surrounding components.

Abstract: A method for operating a wave energy converter for converting energy from a wave motion of a fluid into a different form of energy includes at least one rotor and at least one energy converter that is coupled to the at least one rotor. A first torque that acts on the at least one rotor is generated by the wave motion, and a second torque (M1) that acts on the at least one rotor is generated by the at least one energy converter. The second torque (M1) is specified during a control of the energy converter.

Abstract: A device for de-icing a wall of a leading edge of a turbine engine, the leading edge being adapted to cooperate with a downstream guide vane subjected to a flow of fluid, the device including: a first fluid flow device provided along an upper zone of the downstream guide vane so as to guide the fluid to the wall of the leading edge, and a second fluid flow device provided along a lower zone of the downstream guide vane so as to evacuate the fluid from the leading edge, wherein the first fluid flow device is arranged such that the wall of the leading edge is impacted by the fluid along a non-orthogonal direction.

Abstract: An air turbine has two sets of blades concentrically mounted on a rotatable shaft. The two sets of blades are housed separately and an air supply for the turbine enters an air inlet of a first housing to drive a first set of blades and exits from the first housing to a second housing through an air transfer opening to drive the second set of blades in the same direction, the air exiting the second housing through an air outlet. Returning blades of each cycle of each set of blades is subjected to little or no resistance. A flywheel is concentrically mounted on the shaft and is connected to drive generators. The air supply is a controlled air supply and, preferably, the air supply is compressed air. The shaft of the turbine is oriented to the either horizontal or vertical.

Abstract: Various methods and systems are provided for detecting turbocharger degradation. In one example, a method comprises detecting an axial position of a turbine rotor based on output from a turbine speed sensor, and if the axial position is greater than a threshold distance from a base position, indicating turbocharger degradation.

Abstract: Provided is a well pump system that includes a pressure pipe, a rotatable shaft surrounded by a plurality of bearings, a pumping mechanism mounted to the pressure pipe and having a plurality of pump impellers mounted to a second end of the shaft, a rotating mechanism mounted to a first end of the shaft and configured for rotating it within the bearings, thereby causing the pump impellers to move the fluid in the pressure pipe, and at least one non-return valve configured for assuming at least two states including a first, opened state, in which the second pipe chamber is in fluid communication with the first pipe chamber, and a second, closed state, in which the non-return valve obstructs the fluid communication between the first and the second pipe chambers, thereby lubricating them.

Abstract: A method for barring a rotor of a thermally loaded turbomachine includes stopping normal operation of the turbomachine; providing a barring device for rotating the rotor about a machine axis; coupling the barring device to the rotor; letting the rotor cool down during cool down of the rotor rotating the rotor by means of the barring device. A damage of the machine due to thermally induced buckling during the barring process is avoided by consecutively determining the force or torque applied to the rotor by the barring device for rotating the rotor and/or the circumferential speed of the rotor during barring. The rotation of the rotor is controlled by means of the barring device in dependence of the determined force or torque and/or circumferential speed in order to reduce a bending or imbalance of the rotor, which is due to a nonuniform temperature distribution on the rotor during cool down.

Abstract: A system for bleeding air on an aircraft, including: at least one air bleed valve that can bleed a flow of air on the aircraft, a first temperature information module, a second temperature information module, at least one control module, and at least one data processing module coupled to the control module.

Abstract: A method of operating a variable speed wind turbine as a function of a wind speed is disclosed. The method comprises following a power curve describing the operation of the wind turbine as a function of wind speed in steady-state conditions. The method further comprises changing the pitch angles of the blades in transient conditions in which the wind turbine cannot follow the power curve in the second operational range.

Abstract: A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having an outer surface and an inner surface that axially extend between a leading edge portion and a trailing edge portion. At least one augmentation feature is disposed on at least one of the leading edge portion and the trailing edge portion of the outer surface of the platform.

Abstract: A fan system is disclosed having a forward fan stage configured to pressurize an airflow and an aft fan stage having a tip-fan configured to pressurize a first portion of a pressurized air flow from the forward fan stage wherein the aft fan stage is driven by a second portion of the pressurized airflow.

Abstract: A gas turbine engine includes a fan section including a fan that is rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A bypass ratio is greater than about 11.0.

Abstract: The disclosure relates to a turbo-machine comprising a stator and a rotor arranged rotatable inside the stator as well as at least one electric heating device which is arranged on the surface of at least part of the stator for active clearance control. Besides the turbo-machine, a method for operating the active clearance control comprising electric heating devices is disclosed.

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 and a process for measuring rotor creep values for a monolithic rotor of an industrial gas turbine engine in order to determine when creep growth of the rotor has exceeded an allowable limit. One or more critical locations of the rotor are measured for real-time radius, and a CPU having rotor creep deflection model is used to compare the real-time data and determine if the rotor creep is within safe and allowable limits. If the creep is determined to exceed allowable values, then an alarm in initiated or engine shutdown occurs.

Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for controlling turbine guide vane positions. According to an example embodiment of the invention, a method is provided for controlling at least one turbine guide vane. The method includes receiving a reference signal associated with the at least one turbine guide vane, measuring an actuator position and an angular position associated with the at least one turbine guide vane, generating a deadband signal based at least in part on the angular position, and manipulating the at least one turbine guide vane based at least in part on the deadband signal and the reference signal.

Abstract: A compressor (22; 260; 300; 400) has a housing assembly (140) with a suction port (24), a discharge port (26), and an economizer port (58). An impeller (154) is mounted to be driven in at least a first condition so as to draw a main flow of fluid through the suction port and discharge the fluid from the discharge port. A diffuser (220; 302; 402) has a plurality of diffuser passages (222; 310, 308; 403). Each diffuser passage has an inlet (224) positioned to receive fluid from the impeller and an outlet (220) downstream of the inlet in the first condition. One or more passages (230, 231, 232, 234, 236, 268; 320, 330, 332; 412) are positioned to draw an economizer flow of fluid from the economizer port and deliver the economizer flow downstream of the impeller inlet (212) but upstream of the diffuser passage outlets (226).

Abstract: A blade outer air seal system for a gas turbine engine includes a plurality of ring carriers made of a first material having a first coefficient of thermal expansion. A plurality of seal segments are carried, respectively, on the plurality of ring carriers. A ring member is carried in the plurality of ring carriers. The ring member is made of a second material that is different from the first material in composition. The second material has a second coefficient of thermal expansion such that the first coefficient of thermal expansion is 75-175% of the second coefficient of thermal expansion.

Abstract: A sealing system for a wind turbine comprises first component and a second component positioned proximate the first component and movable relative thereto. An absorbent element is secured to the first component and comprises an oil-absorbent material. A contact member is secured to the absorbent element and comprises a non-absorbent material. The contact member abuts the second component so that lubricant leaking from between the first and second components is collected by the absorbent element. A method of maintain a clean environment in a wind turbine with such a sealing system is also disclosed.

Abstract: According to an example embodiment, a gas turbine engine assembly includes, among other things, a compressor. A strut near the compressor includes a flow passage through a portion of the strut. The flow passage is configured to direct air from the compressor to another portion of the gas turbine engine. The flow passage has at least one surface feature that at least partially hinders some airflow through the flow passage.

Abstract: A method of monitoring a rotational system includes identifying a non-nominal spool-down profile.

Abstract: A recirculation flow collector for a fan includes an arcuate housing; a first face with a first circular opening to receive flow; a second face with a second circular opening to allow flow in a normal fan operating condition; and an outlet in a bottom of the arcuate housing to allow recirculation flow.

Abstract: An axial compressor comprising liquid drop feed means for feeding liquid drops to an operating fluid of the compressor, a casing for forming a flow path through which the operating fluid flows down and a plurality of stages, each of which is composed of one continuous rotor blade row and one continuous stator vane row, the axial compressor being structured so that the liquid drops evaporate inside the compressor, characterized in that: the casing is provided with a cavity therein, and the cavity is formed by an outer casing and an inner casing which is enclosing a periphery of the rotor blade rows at the plurality of stages and forming internally a flow path of the operating fluid, and a flow path is provided for feeding the operating fluid to the cavity on a downstream side of a region forming the cavity of the inner casing.

Abstract: According to some aspects of the invention, a turbine, such as a wind turbine, is provided that includes one or more fluid (e.g., air) flow components for inducing a secondary fluid flow that emanates from a rearward location on the turbine to minimize wake effects. According to some aspects of the invention, arrays of turbines, such as in wind farms, are provided that comprise a plurality such turbines. According to further aspects of the invention, methods are provided for minimizing wake effects in a wind turbine and for improving the efficiency of a wind farms.

Abstract: Example embodiments are directed to fluid turbines that include a turbine shroud, a rotor and an ejector shroud. The turbine shroud includes an inlet, an outlet, a leading edge and a trialing edge. The leading edge of the turbine shroud can be round and the trialing edge of the turbine shroud can include linear faceted segments. The rotor can be disposed within the turbine shroud and can define a rotor plane. The turbine shroud can provide a first portion of a fluid stream to the rotor plane via the inlet of the turbine shroud. The ejector shroud can provide a second portion of the fluid stream to the outlet of the turbine shroud via an open area. An example method of operating a fluid turbine is also provided.

Abstract: A method for detecting heat-dissipating air flow is disclosed. The method includes the following steps: detecting whether a reset command is input; if the reset command is input, resetting a wind pressure standard value according to the reset command; if the reset command is not input, controlling a fan to operate at full speed according to a start signal; detecting the wind pressure of a heat-dissipating air flow after controlling the fan to operate at full speed to acquire a wind pressure value; determining whether the wind pressure value is equal to the wind pressure standard value; and generating a warning signal if the wind pressure value is not equal to the wind pressure standard value.

Abstract: Disclosed is a gas turbine engine including a plurality of inlet guide vanes. The gas turbine engine further includes an inlet case supporting each of the plurality of inlet guide vanes, and the inlet case is provided with at least one passageway in communication with a source of fluid. The at least one passageway is configured to communicate the fluid to each of the plurality of inlet guide vanes.

Abstract: A windmill is disclosed having over speed protection. In a preferred embodiment, the vanes are symmetric, curved metal sheets, with each vane's shape having a circular arc corresponding to its portion of the cylindrical support structure. Each vane is mounted with a large leading portion exposed to the wind. The imbalance of surface area causes the wind to push the vane open when moving downwind and push the vane closed when moving upwind. During periods of high rotational speed, the off-axis centers of mass cause each vane to rotate towards a closed position under centrifugal force. Once the critical speed is reached, the vanes fully close as they pass through the upwind side.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan with a plurality of fan blades rotatable about an axis. Each of the plurality of fan blades includes a mid-span shroud and a speed change device in communication with the fan.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan rotatable about an axis and a speed reduction device in communication with the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A fan blade tip speed of the fan is less than 1400 fps.

Abstract: A passive leakage device for an axial turbomachine, more particularly for a low-pressure compressor of an axial turbomachine, is adapted to reduce and/or eliminate the surging phenomenon within the machine. The passive leakage device includes an insert having a general cylindrical shape with a flange at one end and a bottom or membrane at the other end. The membrane comprises two cross-shaped notches, the notches being adapted to enable a deformation of the membrane under a pressure exceeding a predetermined threshold, so as to allow a leakage to go through the membrane. Several inserts are arranged through the wall of a compressor casing, distributed over one or several circumferences of the casing, facing one or several rows of rotor blades. In the case of a double-flow turbomachine, such as a jet engine, the beak for separating the primary and secondary flows is used to form a chamber for communication between the inserts and for compensation with the pressure present in the secondary flow.

Abstract: A seal monitoring and control system for a gas lubricated non-contacting seal includes various sensors providing signals to a programmable logic control system. The control system is disposed to determine a presence of an anomalous operating condition of the seal, for example, based on phase, relative position of rotor to stator or other signals in combination provided by the various sensors to provide an output signal, which in one embodiment performs at least one mitigating process to correct the anomalous operating condition by adjusting at least one operating parameter of the seal.

Abstract: The invention concerns a pump turbine plant, comprising a turbine with a turbine impeller as well as a turbine spiral housing; a pump with a pump impeller as well as a pump spiral housing; an electrical machine, which is in a drive connection with the shaft or can be brought into said connection; a hydraulic short-circuit can be created between turbine and pump. The invention is characterised by the following features: the turbine has a higher rated power than the pump.

Abstract: A component, a component manufacturing process, and a component operation process are disclosed. The component has a diffuser permitting compressible fluid to flow throughout a first region and a second region of the diffuser at a decreasing velocity. The diffuser includes a coating collection feature. The component manufacturing process includes positioning the component and applying the coating to at least a surface of the component outside of the diffuser and to at least a portion of the second region, not to the first region, to the coating collection feature, or a combination thereof. The component operation process includes positioning the component and transporting the compressible fluid through the diffuser.

Abstract: A method or system for steam purity monitoring in a steam powered turbine includes providing a chloride-sensing device in a steam flow path; generating a signal from the chloride-sensing device indicative of a concentration level of chloride ions in a steam flow; and indicating a concentration level of chloride ions in a steam flow. The steam turbine includes a rotor, a rotating shaft and a plurality of axially spaced rotor wheels. A plurality of rotating blades is mechanically coupled to each rotor wheel. A chloride-sensing device is disposed in a steam flow path. A controller is arranged to generate a signal from the chloride-sensing device indicative of a concentration level of chloride ions in a steam flow and indicate a concentration level of chloride ions in a steam flow.

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

Abstract: A gas turbine engine (100) variable nozzle (460) includes an outer shroud (461), an inner shroud (462), a variable nozzle airfoil (463), and a position selector (470). The inner shroud (462) is located radially inward from the outer shroud (461). The variable nozzle airfoil (463) extends radially between the outer shroud (461) and the inner shroud (462). The variable nozzle airfoil (463) includes a vane shaft (464) extending radially outward from the variable nozzle airfoil (463) through the outer shroud (461). The position selector (470) is coupled with the variable nozzle airfoil (463) to fixedly lock the variable nozzle airfoil (463) into one of a plurality of preselected positions.

Abstract: A hub cooling apparatus adapted to a wind generator has a circulating fan module installed in a nosed end of a hub and a wind guiding module installed in a main shaft of a nacelle; wherein the circulating fan module is driven by the rotating hub, the wind guiding module is driven by the rotating main shaft.

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 method for operating a rotary machine with a rotor that is mounted in a bearing is provided. The rotor is subjected to a thrust that acts substantially in only an axial direction during the operating time. The thrust is received and dissipated by a first thrust bearing of the bearing via sliding means, the bearing having a second thrust bearing. The axial vibrations of the rotor are damped or completely prevented by means of the second thrust bearing generating a force that acts on the first thrust bearing in the direction of the thrust at least temporarily at the same time as the thrust occurs.

Abstract: A counter-rotating wet gas compressor for deployment and operation on the sea floor is described. The compressor has alternating rows of impellers, with each successive row of impellers being mounted a central hub or to an outer sleeve. According to some embodiments, no static diffusers are positioned between the alternating counter-rotating rows of impellers such that the design is structurally robust, compact and capable of compressing fluids that contain significant portions of liquid phase.

Abstract: A seal system, for an apparatus that includes a rotatable portion with airfoils coupled thereto and a stationary portion with an inner surface, includes an abradable portion including at least one abradable layer of an abradable material formed over the inner surface. The seal system also includes an abrading portion disposed over at least a portion of a substrate of the airfoil. The abrading portion includes at least one abrading layer formed on at least a portion of the substrate and a plurality of abrasive particles embedded within the abrading layer. The plurality of abrasive particles includes at least one of substantially all of one of tantalum carbide (TaC), aluminum oxide (Al2O3), and ziconia (ZrO2), cubic boron nitride (cBN) and Al2O3 in predetermined ratios, cBN, Al2O3 and ZrO2 in predetermined ratios, Al2O3 and ZrO2 fused together in predetermined ratios, and TaC and Al2O3 in predetermined ratios.