Abstract: A gas turbine engine including a compressor section including a compressor and a turbine section located downstream of the compressor section. The turbine section including a high pressure turbine, a low pressure turbine, a sump positioned between the high pressure turbine and the low pressure turbine, and a rotating cross flow arrangement defining a plurality of guiding passages fluidly coupling the compressor to the sump.

Abstract: A cooling system for a turbine engine. The turbine engine includes a compressor, a turbine, and a shaft that drivingly couples the compressor and the turbine. The cooling system includes one or more cavities of the compressor. The cooling system includes a shaft flowpath defined in the shaft. The shaft includes one or more shaft apertures that provide fluid communication between the shaft flowpath and the one or more cavities. Air passes through the one or more shaft apertures and the shaft flowpath during a shutdown of the turbine engine to cool the one or more cavities.

Abstract: A gas turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement to define a diffuser cavity between the compressor section and the combustor section, and an aft cavity. A compressor discharge pressure duct fluidly draws air from the diffuser cavity, passes it through a heat exchanger to cool the air, and then supplies the cooled air to the aft cavity.

Abstract: A connecting apparatus for fluid connection between a fuel feed line system and a nozzle apparatus of a gas turbine arrangement, includes a gas fuel line which is surrounded by a wall for conducting a gaseous fuel, and a liquid fuel line which is surrounded by a wall for conducting a liquid fuel. Optimized operation is achieved by the connecting apparatus having at least one separate gas line portion arranged on the inlet side of the gas fuel line and a gas/liquid line portion which is arranged downstream of the separate gas line portion and within which the gas fuel line and the liquid fuel line are arranged to form a line arrangement for connection to the nozzle apparatus. The flow cross section of the gas fuel line is of at least substantially identically large configuration within the separate gas line portion and the gas/liquid line portion.

Abstract: A system includes a top cycle and a bottoming cycle. The top cycle is an engine having a combustor. The combustor receives a fuel. The combustor is capable of igniting a mix of fuel and a gas, and creating products of combustion. Products of the combustion pass downstream through a first heat exchanger. The bottoming cycle has a bottoming cycle working fluid receiving a first amount of heat through the first heat exchanger. The bottoming cycle produces work from the first amount of heat. The bottoming cycle working fluid then passes through a second heat exchanger and rejects a second lesser amount of heat. A source housing fuel is delivered to the combustor via the second heat exchanger. The bottoming cycle working fluid provides heat to the fuel being delivered to the combustor. The source is configured to maintain the fuel at a temperature equal to or below 0° F.

Abstract: A two stage fuel delivery system for an aircraft includes a first stage pump including an inlet connected to a source of fuel and an outlet connected to a combustor assembly, and a second stage pump including an inlet portion connected to the source of fuel and an outlet portion connected to the combustor assembly. A bypass valve is connected between the source of fuel, the inlet, and the inlet portion. The bypass valve selectively disconnects the second stage pump from the source of fuel. A metering valve is connected to the inlet and the inlet portion. The metering valve includes a metering valve inlet and a metering valve outlet. A pressure regulating valve is connected to the metering valve. A stage monitoring system is configured to detect a change in operation of the second stage and control the bypass valve.

Abstract: A fuel system of an aircraft engine, having: a boost pump having an input and an output; one or more selector valves; a first component pump having an input fluidly coupled to the output of the boost pump and an output of the first component pump is configured to direct fuel to a first component via the one or more selector valves; and a second component pump having an input that is selectively coupled to either the input or the output of the boost pump by the one or more selector valves, and an output of the second component pump is fluidly coupled to a second component and selectively coupled to the first component by the one or more selector valves.

Abstract: An aircraft system is provided that includes a gas turbine engine, a gearbox and at least one compressor. The gas turbine engine includes a compressor section, a turbine section, a combustor section and a rotating structure. The combustor section is fluidly coupled with and between the compressor section and the turbine section. The rotating structure includes a compressor section rotor within the compressor section and a turbine section rotor within the turbine section. The at least one compressor includes a compressor rotor rotatably driven by the rotating structure through the gearbox. The gas turbine engine may be dedicated to powering the at least one compressor.

Abstract: A method of determining an inlet total air pressure includes determining a first parameter indicative of a first inlet total air pressure. The method includes executing a sequence that includes: determining a mass air flow passing through the air inlet based on the first parameter, determining a Mach number of air passing through the air inlet based on the mass air flow, determining a static air pressure at the air inlet, determining an air pressure ratio based on the Mach number, generating a subsequent parameter indicative of the revised inlet total air pressure based on the air pressure ratio and the static air pressure, and substituting the subsequent parameter for the first parameter. The method includes executing at least one additional instance of the sequence with the subsequent parameter, and outputting the subsequent parameter as the inlet total air pressure.

Abstract: A system is provided for an aircraft. This aircraft system includes an exhaust duct, an exhaust flow regulator, a nozzle bypass duct and a bypass flow regulator. The exhaust duct extends longitudinally to an exhaust nozzle. The exhaust flow regulator is configured to regulate fluid flow through the exhaust duct to the exhaust nozzle. The nozzle bypass duct projects out from a side of the exhaust duct. The bypass flow regulator is configured to regulate fluid flow from the exhaust duct into the nozzle bypass duct. The bypass flow regulator is disposed upstream of the exhaust flow regulator.

Abstract: Systems and methods to control gas turbine firing temperatures during air injection. A method of achieving a desired firing temperature of a gas turbine engine during air injection comprises injecting compressed air into the gas turbine engine using an external source. The external source includes a compressor and a recuperator. The method comprises using a controller of the gas turbine engine to: (a) determine an air injection exhaust bias gain using an inlet temperature of the gas turbine engine; (b) calculate, based on the determined air injection exhaust bias gain and a flow rate of the injected compressed air, an air injection exhaust curve bias; and (c) change a fuel flow of the gas turbine engine by adding the air injection exhaust curve bias to an existing exhaust curve of the gas turbine engine to thereby achieve the desired firing temperature during air injection.

Abstract: Systems and methods are disclosed for estimating or determining a rate or an amount of fuel coke formation in a fuel system, such as of a gas turbine engine. The system is operable to control a rate of fuel coke formation. The system may include a sensor that measures an operating parameter associated with fuel coke formation in the fuel system. A controller is in communication with the sensor to receive the signal therefrom for determining an amount or a rate of fuel coking in the fuel system. Based on this determination the controller may adjust the rate of fuel coke formation by adjusting the operation of the turbine engine, a thermal management system of the turbine engine, or the fuel system.

Abstract: An engine having a linkage assembly, the linkage assembly having a governor lever, a governor shaft, and a throttle link. The governor lever couples the governor shaft to the throttle link. The governor lever is configured to adjust the relative position between the throttle link and the governor shaft. The governor lever has a primary arm and a secondary arm, the primary arm being movable with respect to the secondary arm. The primary arm and secondary arm are secured via a fastener which prevents relative motion between the primary and secondary arms.

Abstract: A method of controlling a fixed cylinder deactivation (CDA) system of an engine system is provided. The method includes: deactivating, by a controller, a cylinder of the engine system to operate the engine system in a fixed CDA mode; determining, by the controller, a temperature of an injector tip nozzle associated with the cylinder; comparing, by the controller, the temperature of the injector tip nozzle to a threshold temperature; and in response to determining that the temperature of the injector tip nozzle is greater than the threshold temperature, activating, by the controller, the cylinder.

Abstract: An ECU includes: an index calculation unit calculating, as indices relating to fuel properties, a first index that indicates a degree of anti-knocking margin and a second index that indicates required ignition energy required for normal ignition; a first control unit for setting a target in-cylinder temperature based on the first index and controlling an in-cylinder temperature based on the target in-cylinder temperature, as an in-cylinder temperature control for controlling the in-cylinder temperature immediately before combustion; and a second control unit for setting a target EGR rate based on the second index and controlling an EGR rate based on the target EGR rate as an EGR control performed by an EGR device for controlling the EGR rate.

Abstract: A thermal management system for controlling cooling of an engine system during shutdown, the engine system includes an engine configured to provide power to a working machine, wherein the thermal management system includes a controller which is configured to receive a signal indicative of an engine shutdown command. The controller is further configured to derive, infer or receive a temperature parameter of the engine system and to determine whether the temperature parameter of the engine system is above a first predetermined threshold; and wherein the controller is configured to signal the progressive reduction of a speed of the engine prior to issuing a signal to shutdown the engine in the event that the first predetermined threshold is exceeded when the engine shutdown command is received, thereby cooling the engine system prior to engine shutdown.

Abstract: At least one server comprising at least one processor coupled to at least one memory storing instructions. The server can receive a first signal from a first monitored system comprising an internal combustion engine and a first sensor, the first signal associated with a first occurrence of an internal combustion engine event, a second occurrence of the internal combustion engine event, and first measurement data of the first sensor. The server can determine a first measurement from the first measurement data. The server can determine a second measurement from the first measurement data. The server can determine a measurement deviation between the first measurement and the second measurement. The server can compare the measurement deviation to a stored measurement threshold. The server can determine a first exhibited useful life of the first sensor based on the measurement deviation and at least one of the first measurement or the second measurement.

Abstract: Provided are a composite coating, a piston, an engine, and a vehicle. The composite coating comprises a metal bonding layer, a transition layer, a ceramic layer, and a sealing layer which are sequentially laminated, wherein the metal bonding layer is configured to be bonded with a piston basic body, the metal bonding layer is a rare earth metal modified bonding layer, and the transition layer is a rare earth metal modified zirconia layer.

Abstract: Systems and generating power in an organic Rankine cycle (ORC) operation to supply electrical power. In embodiments, an inlet temperature of a flow of gas from a source to an ORC unit may be determined. The source may connect to a main pipeline. The main pipeline may connect to a supply pipeline. The supply pipeline may connect to the ORC unit thereby to allow gas to flow from the source to the ORC unit. Heat from the flow of gas may cause the ORC unit to generate electrical power. The outlet temperature of the flow of the gas from the ORC unit to a return pipe may be determined. A bypass valve, positioned on a bypass pipeline connecting the supply pipeline to the return pipeline, may be adjusted to a position sufficient to maintain temperature of the flow of gas above a threshold based on the inlet and outlet temperature.

Abstract: A device and assembly for reliably generating supersonic detonation waves in a fuel and air or fuel and oxygen mixture. The device may use a hemispherical detonation chamber into which reactants, comprising a fuel and air or oxygen mixture are injected and ignited by a laser igniter to initiate a detonation wave. The wave is reflected by the hemispherical geometry of the detonation chamber and may exit the device through a fast-acting valve. The detonation chamber may be then purged and the cycle is repeated many times per second. The device may be used for various applications which include but are not limited to a stand-alone intermittent combustion engine, a pre-detonator for an intermittent combustion engine, a projectile launcher, a cleaning device, acoustical energy generation, pressure energy generation, various manufacturing processes and electric power generation. The device may use liquid, gaseous, or solid fuels, depending on the application.

Abstract: The present invention relates a safety ignition device for a high altitude dual pulse motor according to the present invention, and can prevent accidental ignition of an ignition device or a propulsion engine while efficiently using a space by installing the safety ignition device in front of a combustion pipe, increase the reliability of ignition, and maintain the air tightness of the inside of the propulsion engine and the ignition device even in a high altitude environment.

Abstract: A fuel regulator includes a limit cap which is attached to a needle valve which is inserted into a regulation hole. In an inner peripheral surface of a second hole portion of the regulation hole, a restriction groove and a guide groove which extends from the restriction groove through an outer surface of a main body portion in an axial direction of the second hole portion are formed. A projecting portion which is inserted into the restriction groove is formed on an outer peripheral surface of the limit cap, and the projecting portion is capable of passing through the guide groove, and in the main body portion, a cast hole which extends from the restriction groove through the outer surface of the main body portion in a direction intersecting the axial direction of the second hole portion is formed.

Abstract: A flow control restrictor includes: a needle valve; and a limit cap which is made of metal and attached to the needle valve. In the needle valve, a first shaft portion which is made of metal and screwed into a regulation hole and a second shaft portion which is made of metal and housed inside the regulation hole are formed. On the second shaft portion, a first projection-and-recess portion is formed, and a pressed portion made of resin is provided on the first shaft portion side relative to the first projection-and-recess portion. The limit cap is fitted onto the second shaft portion. On the limit cap, a projecting portion which is inserted into a restriction groove of the regulation hole and a second projection-and-recess portion which is engaged with the first projection-and-recess portion are formed. The pressed portion is pressed against an inner peripheral surface of the limit cap.

Abstract: A fuel vapor recirculation system includes a filler neck adapted to receive a refueling nozzle that dispenses fuel into the filler neck. A fuel tank receives fuel from the filler neck through an inlet check valve. The check valve is disposed in the fuel inlet opening and is normally closed. The check valve opens when fuel is dispensed into the fuel tank. The check valve defines a vent hole that is always open. The fuel tank also includes a fuel limiting vent valve and a grade limit vent valve. A fuel vapor cannister collects fuel vapor and selectively supplies fuel vapor to an intake manifold of a vehicle. The fuel vapor recirculation manifold receives fuel vapor only from the fuel limiting vent valve and the grade limit vent valve in the fuel tank and does not receive fuel vapor directly from the filler neck.

Abstract: An air intake unit for an engine of a vehicle includes a housing, a bypass air intake, a shutter element, and actuator. A plenum is defined inside the housing which can be connected to the engine. Air coming from the outside needed for the operation of the engine can be sucked into the plenum through the bypass air intake. The shutter element is coupled to the bypass air intake and is mounted to move between a closed position, in which the shutter element closes the bypass air intake, and an open position, in which the shutter element leaves the passage through the bypass air intake free. The actuator is configured to move the shutter element between the closed position and the open position. The actuator has a spring configured to generate, by expanding, an opening movement moving the shutter element from the closed position to the open position.

Abstract: An internal combustion engine includes a plurality of cylinders, and a plurality of fuel injectors configured to inject a fuel into a respective cylinder of the plurality cylinders. The fuel injectors are received within a bore in a body of the engine and when in service are movable in relation to the body. A seal surrounds each fuel injector and extends between each injector and a peripheral region of the bore.

Abstract: The invention provides a power supply device for vehicle emergency starting, which includes a built-in battery, a protection switch and a control unit, wherein the control unit is configured to receive vehicle ignition signal; and the control unit is configured to close the protection switch when the vehicle ignition signal is received after the power supply device is connected to accumulator of the vehicle.

Abstract: A starting device for a general-purpose engine according to one embodiment includes: a starter motor; a pinion gear mounted on an output shaft of the starter motor; a camshaft gear mounted on a camshaft; a crankshaft gear mounted on a crankshaft and meshing with the camshaft gear; and a gear assembly configured to transmit a driving force of the starter motor via the pinion gear to the camshaft gear and configured not to transmit a driving force of the camshaft gear to the pinion gear. The pinion gear, the camshaft gear, the crankshaft gear, and the gear assembly are disposed in a crankcase in a state where the pinion gear meshes with a gear included in the gear assembly.

Abstract: A control method is provided for an internal combustion engine which includes a turbocharger, and which is connected to a stepped automatic transmission. The control method includes judging whether or not an upshift of the automatic transmission is performed; performing a first torque down control by an ignition timing retard of the internal combustion engine during the upshift; judging whether or not a predicted torque estimated from a driving condition of the internal combustion engine is greater than a target torque at an end of the upshift; and performing a second torque down control by the ignition timing retard of the internal combustion engine when the predicted torque is greater than the target torque.

Abstract: An ignition resumption control unit (40) is disposed that resumes control of an ignition plug (14) if a first predetermined time has elapsed or if engine rotation number has fallen below a threshold value, after receiving an engine stop signal. The ignition resumption control unit (40) executes the control of the ignition plug (14), based on resumption ignition timings (Tg(R-on)) that are timing deviating from an entire ignition timing range set in a normal working area of an engine body (2).

Abstract: An ignition system for automobile industry is disclosed. The system includes a high voltage source to initiate the spark and a low voltage source to add additional energy to the spark and the initiation of the spark and adding of the additional energy to the spark is carried out while the primary winding of the transformer is conducting. This high energy ignition system is carried out using the transformer with a secondary high voltage winding. The spark generation and adding additional energy is carried out using both capacitive and inductive transfer system using the transformer. Different ways of generating high voltage are also disclosed. Both single switch method and two switch method and multiple switch methods are also disclosed. Current controlled spark generation and multiple pulse method are also disclosed. The system delivers more energy efficiently while the primary is on and with smaller transformer and faster current rise.

Abstract: An energy recovery system for generating electric power from flow out of a gas well includes a first flow path from a well to a pipeline comprising a turbine wheel coupled to a generator and a second flow path from the well to the pipeline. The second flow path is apart from the first flow path, and includes a valve. The first and second flow paths reside on a production site of the well.

Abstract: A system in a water body uses buoyant force of gaseous Hydrogen and Oxygen to generate electrical power with one or more turbines that includes power resulting from the buoyant force while transporting the Hydrogen or Oxygen to a higher elevation, without loss of electrons, for conversion to electricity at the higher elevation. Conversion of Hydrogen and Oxygen to water through a Hydrogen Fuel Cell or by burning at the higher elevation may generate additional steam power, hydropower, or purified water. Portable submersible modules may transport the system below or above the water to and from the base of a plumbing portion of the system. The amount of gaseous fuel energy available at the higher elevation is not detrimentally impacted by the generation of electricity by the turbine.

Abstract: The present invention patent relates to a Current Energy Collection Unit (1) which is characterized in that it comprises a reaction turbine (2), which in turn is formed by blades (4) that have an elliptical arc axial profile and that are attached to the axle (5), the geometry of which is an elliptical cap, filling the entire impact zone configured by the flatted projection of the turbine (2), with a tubular enclosure structure (3) that has an internal cross-section and is split into load (6), work (7), discharge (8) and free (9).

Abstract: A hydrokinetic turbine system with dynamic tuning capabilities is disclosed. Individual hydrokinetic turbine units are dynamically tuned to accommodate changes in height and flow velocity corresponding to water in a waterway. Dynamically tuning the turbine units to accommodate waterway changes optimizes power generation output. Dynamically tuning a turbine system includes raising or lowering turbine blade height, extending or retracting turbine blade length, and narrowing or widening a turbine mouth, channel, and exit through which water flows. The hydrokinetic turbines may be arranged in an array along a waterway, and each hydrokinetic turbine in the array is connected over a controls system configured to adjust turbine characteristics at each turbine unit in the array for optimizing power generation output for the waterway in which the turbine array is installed.

Abstract: The present disclosure relates to methods (400, 500) for reducing vibrations in parked wind turbines (10), assemblies (82) comprising vibration mitigating devices (300) for wind turbine blades (22) and wind turbines (10). An assembly (82) comprises a vibration mitigating device (300) configured to be arranged around a wind turbine blade (22) of a wind turbine (10) and comprising one or more inflatable bodies (305) and one or more air flow modifying elements (310); and a pressure source (98) configured to inflate and/or deflate one or more of the one or more inflatable bodies (305) based on measurements of a sensor system (97) configured to monitor the wind turbine (10) and/or environmental conditions around the wind turbine (10).

Abstract: A segmented wind turbine rotor blade includes sleeve-shaped pressure pieces arranged between rotor blade segments, each of which is mounted on a connecting bolt. Each pressure piece includes one or more cylindrical sections and a tool engaging section for an assembly tool). Each pressure piece is connected to a corresponding connecting bolt in a form fit manner, so that a screwing force can be applied to the corresponding connecting bolt via the assembly tool via the pressure piece. A diameter of the cylindrical section(s) is less than a diameter of the tool engaging section. Each two adjacent pressure pieces are arranged rotated by 180° relative to one another.

Abstract: Provided are a method for operating a wind turbine, wherein the wind turbine has an aerodynamic rotor with at least one rotor blade which is mounted on a rotor hub of the rotor, wherein a blade angle of the at least one rotor blade can be adjusted about its longitudinal axis with respect to the rotor hub, and a corresponding wind turbine.

Abstract: The invention relates to a method for improving reporting of operational data of a wind turbine during operation thereof; said method comprising the steps of: allowing an array of sensors to sense one or more specific parameter values of said wind turbine during operation thereof; in respect of one or more sensors, transmitting said parameter value being sensed to a control system; allowing said control system to register a critical event in case a sensed parameter value, or a combination of two or more sensed parameter values, represents a situation in which it is desired to shut down the wind turbine according to one or more predetermined criteria; allowing said control system to set a specific alarm at a point in time at which a specific critical event is registered; and allowing said control system to reset said specific alarm at a point in time at which the registration of the presence of said critical event ceases; wherein each specific alarm is associated with a corresponding alarm ID; wherein said

Abstract: A method for modifying a sound emission of a wind power installation, wherein the wind power installation comprises a nacelle and a generator with a rotor which is adjustable in terms of its rotational speed, and the rotor has at least one rotor blade, the generator produces sound with at least one characteristic generator sound frequency which depends on the rotor rotational speed, the wind power installation has at least one fan for cooling the nacelle and/or generator, the at least one fan is adjustable in terms of a fan rotational speed, wherein the at least one fan produces sound with a characteristic fan sound frequency which depends on the fan rotational speed, and the fan rotational speed of the at least one fan is set in such a way on the basis of the rotor rotational speed that the fan sound frequency deviates from the at least one generator sound frequency. Tonal sounds in wind power installations, or the perception thereof, are intended to be reduced in particular.

Abstract: A friction limiting turbine gyroscope is a compact and efficient means to convert the energy of a moving fluid into electrical energy. The gyroscope's flywheel rotates when a fluid passes through its spokes while magnets located along the perimeter act upon proximate movable field coils to produce electricity. The spokes of the flywheel are optimized for the flow and density of the fluid with the ability to trans mutate using shaped memory alloys as well as rotate about their center of pressure allowing the flywheel to capture more of the energy from the fluid passing over their surfaces in all conditions. Mechanical energy losses are reduced because of the inherent stabilizing effects created by the gyroscope. Because of the stabilization, a magnetic bearing field effectively supports the gyroscope eliminating mechanical interference in rotation.

Abstract: The present disclosure is related to a device 100 configured for aligning a first hole 131 of a first flange 130 with a second hole 141 of a second flange 140. The device 100 comprises a base 101, a shaft 110 extending from the base 101 and a first and a second pusher 115, 116. The shaft 110 is configured to move between a retracted position and an extended position. The shaft 110 in the extended position extends from the first hole 131 into the second hole 141. The first and second pushers 115, 116 are also configured to be moved radially outwardly from the shaft 110 to exert pressure against an inner wall of the first and second holes 131, 141. Methods for aligning a first and a second hole 130, 140 are also provided.

Abstract: This document describes an offshore power generating system comprising a T-shaped hub connected to propeller blades and generators on a common shaft in a generator housing. The hub transfers the variable torque of the respective propeller blades, with flaps to a common shaft where generators are connected by means of couplings.

Abstract: A method and system of recovering heat from geothermal energy with a curved producing well extending around an injection well. The injection well is substantially vertical, and the producing well is helical about the injection well. The producing well extends through a plurality of geologic fractures about the injection well formed by multiple injections made through the injection well.

Abstract: A human-powered generator includes a frame and a pedal crankset and crankset sprocket rotatably mounted on the frame, a flywheel rotatably mounted on the frame including a flywheel-crankset sprocket a flywheel-countershaft sprocket, a countershaft rotatably mounted on the frame including a countershaft-flywheel sprocket and a countershaft-alternator sprocket, and an alternator including an alternator drive shaft and an alternator sprocket. The human-powered generator also includes a crankset-flywheel drive chain, a flywheel-countershaft drive chain, and a countershaft-alternator drive chain. A pedaling cadence at the pedal crankset of between approximately 60 RPM and approximately 100 RPM achieves an alternator drive shaft RPM of between approximately 2,000 RPM and approximately 5,000 RPM.

Abstract: An actuator device comprises an enclosed volume region defined by a housing body and a movable surface, such that at least a portion of the enclosed volume region is expandable from an initial volume state to an enlarged volume state. An electrically conductive porous material is disposed in the enclosed volume region, wherein the electrically conductive porous material has a mass density of from about 0.5 mg/cc to about 100 mg/cc, and wherein at least about 90% of the electrically conductive porous material is a carbonaceous material. A first electrode and a second electrode are configured to pass an electric current through the electrically conductive porous material. When an electric current is passed through the electrically conductive porous material, air disposed in the enclosed volume region expands and displaces the movable surface. A method of displacing a movable surface in an actuator device is also described.

Abstract: A shape memory alloy (SMA) actuator assembly comprising: a support structure (211); a moveable part (213) moveable relative to the support structure; at least one SMA wire (202) having a first portion and a second portion respectively attached to the support structure and the moveable part, the said SMA wire is configured to, on contraction, drive movement in the moveable part at least in a primary axis along which the shortest side of the SMA actuator assembly extends; an intermediate component (220) engaging the SMA wire at a location between the first and second portions, the second portion of the SMA wire being arranged at an oblique angle to both the primary axis and the first portion of the SMA wire.

Abstract: A variable displacement hydraulic unit with a housing in which a rotating group is housed, wherein the displacement volume of the rotating group is variably adjustable by means of a swivel element able to tilt around a tilt axis perpendicular to the rotational axis of the rotating group. The swivel element can be actuated by at least one servo unit including a servo cylinder integrated in the housing and a servo piston moveably within the servo cylinder. The head of the servo piston can be pressurized in the servo cylinder such that a movement of the servo piston coupled to the swivel element via a servo piston shaft tilts the swivel element; wherein the servo unit is located within the housing on that side of the swivel element on which no rotating group is located, and follow a working direction substantially parallel to the rotational axis of the rotating group.

Abstract: A system and a method for producing fracturing fluid, comprising: engaging an engagement coupling attached to one end of a gear box dual shaft to a gear box connector of an external gear box, wherein the external gear box is part of a pump; rotating the gear box dual shaft to drive the pump after engaging the engagement coupling with the gear box connector; disengaging the engagement coupling from the gear box connector; and rotating the gear box dual shaft without driving the pump after disengaging the engagement coupling with the gear box connector.

Abstract: A positioning process of a piston of a reciprocating compressor is applied before the beginning of a start procedure of a BLDC motor. The reciprocating compressor includes the BLDC motor having a rotor associated mechanically to the piston; a frequency inverter; a current sensor; and a processing unit having a current controller and a command unit. The switches are driven by the processing unit to control the currents applied to the phases of the motor. In each new step of the process, the value of an initial current is higher or equal to the value of the initial current of a previous step; and the value of a maximum current is higher or equal to the value of the maximum current of the previous step. The process includes adjusting the current at each position to avoid the return of the piston and mechanical oscillation in each new step.