Abstract: A system for actuating fluid flow is disclosed. The system includes a fluid actuator, an electric motor for driving the fluid actuator, a motor controller for controlling the motor, a local energy storage device for powering the motor, a stability monitor that assesses instability of operation of the fluid actuator, and a mitigation control that mitigates instability of the fluid actuator via the motor controller based on the assessment of the stability monitor, wherein a response time of the mitigation is faster than changes in fluid flow in the system during fluid actuation.

Abstract: A hermetic compressor including a casing; a motor inside the casing, and including a rotor and stator; a drive shaft that rotates with the rotor; a compression unit below the motor to compress refrigerant and discharge compressed refrigerant to an inside of the casing; and an oil blocking guide above the motor to rotate with the rotor. The oil blocking guide includes an oil blocking plate formed in a disk shape, an oil guide part extending outward and upward from an edge of the oil blocking plate, and a support part connecting the oil blocking plate to the drive shaft and space the oil blocking plate from the rotor. The oil blocking plate and the oil guide part block upward movement of oil passing through the motor, and guide the oil to an inner circumferential surface of the casing through centrifugal force while the oil blocking guide is rotating.

Abstract: Disclosed is an air supply system (100) for supplying air to an outside of a hull (201) of a vessel (200). The vessel comprises an engine. The air supply system comprises one or more turbocharger(s) (10) for supplying a compressed main air flow to the engine of the vessel via a respective first flow path (11A). The air supply system comprises an exhaust gas recirculation (EGR) system for recirculating exhaust gas into the compressed main airflow supplied to the engine via a second flow path (11B). The air supply system comprises a third flow path (11C) for supplying a sub-flow of compressed air to one or more Air Discharge Units (ADUs). The EGR system comprises a blower (31) arranged in the second flow path (11B) for supplying exhaust gas to the engine. The first flow path and the second flow path have a first connecting path (11AB) upstream of the blower (31) and a second connecting path (11BA) downstream of the blower.

Abstract: A turbine includes a turbine housing having a scroll flow passage and a gas inflow passage fluidly coupled to the scroll flow passage, and a variable nozzle assembly located inside the turbine housing. The variable nozzle assembly includes a plurality of nozzle vanes located in the gas inflow passage and a plurality of vane shafts separately fixed to the nozzle vanes. The plurality of nozzle vanes includes a first nozzle vane and a number of second nozzle vanes. A width of the first nozzle vane in an axial direction of the vane shafts is smaller than a width of each of the second nozzle vane in the axial direction of the vane shafts.

Abstract: A car having two front wheels; two rear drive wheels; a supercharged internal combustion engine which is provided with a plurality of cylinders with which respective pistons slide and a drive shaft connected to the pistons; a compressor configured to compress air suited to be sucked by the supercharged internal combustion engine; a transmission which is interposed between the internal combustion engine and the rear drive wheels and has: a drum which is brought into rotation by the drive shaft, at least one clutch contained in the drum to receive the motion from the drum, and a primary shaft connected to the clutch; and an actuating system which connects the drum of the transmission to the first compressor so as to receive the motion from the drum of the transmission to cause the rotation of the first compressor.

Abstract: A recirculation fan turbocharger assembly (23) recycles hydrogen and supplies air in a fuel cell system. The assembly (23) includes a fan (25), a compressor (27), and an electric drive (31) and/or a turbine (29). The fan (25) has an impeller (255) which is designed to convey a hydrogen containing recycle stream (250) to a fuel cell unit (1). The compressor (27) has a compressor wheel (275) which is designed to compress an air stream (270) for a fuel cell unit. The compressor wheel (275) and the impeller (255) are coupled to one another in a rotationally fixed manner. The electric drive (31) and/or a turbine (29) is/are designed to drive the impeller (255) and the compressor wheel (275) simultaneously.

Abstract: A compressor and a moving scroll thereof includes a moving scroll wall integrally formed at a first side of a moving base plate, the moving scroll wall extending around an axis. A collection groove is disposed on an end face of the moving scroll wall, the end face being located at the end of the moving scroll wall that is opposite the moving base plate in the direction of the axis. A channel running in the direction of the axis is disposed between the collection groove and a second side, the channel and the collection groove being connected at a first port, and the channel running through the second side at a second port. The collection groove extends not less than 60 degrees and not more than 400 degrees around the axis from the first port to the collection end.

Abstract: A reconfigurable hybrid solar gas turbine system includes a turbocharger (TC), a gas turbine engine, and a solar energy module. The TC and engine each include a compressor and a turbine joined by a turboshaft. The engine further includes a burner, a mixer, a generator, and a flow control valve. The system operates in a semi-open cycle in which the TC receives inlet ambient air. The burner receives pressurized air from the TC and fuel, for example from an NG source. The mixer combines hot gas flows from both the burner and the solar energy module to form a combined flow, whose mixing ratio is determined by a position of the flow control valve, thereby reconfiguring the system in response to variations in incident solar irradiance. Electrical power is generated by the engine generator and an optional TC generator. The engine and/or solar energy module may include a recuperator.

Abstract: Various examples of the present disclosure provide aircraft engine sensing apparatuses and methods of manufacturing aircraft engine sensing apparatuses. For example, an example aircraft engine sensing apparatus includes an aircraft engine sensor, a plurality of connection wires, and at least one ceramic insulator. In some examples, the aircraft engine sensor is positioned within an aircraft engine. In some examples, the plurality of connection wires connect the aircraft engine sensor to a sensor connector. In some examples, the plurality of connection wires are positioned within a wire protection housing. In some examples, the at least one ceramic insulator is positioned within the wire protection housing and defines a plurality of insulator openings. In some examples, each of the plurality of connection wires passes through one of the plurality of insulator openings.

Abstract: A rotary compressor provided that may include a casing, a cylinder, a roller, and at least one vane slidably inserted into the roller, and the roller may have at least one bypass passage through which spaces on both sides of a contact point based on a rotational direction of the roller communicate with each other. Through the at least one bypass passage, residual refrigerant remaining in a compression space even after a discharge stroke may be bypassed to a suction chamber, thereby minimizing the refrigerant remaining in the compression space after the discharge stroke. Also, loss due to overcompression in a residual space may be suppressed or prevented while reducing suction loss due to the introduction of overcompressed high-pressure refrigerant by the bypassing the refrigerant in the residual space toward a suction side in advance.

Abstract: Systems and methods for multi-modal representation learning are described. One or more embodiments provide a visual representation learning system trained using machine learning techniques. For example, some embodiments of the visual representation learning system are trained using cross-modal training tasks including a combination of intra-modal and inter-modal similarity preservation objectives. In some examples, the training tasks are based on contrastive learning techniques.

Abstract: A turbine engine includes a rotor, a stator, and a seal assembly disposed between the rotor and the stator. The seal assembly includes seal segment. The seal segment includes a seal face that is configured to form a fluid bearing with the rotor. A lift channel extends within the seal segment from an opening on the seal face. The turbine engine further includes a spring assembly disposed within the lift channel. The spring assembly including a biasing element and a piston element coupled to the biasing element. The lift channel includes a lift volume portion extending is between the opening and the piston element. The piston element is movable within the lift channel based on a pressure within the fluid bearing to adjust a size of the lift volume portion.

Abstract: A scroll compressor for generating oil-free compressed air, in particular for a compressed air brake system of a lorry, with a drive which is arranged in a housing and is connected to an orbiting displacer scroll which has a displacer scroll bottom and a displacer scroll wall. The displacer scroll wall engages into a stationary mating scroll, with the result that at least one variable compression chamber is formed between the displacer scroll and the mating scroll. A seal element is provided between the displacer scroll and the housing wherein the seal element is fastened in the displacer scroll bottom and seals against a sliding plate which is connected fixedly to the housing. A compressed air brake system with a scroll compressor of this type.

Abstract: A rotary internal combustion engine includes a housing, a front cover, a rear cover, and a rotor. The rotor contains 2 or more pair of radially arranged, synchronously geared, crank shafts. The main journal of every other crankshaft has a timing gear at one end and a drive gear at the other. The timing gears mesh with a stationary sun gear fixed to the front cover. The rotor contains radial cylinder bores, each with a piston and connecting rod operably connected to each crankshaft. An output shaft with a sun gear pierces the center of the rotor and meshes with the drive gears. The rotor revolves around the output shaft within the housing which contains ports for intake, fuel delivery, spark, and exhaust. The crankshafts rotate at twice the rate of the rotor, thus producing four piston strokes per revolution of the rotor.

Abstract: Systems and apparatuses are disclosed that comprise or utilize a hydraulic vane device. This device can be configured with a ring and/or a rotor shaped and positioned relative to one another to provide the hydraulic vane device with four or more chambers in which the vanes of the device can work a hydraulic fluid.

Abstract: A fan assembly for a clothes treatment device and a clothes treatment device. The fan assembly includes an air passage housing defining an installation cavity; an impeller rotatably provided in the installation cavity; and a motor provided in the air passage housing and including a stator and a rotor. The stator is fitted over an outside of the rotor, and the rotor is configured to drive the impeller to rotate. The motor extend towards an upper cover of the clothes treatment device and/or an inner wall of the air passage housing. A distance between an upper end of the motor and the upper cover is h1, and the h1 is greater than or equal to 5 mm. A distance between a lower end of the motor and the inner wall of the air passage housing in a vertical direction is h2, and the h2 is greater than or equal to 0.5 mm.

Abstract: A control system comprising: a liquid ring pump; a motor configured to drive the liquid ring pump; and a controller configured to: determine an electrical current within the motor; determine a speed of the motor; calculate a value of a function, the function being a function of the determined electrical current within the motor and the determined speed of the motor; and output one or more control signals based on the calculated value of the function.

Abstract: A sealing structure seals a space between first and second parts of a fan duct and a fairing of an aircraft engine. The sealing structure comprises first and second seal portions for positioning between the first and second parts of the fan duct and the fairing. The first seal portion includes an elongated middle region and a first coupling mechanism. The elongated middle region can be secured to the first part of the fan duct and abutting the fairing and includes a forward end from which the first coupling mechanism extends. The second seal portion includes an elongated middle region and a second coupling mechanism. The elongated middle region can be secured to the second part of the fan duct and abutting the fairing and includes a forward end from which the second coupling mechanism extends. The second coupling mechanism is operable to couple to the first coupling mechanism.

Abstract: An engine housing includes a rotor housing and a side housing assembly. The rotor housing extends about an axis to form a rotor cavity of the engine housing. The side housing assembly includes a side housing body, a side plate, and an impingement cooling assembly. The side plate is disposed between the rotor housing and the side housing body. The side plate forms the rotor cavity. The impingement cooling assembly includes a first baffle plate. The first baffle plate is disposed between the side housing body and the side plate. The side housing body, the side plate, and the first baffle plate form a coolant passage. The coolant passage includes an inlet plenum and a plurality of impingement cooling holes. The first baffle plate forms the plurality of impingement cooling holes. Each impingement cooling hole of the plurality of impingement cooling holes is disposed at the inlet plenum.

Abstract: An aircraft engine, has: a shaft rotatable about a central axis; a housing mounted around the shaft; and a seal assembly disposed radially between the shaft and the housing relative to the central axis, the seal assembly having: a sealing ring mounted to the housing, and a seal runner secured to the shaft, the seal runner extending radially relative to the central axis from an inner face facing the shaft to an outer face facing the sealing ring and being radially spaced apart from the sealing ring by a gap, the seal runner having an inner section extending from the inner face towards the outer face, and an outer section extending from the outer face towards the inner face, a density of the outer section being less than that of the inner section, the density defined as a mass per unit of volume of the seal runner.