Abstract: A power generation process is disclosed, the process comprises dissolving a solute (10) into an unsaturated stream (140) to produce a high concentration stream (130) and converting latent mixing energy present in a high concentration input stream (130) into power by passage through a power unit (20) in which the concentration of the high concentration input stream (130) is reduced. The process comprises using a reduced concentration output stream (140) derived from the high concentration input stream (130) following passage through the power unit (20) as the unsaturated stream (140). A first fraction of the high concentration stream (130) is passed to the power unit (20) for use as the high concentration input stream (130) and a second fraction of the high concentration stream (130) is output from the process.

Abstract: Disclosed is a propeller, including a main driving device. Foldable blades and a fixed propeller are detachably connected to a projecting shaft of a driving motor. When the foldable blades are arranged, the propeller can be used as a hydrofoil board booster, and be clamped to a vertical rod of the hydrofoil board. When a fixed propeller is surrounded by a water flow culvert pipe provided with water inlet grooves, the propeller can be handheld with a handheld bracket or worn to advance and play underwater. Further, the propeller can be used as a guiding device for a diving apparatus. In combination with a gas cylinder and an airbag, the propeller can also be used as a scuba gear. Together with movable and fixed hydrofoil boards, the propeller can also be used as a gliding apparatus for diving.

Abstract: An electrolyzer cell, electrolyzer setup, and related methods are provided for converting gaseous carbon dioxide to gas-phase products at elevated pressures with high conversion rates via electrolysis performed by the electrolyzer cell (100?). The electrolyzer cell (100?) is a multi-stack CO2 electrolyzer cell having individual stacks (40) that each include bipolar plate assemblies that have unique gas and fluid flow architecture formed therein.

Abstract: A utility vehicle including a plurality of ground-engaging members, a frame supported by the ground-engaging members, and a powertrain assembly supported by the frame and including an engine supported by the frame, the engine including an exhaust side and a turbocharger operably coupled to the engine, the turbocharger having a turbine housing supporting a turbine and a compressor housing supporting a compressor, the turbocharger being positioned on the exhaust side of the engine and rearward of the engine, a space between the turbocharger and the engine being less than 9 inches.

Abstract: A fluid system is provided for an aircraft engine. This fluid system includes a lubricant reservoir and a pressure relief system. The lubricant reservoir includes an internal volume. The pressure relief system includes a sensor system, a pressure relieve valve and a controller. The sensor system is configured to provide sensor data indicative of an air pressure within the internal volume. The pressure relief valve is fluidly coupled with the internal volume. The controller is configured to control operation of the pressure relieve valve based on the sensor data.

Abstract: A natural enhanced geothermal system (NAT-EGS) that uses a hot sedimentary aquifer (HSA) is disclosed. An example method may include pumping, via an extraction well, heated water from an extraction depth of a HSA, wherein the HSA satisfies a threshold geothermal characteristic. The example method may include extracting, via an energy conversion unit, heat from the heated water to capture energy, resulting in cooled water. The example method may include injecting, via an injection well, the cooled water at an injection depth of the HSA, wherein the injection depth is deeper than the extraction depth.

Abstract: An electric compressor includes a rotary shaft, a compression part, a motor including a stator, and a housing. The stator includes a stator core, coils corresponding to a plurality of phases, an insulator, coil ends, first leads of the winding wires, a neutral connection portion, and a cover member. The cover member has a cover end surface opposite from the coil ends. The cover end surface has an accommodation portion in which the neutral connection portion is accommodated. The first leads each include a covered portion, and a non-covered portion. The non-covered portion includes an extension portion continuous with the neutral connection portion extending out from the accommodation portion by a predetermined length. The cover end surface includes a first surface, and a second surface. At least the first surface has a through hole. The first surface is positioned farther from the coil ends than the second surface is.

Abstract: An engine for aeromechanical instability abatement includes a sensor configured to capture data from rotating blades of the engine system, a airflow effector device, and an engine controller. The engine controller is configured to control the airflow effector device according to a nominal schedule, detect, based on a signal from the sensor indicating a vibration amplitude of the rotating blades within a frequency band, an incipient instability condition, in response to the incipient instability condition being present, determine a modified control parameter for at least one of the airflow effector device, and control the airflow effector device according to the modified control parameter, deviating from the nominal schedule.

Abstract: An exhaust structure for an exhaust manifold includes a body including a first inlet section configured to receive exhaust gas, a second inlet section configured to receive exhaust gas, and an outlet section disposed in fluid communication with each of the first inlet section and the second inlet section to receive exhaust gas, wherein exhaust gas from the first inlet section and the second inlet section exit the exhaust structure through the outlet section, and wherein the outlet section includes a flange. The body may include a rib extending generally along the longitudinal axis and disposed on a surface of the outlet section, the rib including a first section having a first inclined surface, a second section spaced from the first section and having a second inclined surface, and a third section disposed between the first section and the second section, the third section having a curved surface.

Abstract: Turbine engine systems include a core assembly having a compressor section, a burner section, and a turbine section arranged along a shaft, with a core flow path through the turbine engine such that exhaust from the burner section passes through the turbine section and exits through a nozzle. A core condenser is arranged downstream of the turbine section and upstream of the nozzle and configured to condense water from the core flow path. A fuel cell is operably connected to the core assembly. A fuel source is configured to supply a fuel to each of the burner section for combustion and the fuel cell for reaction to generate electricity. At least one electric motor is operably coupled to the core assembly and configured to impart power to a portion of the core assembly and the fuel cell is configured to supply electrical power to the at least one electric motor.

Abstract: An apparatus to be positioned in a geothermal wellbore formed in a subsurface formation. The apparatus comprises one or more components to inject a supercritical fluid into the subsurface formation. The apparatus comprises a flow control assembly configured to control flow of the supercritical fluid into the geothermal wellbore based on a density of the supercritical fluid in the subsurface formation.

Abstract: A gas turbine engine includes a low speed spool mechanically interconnecting a low pressure turbine and at least one of a fan and a prop, a high speed spool mechanically interconnecting a high pressure turbine and a high pressure compressor, and an epicyclic gear system mechanically coupled to the high speed spool. The gas turbine engine also includes a low pressure compressor mechanically coupled to the high speed spool via the epicyclic gear system. The low pressure compressor may be mechanically independent of the low speed spool. The gas turbine engine may include a plurality of motor-generators for transferring power between the high speed spool and the low pressure compressor.

Abstract: A control system for an engine comprising a turbocharger includes, a cold light off catalyst (CLOC), a CLOC valve, and a controller. The CLOC is positioned in a bypass passage around a turbine of the turbocharger. The CLOC valve selectively routes exhaust flow from the engine between the turbine and the CLOC. The controller is configured to command the CLOC valve to operate in a CLOC mode whereby exhaust flow is routed to the CLOC; determine, based on operation in the CLOC mode, a position of the CLOC valve; determine, based on the position of the CLOC valve, an available torque of the engine; and set a maximum available engine torque based on the determined available torque of the engine.

Abstract: A foreign material exclusion system for positioning within a casing of a turbine to catch any foreign material during maintenance of the turbine. The foreign material exclusion system may include a fabric sleeve with a semicircular shape and a number of poles attached to the sleeve to maintain the sleeve in place within the turbine casing.

Abstract: Aircraft turbine engine including two coaxial annular walls defining between them a main annular duct for the flow of a primary airflow; —a rotor blading extending radially through the first duct; —an annular separator arranged downstream of the rotor blading and configured to divide the primary airflow into two to form the secondary air flows; —first variable guide vanes which are distributed around the shaft and each comprise a leading edge which is located upstream of the separator and trailing edges which are located in the secondary airflows; —and fixed guide vanes which are distributed around the shaft in the external airflow and downstream of the first variable vanes.

Abstract: An aircraft engine assembly includes a gas turbine engine having an intake channel configured to receive an incoming flow of air and form an intake flow of air, the intake channel configured to turn the received incoming flow of air from an incoming flow direction to a first axial direction of the gas turbine engine, the incoming flow direction reverse of the first axial direction, and an electric machine coupled with the low pressure shaft and located at the aft end of the gas turbine engine proximate the intake channel, the electric machine in heat exchange communication with the intake flow of air such that the electric machine transfers heat to the incoming flow of air within the intake channel when the electric machine is operated.

Abstract: A system for capturing energy from waves in a body of water comprising: an artificial beach configured to remove water flowing backwards on the artificial beach; a plurality of guide walls each comprising wave actuators configured to convert wave energy to create compressed air; a top guide extending to cover a portion of the artificial beach and configured to create pressure; an air/water reservoir configured to receive high/pressure water flowing from a normally closed check valve in the top guide when the top guide stops the momentum of the waves; a vertical pipe with a bubbler stone configured to create air bubbles to raise water head and a supply of potential energy within a top water reservoir; and a plurality pipes each comprising a turbine generator configured to receive water leaving the top water reservoir to operate the turbine.

Abstract: A system of a hybrid aircraft includes a first gas turbine engine, a second gas turbine engine, and a controller. The first gas turbine engine includes a first low spool electric machine and a first high spool electric machine. The second gas turbine engine includes a second low spool electric machine and a second high spool electric machine. The controller is operable to determine an operating mode of the hybrid aircraft and control power extraction from either or both of the first low spool electric machine and the first high spool electric machine while a single engine descent mode is active. Electric power is provided to either or both of the second low spool electric machine and the second high spool electric machine while the single engine descent mode is active to balance thrust between the first gas turbine engine and the second gas turbine engine.

Abstract: An electromagnetic brake controller for controlling a negative-actuated electromagnetic brake includes an output terminal connectable to the electromagnetic brake and a brake control section that outputs, through the output terminal, a brake control signal to be provided to the electromagnetic brake. The brake control section outputs a brake control signal for releasing the electromagnetic brake in response to a normal brake command and a safety brake command both indicating ON and outputs a brake control signal for applying the electromagnetic brake in response to at least one of the normal brake command or the safety brake command indicating OFF. The electromagnetic brake controller performs both safety control and normal control over the electromagnetic brake connected to the output terminal.

Abstract: A supply system for supplying ozone to an engine includes an electrolysis part that electrolyzes water to generate hydrogen and oxygen, a first supply part that supplies hydrogen generated by the electrolysis part to an intake pipe of the engine, an ozone generation part that generates ozone from oxygen generated by the electrolysis part, and a second supply part that supplies ozone generated by the ozone generation part to the intake pipe.