An energy recovery apparatus for use in a refrigeration system, comprises an intake port, a nozzle, a turbine and a discharge port. The intake port is adapted to be in fluid communication with a refrigerant cooler of a refrigeration system. The nozzle comprises a fluid passageway. The nozzle is configured to increase velocity of the refrigerant as it passes through the fluid passage -way. The turbine is positioned relative to the nozzle and configured to be driven by refrigerant discharged from the fluid passageway. The discharge port is downstream of the turbine and is configured to be in fluid communication with an evaporator of the refrigeration system.

The present invention discloses a turbine fracturing equipment, including a transporter, a turbine engine, a reduction gearbox, a transmission mechanism and a plunger pump, wherein an output end of the turbine engine is connected to one end of the reduction gearbox, the other end of the reduction gearbox is connected to the plunger pump through a transmission mechanism; the transporter is used to support the turbine engine, the reduction gearbox, the transmission mechanism and the plunger pump; the transporter includes a chassis provided with a transport section, a bearing section and a lapping section which are connected in sequence; while the turbine fracturing equipment is in a working state, the bearing section can contact with the ground, while the turbine fracturing equipment is in a transport state, the bearing section does not contact with the ground. Beneficial effects: the equipment adopts a linear connection and a special chassis design, so that the center of gravity is double lowered to guarantee its stability and safety, the structure is simpler, the investment and operation costs are decreased, the risk of total breakdown of the fracturing site is reduced, and the equipment has a good transmission performance and is suitable for continuous operation conditions with long time and heavy load.

A magnetic coupling may include a stator having a first axial portion which merges with a second axial portion along an axial direction, the second axial portion being adjustable relative to the first axial portion along a circumferential direction. The magnetic coupling may also include a first rotor and a second rotor each rotationally adjustable relative to the stator about a rotational axis which runs along an axial direction, the second rotor arranged concentrically with respect to the first rotor. The first axial portion, the second axial portion, and the first and second rotors may each include respective magnet elements arranged in pairs having alternating magnetic polarity along the circumferential direction.

A magnetic coupling may include a stator having a first axial portion which merges with a second axial portion along an axial direction, the second axial portion being adjustable relative to the first axial portion along a circumferential direction. The magnetic coupling may also include a first rotor and a second rotor each rotationally adjustable relative to the stator about a rotational axis which runs along an axial direction, the second rotor arranged concentrically with respect to the first rotor. The first axial portion, the second axial portion, and the first and second rotors may each include respective magnet elements arranged in pairs having alternating magnetic polarity along the circumferential direction.

A cryogenic liquid expansion turbine has a turbine wheel mounted on a rotary shaft, at least one radial inlet for cryogenic liquid to be expanded in the expansion turbine for the rotary shaft, and a dry gas sealing means at a position along the rotary shaft between the turbine wheel and the bearings. There is a thermal barrier member between the turbine wheel and the dry gas sealing means, a gas chamber on the dry gas sealing means side of the thermal barrier member, and an internal passage for cryogenic gas to the said gas chamber. A method is also provided.

The present disclosure is directed to an aircraft power generation system including a reverse Brayton cycle system, a gas turbine engine, and a gearbox. The gas turbine engine includes a compressor section, a turbine section, and an engine shaft. The compressor section is arranged in serial flow arrangement with the turbine section. The engine shaft is rotatable with at least a portion of the compressor section and with at least a portion of the turbine section. The reverse Brayton cycle system includes a compressor, a driveshaft, a turbine, and a first exchanger. The driveshaft is rotatable with the compressor or the turbine, and the compressor, the first heat exchanger, and the turbine are in serial flow arrangement. The gearbox is configured to receive mechanical energy from the engine shaft and transmit mechanical energy to the reverse Brayton cycle system through the driveshaft.

A compressor according to an exemplary aspect of the present disclosure includes, among other things, a rotor configured to rotate with respect to a stator, the stator having an abradable portion. At least one labyrinth seal is between the rotor and the stator, wherein the labyrinth seal comprises a plurality of teeth extending from the rotor toward the abradable portion.

A convertible ducted fan engine having a shroud, a drive shaft connected to a mechanical fan, and a rotational drive motor configured to rotate the mechanical fan. An embodiment includes a linear drive motor configured to translate the drive shaft and mechanical fan in a direction parallel to a longitudinal axis of the shroud. The convertible ducted fan engine includes a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow, and a drive-wheel configuration in which the shroud rotates about the rotational axis.

A convertible ducted fan engine having a shroud, a drive shaft connected to a mechanical fan, and a rotational drive motor configured to rotate the mechanical fan. An embodiment includes a linear drive motor configured to translate the drive shaft and mechanical fan in a direction parallel to a longitudinal axis of the shroud. The convertible ducted fan engine includes a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow, and a drive-wheel configuration in which the shroud rotates about the rotational axis.

Disclosed is a hybrid power generation facility. The hybrid power generation facility includes a gas turbine including a compressor configured to compress air introduced from an outside, a combustor configured to mix the compressed air with fuel and to combust the air and fuel mixture, and a turbine configured to produce power with first combustion gas discharged from the combustor, a boiler configured to burn a mixture of the first combustion gas and air, a first water heat exchanger configured to pass second combustion gas discharged from the boiler and to heat water through heat exchange to between the water and the second combustion gas, a water supply device configured to supply water to the first water heat exchanger, a steam turbine through which steam generated in the boiler passes, and a fuel heat exchanger configured to pass fuel supplied to the combustor and to pass a portion of water that is returned to the water supply device from the first water heat exchanger and has a higher temperature than the water supplied to the first water heat exchanger.