The present invention provides a compressor system including a plurality of compressor trains each including a gas turbine and a compression part including a compressor driven by the gas turbine, and a fluid feeding part for distributing a fluid fed from one fluid source to each of the compressors in the plurality of compressor trains. The gas turbine includes a gas turbine compressor for compressing air, a combustor for generating a combustion gas, a high-pressure turbine including a high-pressure turbine rotor mechanically coupled to a compressor rotor, and a low-pressure turbine including a low-pressure turbine rotor disposed away from the high-pressure turbine rotor. The plurality of compressor trains can be operated in parallel.

The present disclosure is directed to turbine engines and systems for active stability control of rotating compression systems utilizing an electric machine operatively coupled thereto. In one exemplary aspect, an electric machine operatively coupled with a compression system, e.g., via a shaft system, is controlled to provide shaft damping for instability fluctuations of the pressurized fluid stream within the compression system. Based on control data indicative of a system state of the compression system, a control parameter of the electric machine is adjusted to control or change an output of the shaft system. Adjusting the shaft system output by adjusting one or more control parameters of the electric machine allows the compression system to dampen instability fluctuations of the fluid stream within the compression system. A method for active stability control of a compression system operatively coupled with an electric machine via a shaft system is also provided.

A self-rotation graphene heat-dissipation device for a direct-drive electro-hydrostatic actuator, that includes inner and outer walls of a shell eccentrically arranged relative to each other, the shell sleeves on an outer side of a self-rotation mechanism. The self-rotation mechanism is arranged on an outer side of a shaft; the shaft is coaxial with the inner wall of the shell and connected with outer and inner end covers. The self-rotation mechanism includes a rotor and blades, the rotor sleeves on the shaft and is connected with the outer and inner end covers. The rotor is slidably connected with the blades, and outer walls of the blades are closely attached to the inner wall of the shell. Graphene heat-dissipation layers are coated on outer walls of all of the shell, blades, the rotor, the inner and outer end covers respectively.

An air cycle machine is provided. The air cycle machine can be included an environmental control system of an aircraft. The air cycle machine can include a turbine comprising a plurality of inlet gas flow paths, a compressor driven by the turbine from a shaft, and a fan driven by the turbine from the shaft.

An electric fan for producing thrust to propel an aircraft is disclosed. The electric fan comprises a stator, a fan rotor rotatably mounted relative to the stator and an electric motor mounted to the stator and drivingly engaged with the fan rotor to cause rotation of the fan rotor relative to the stator. The fan rotor comprises an annular body defining a flow passage therethrough and a plurality of fan blades disposed in the flow passage and mounted for common rotation with the annular body about a fan rotation axis. The electric motor has a motor rotation axis that differs from the fan rotation axis.

A charge gas compressor train for an ethylene plant includes: a steam turbine; and a compression unit that is configured to be driven by the steam turbine to compress a charge gas. The compression unit includes a closed impeller at each impeller of a plurality of compression stages. An outer diameter of blades of the closed impeller at least at an initial stage of the plurality of compression stages is 1,400 to 1,800 mm. A maximum operating peripheral speed of the blades of the closed impeller at the initial stage at an outermost diameter position is 350 to 400 m/s. An output of the charge gas compressor train is 100 to 140 MW.

A charge gas compressor train for an ethylene plant includes: a steam turbine; and a compression unit that is configured to be driven by the steam turbine to compress a charge gas. The compression unit includes a closed impeller at each impeller of a plurality of compression stages. An outer diameter of blades of the closed impeller at least at an initial stage of the plurality of compression stages is 1,400 to 1,800 mm. A maximum operating peripheral speed of the blades of the closed impeller at the initial stage at an outermost diameter position is 350 to 400 m/s. An output of the charge gas compressor train is 100 to 140 MW.

An electric fan for producing thrust to propel an aircraft is disclosed. The electric fan comprises a stator, a fan rotor rotatably mounted relative to the stator and an electric motor mounted to the stator and drivingly engaged with the fan rotor to cause rotation of the fan rotor relative to the stator. The fan rotor comprises an annular body defining a flow passage therethrough and a plurality of fan blades disposed in the flow passage and mounted for common rotation with the annular body about a fan rotation axis. The electric motor has a motor rotation axis that differs from the fan rotation axis.

A method for handling the shutdown of a turbomachine string installed in a plant for the liquefaction of a gaseous product comprising at least two turbomachine strings comprises the steps of detecting the shutdown of a first turbomachine string; promptly increasing the driving torque on a shaft of a second turbomachine string when the shutdown is detected; maintaining the driving torque increase on the shaft of the second turbomachine string until a preset speed of the motor driver is reached or a predetermined period of time expires.

A method for handling the shutdown of a turbomachine string installed in a plant for the liquefaction of a gaseous product comprising at least two turbomachine strings comprises the steps of detecting the shutdown of a first turbomachine string; promptly increasing the driving torque on a shaft of a second turbomachine string when the shutdown is detected; maintaining the driving torque increase on the shaft of the second turbomachine string until a preset speed of the motor driver is reached or a predetermined period of time expires.