Power recovery turbines can be used debottlenecking of an existing plant, as well as recover electric power when revamping a plant. A process for recovering energy in a petroleum, petrochemical, or chemical plant is described. A fluid stream having a first control valve thereon is identified. A first power-recovery turbine is installed at the location of the first control valve, and at least a portion of the first fluid stream is directed through the first power-recovery turbine to generate electric power as direct current therefrom. The electric power is then recovered.

An electric generator assembly for an aircraft is provided. The electric generator assembly includes: a main generator having a main rotor and a main stator, the main stator includes a first three-phase winding and a second three-phase winding, the first and second three-phase windings each configured to have a voltage induced therein by the main rotor, the first three-phase winding defining a phase shift from the second three-phase winding greater than zero degrees.

Power recovery turbines can be used debottlenecking of an existing plant, as well as recover electric power when revamping a plant. A process for recovering energy in a petroleum, petrochemical, or chemical plant is described. A fluid stream having a first control valve thereon is identified. A first power-recovery turbine is installed at the location of the first control valve, and at least a portion of the first fluid stream is directed through the first power-recovery turbine to generate electric power as direct current therefrom. The electric power is then recovered.

Systems and methods associated with electrical systems of aircraft are disclosed. A method disclosed herein comprises generating electricity using an electric generator operatively coupled to an engine of the aircraft, supplying the electricity generated using the electric generator to a baseline power bus; generating electricity using an electric starter generator operatively coupled to the engine; and supplying the electricity generated using the electric starter generator to a supplemental power bus independent from the baseline power bus.

A system includes a gas turbine operational at a constant rated rotational speed, a speed sensor to measure an actual speed of the gas turbine, a turbine controller to control the gas turbine to the constant rated rotational speed, and a generator coupled with the gas turbine and rotatable to output electric power. The system also includes a DC to DC converter to output a load current on a load bus to supply a load. The DC to DC converter is supplied input electric power from the generator. The system also includes an energy storage device cooperative operable with the DC to DC converter to supply power on the load bus, and a controller to receive the actual speed and adjust an output electrical current set point of the DC to DC converter to compensate for deviation of the actual speed from the constant rated speed of the gas turbine.

A system includes a DC to DC converter coupled with a load, a power source bus coupled with an input of the DC to DC converter, and an energy storage device. The energy storage device and an output of the DC to DC converter are coupled with a load bus, which supplies the load. The power source bus is supplied power by a generator being driven by a gas turbine. During operation, an operational temperature of the gas turbine may be received by the controller. The controller may dynamically adjust a demand output of the DC to DC converter in response to the operational temperature of the gas turbine exceeding a predetermined threshold temperature value for a predetermined period of time.

Power recovery turbines can be used debottlenecking of an existing plant, as well as recover electric power when revamping a plant. A process for recovering energy in a petroleum, petrochemical, or chemical plant is described. A fluid stream having a first control valve thereon is identified. A first power-recovery turbine is installed at the location of the first control valve, and at least a portion of the first fluid stream is directed through the first power-recovery turbine to generate electric power as direct current therefrom. The electric power is then recovered.

A power generation system includes an electric generator mechanically driven by a variable speed kinetic source, a first power conversion system connected with an output of the electric generator, and a second power conversion system connected with the output of the electric generator, wherein the electric generator and power conversion systems are adapted to convert the output of the electric generator to a predetermined direct current (DC) voltage.

An aircraft electrical system including: a first DC power bus and a fuel cell assembly including a first fuel cell group, wherein the first fuel cell group is electrically coupled directly to the first DC power bus without a voltage converter to provide a first power output to the first DC power bus.

A system includes a gas turbine operational at a constant rated rotational speed, a speed sensor to measure an actual speed of the gas turbine, a turbine controller to control the gas turbine to the constant rated rotational speed, and a generator coupled with the gas turbine and rotatable to output electric power. The system also includes a DC to DC converter to output a load current on a load bus to supply a load. The DC to DC converter is supplied input electric power from the generator. The system also includes an energy storage device cooperative operable with the DC to DC converter to supply power on the load bus, and a controller to receive the actual speed and adjust an output electrical current set point of the DC to DC converter to compensate for deviation of the actual speed from the constant rated speed of the gas turbine.