A turbine and a turbine-generator device for use in electricity generation. The turbine has a universal design and so may be relatively easily modified for use in connection with generators having a rated power output in the range of 50 KW to 5 MW. Such modifications are achieved, in part, through use of a modular turbine cartridge built up of discrete rotor and stator plates sized for the desired application with turbine brush seals chosen to accommodate radial rotor movements from the supported generator. The cartridge may be installed and removed from the turbine relatively easily for maintenance or rebuilding. The rotor housing is designed to be relatively easily machined to dimensions that meet desired operating parameters.

An aircraft power system includes an auxiliary power unit (APU), a generator, and a constant speed drive (CSD). The APU drives an APU drive shaft at a first rotational speed during a first condition and a second rotational speed during a second condition. The generator is rotatably coupled to a generator shaft and produces an AC voltage having a target frequency in response to rotation of the generator shaft at a target rotational speed. The CSD unit receives the first rotational speed from the APU drive shaft and rotates the generator shaft at the target rotational speed based on the first rotational speed. The CSD further receives the second rotational speed from the APU drive shaft and rotates the generator shaft at the target rotational speed based on the second rotational speed.

A turbogenerator includes a stator core defining a first end and a second end, a plurality of stator bars disposed within the stator core, each stator bar including a coolant flow path, and a parallel ring having a first segment and a second segment separate from the first segment. The parallel ring is coupled to the first end of the stator core and is arranged to electrically connect the plurality of stator bars and to fluidly connect the coolant flow paths of the plurality of stator bars. A tang includes a main chamber, a first coolant opening, a second coolant opening, and a distribution channel that fluidly interconnects the main chamber, the first coolant opening, and the second coolant opening. A first lead tube has a first lead end connected to the first coolant opening and a second lead end connected to the first segment, and a second lead tube separate from the first lead tube has a first lead end connected to the second coolant opening and a second lead end connected to the second segment. The plurality of stator bars, the parallel ring, the tang, the first lead tube, and the second lead tube cooperate to define a portion of a circuit and a portion of a cooling path.

A system includes a clutchless synchronous condensing coupling configured to couple a turbine shaft of a gas turbine system to a generator shaft of a synchronous generator of a power generation system. The clutchless synchronous condensing coupling includes a first coupling portion configured to couple to the turbine shaft, and a second coupling portion configured to couple to the generator shaft. The clutchless synchronous condensing coupling is configured to allow the power generation system to operate in an active power mode and a reactive power mode without a clutch assembly.

An aircraft electrical power generation system includes an AC generator having a rotor including a plurality of electromagnetic rotor-windings and stator including plurality of electrical stator-windings. The rotor mechanically coupled to a shaft of a gas turbine engine by transmission-system. The generator includes a frequency controller, a torque sensor determining a torque on the transmission-system by the generator and controller to operate the system in first and second modes. In first mode, the power output frequency of the generator controlled by the frequency controller within limits, and reduced idle signal going to a turbine engine controller. In second mode, the power output frequency of the generator not controlled by the frequency controller and increased idle signal going to the turbine engine controller. The controller operates the system in first mode when the torque is below a limit, and in second mode when the torque is above a limit.

A turboelectric generator system includes a gas turbine engine which includes, in fluid flow series, a gas-generator compressor, a combustor, a gas-generator turbine, and a variable-speed free power turbine. The system further comprises a variable-frequency electric machine rotatably connected with the free power turbine and a power converter configured to convert a variable frequency electrical output from the electric machine to a fixed frequency output.

An aircraft power system includes an auxiliary power unit (APU), a transmission unit, and a generator. The APU is configured to output a first APU rotational power in response to determining a first condition and a second APU rotational power in response to a determining a second condition. The transmission unit is configured to receive the first APU rotational output power from the APU. The transmission unit outputs a transmission rotational power based on the first APU rotational output power and outputs the transmission rotational power based on the second APU rotational output power. The generator receives the transmission rotational power and produces an alternating current (AC) voltage having a target frequency based on the transmission rotational power.

A first turboexpander generator defines a portion of a first conduit flow passage. The first turboexpander generator is configured to decrease a temperature or pressure of a process stream flowing through the first turboexpander generator by generating electrical power from the process stream. A second turboexpander generator defines a portion of a second conduit flow passage. The second turboexpander generator is configured to decrease a temperature or pressure of a process stream flowing through the second turboexpander generator by generating electrical power from the process stream. The first and second conduit flow passages are arranged to carry fluid flow in parallel to one another. The first and the second turboexpander generator are substantially identical in critical dimensions and performance.

An aircraft power system includes an auxiliary power unit (APU), a transmission unit, and a generator. The APU is configured to output a first APU rotational power in response to determining a first condition and a second APU rotational power in response to a determining a second condition. The transmission unit is configured to receive the first APU rotational output power from the APU. The transmission unit outputs a transmission rotational power based on the first APU rotational output power and outputs the transmission rotational power based on the second APU rotational output power. The generator receives the transmission rotational power and produces an alternating current (AC) voltage having a target frequency based on the transmission rotational power.

A turbogenerator includes a stator core defining a first end and a second end, a plurality of stator bars disposed within the stator core, each stator bar including a coolant flow path, and a parallel ring having a first segment and a second segment separate from the first segment. The parallel ring is coupled to the first end of the stator core and is arranged to electrically connect the plurality of stator bars and to fluidly connect the coolant flow paths of the plurality of stator bars. A tang includes a main chamber, a first coolant opening, a second coolant opening, and a distribution channel that fluidly interconnects the main chamber, the first coolant opening, and the second coolant opening. A first lead tube has a first lead end connected to the first coolant opening and a second lead end connected to the first segment, and a second lead tube separate from the first lead tube has a first lead end connected to the second coolant opening and a second lead end connected to the second segment. The plurality of stator bars, the parallel ring, the tang, the first lead tube, and the second lead tube cooperate to define a portion of a circuit and a portion of a cooling path.