Disclosed are a hybrid power generation facility and a control method thereof. 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 GT (gas turbine) generator configured to generate electric power using a driving force generated by the gas turbine, a boiler including a combustion chamber and configured to mix the first combustion gas supplied from the turbine of the gas turbine with air and fuel supplied from the outside, a steam turbine through which steam generated in the combustion chamber passes, a ST (steam turbine) generator configured to generate electric power using a driving force generated by the steam turbine, and an energy storage system configured to be charged based on a decrease rate of power demand of a grid and a maximum decrease rate of power supply from the GT generator and the ST generator.

A housing for a gas turbine engine accessory includes an enclosure having a drive end with an opening and a closure. The closure is seated in the opening, defines therethrough a shaft aperture and has a v-band flange extending about a periphery of the closure to limit load carried by the enclosure when the engine accessory is mounted to an accessory gearbox mount in a cantilevered arrangement. Engine accessories for gas turbine engines and mounting arrangements for gas turbine engine accessories are also described.

Fault-tolerant radial flux rotary electric machines are provided. One such machine comprises: a permanent magnet rotor having fourteen poles; and an alternate-wound stator having sixteen slots and four coil pairs, each coil pair forming part of one of four independent electrical phases.

The electrical power generation system including a micro-turbine alternator. The micro-turbine alternator including a combustor, at least one turbine configured to be driven by an exhaust from the combustor, at least one compressor operably connected to the combustor to provide a compressed airflow to the combustor, one or more shafts connecting the at least one turbine to the at least one compressor such that rotation of the at least one turbine drives rotation of the at least one compressor, and a recuperator configured to transfer heat from the exhaust exiting the at least one turbine to the compressed airflow from the at least one compressor entering the combustor.

A power generation system includes one or more micro-turbine electric generators (“MTEGs”). The MTEGs include a housing having an inlet for receiving pressurized gas and an outlet for releasing expanded gas. The MTEGs also include a rotor, a user-replaceable nozzle for directing pressurized gas over blades of the rotor, and a stator for generating alternating current (“AC”) responsive to rotation of the rotor. The power generation system also includes a programmable logic controller (“PLC”) coupled to the MTEGs that operates flow control valves (“FCVs”) coupled to the MTEGs to modulate the flow of gas to the MTEGs to generate output power suitable to support an electrical load. The system also includes power conversion circuitry configured to convert AC generated by the MTEGs to direct current (“DC”) and to provide the DC to an electrical load. The system also includes a skid for mounting multiple and MTEGs and FCVs.

Gas turbine engines and methods of starting gas turbine engines, the gas turbine engine including: an electronic engine controller; one or more spools designated a starting spool for starting the engine, and has a required starting torque τs; a permanent magnet alternator mechanically coupled with the starting spool, the alternator, in a motor mode, provides a peak torque of τa, and, in a generator mode, generates electrical power for the electronic engine controller; and an electrical starter-generator mechanically coupled with the starting spool. The starter-generator in a motor mode, provides a peak torque of τsg, and, in a generator mode, generates electrical power for an external load. τsg+τa≥τs and τsg, τa<τs, and the electronic engine controller, during a start procedure, operates both the permanent magnet alternator and the starter-generator in a motor mode to drive the starting spool.

Gas turbine engines and methods of starting gas turbine engines, the gas turbine engine including: an electronic engine controller; one or more spools designated a starting spool for starting the engine, and has a required starting torque τs; a permanent magnet alternator mechanically coupled with the starting spool, the alternator, in a motor mode, provides a peak torque of τa, and, in a generator mode, generates electrical power for the electronic engine controller; and an electrical starter-generator mechanically coupled with the starting spool. The starter-generator in a motor mode, provides a peak torque of τsg, and, in a generator mode, generates electrical power for an external load. τsg+τa≥τs and τsg, τa<τs, and the electronic engine controller, during a start procedure, operates both the permanent magnet alternator and the starter-generator in a motor mode to drive the starting spool.

Various embodiments that pertain to fuel processing are described. A fuel processor can produce an endothermic reaction that cools a substance and produces a processed fuel from a raw fuel. A generator can employ the processed fuel to produce an electricity. The generator can supply the electricity to a load that uses the electricity to function. The load can become hot due to its functioning and can benefit from being cooled. The substance cooled by the fuel processor can cool load and in the process the substance can rise in temperature. This warmer substance can be transferred to the fuel processor to be cooled again and this cycle can continue. Further, the fuel processor can use the warmer substance to achieve the endothermic reaction.

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 hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.