A mechanical flywheel used to power an aircraft system. In one example, the flywheel is used to rotate a rotor shaft in the aircraft's engine and prevent bowing of the rotor shaft caused by a thermal gradient. In another example, the mechanical flywheel provides electrical power at peak demand times. In yet another example, the flywheel is used as a load source or sink by the engine's control system so as to aid engine operability and engine acceleration rates during abnormal flight conditions.

The present disclosure is directed to a gas turbine engine structure and method for reducing or mitigating bowed rotor. The method includes coupling a rotor assembly to a mechanical energy storage device via a clutch mechanism when the rotor assembly is at or below a speed limit below an idle speed condition; storing mechanical energy at the mechanical energy storage device via rotation of the rotor assembly at or below the speed limit; releasing mechanical energy from the mechanical energy storage device to rotate the rotor assembly following shutdown of the gas turbine engine; and rotating the rotor assembly via the mechanical energy from the mechanical energy storage device.

A flywheel energy storage device includes the Halbach Motor/Generator with rolling biphasic coil control, continuously variable torque transfer via magnetic induction and a reluctance magnetic levitation system known as the Axial-Loading Magnetic Reluctance Device. Electric energy input turns the magnetically coupled rotors of the Halbach motor, and torque is transferred to a flywheel through a copper cylinder variably inserted between the Halbach magnet rotors. In idle mode, the energy is stored kinetically in the spinning flywheel, which is levitated by a permanent magnet bearing. Electric energy output is achieved by transferring torque from the flywheel through the copper cylinder to the rotors of the Halbach Generator by magnetic induction. Rolling biphasic motor control includes dividing Halbach motor coils into increments, then energizing groups of contiguous increments into virtual coils, which revolve in tandem with the magnet rotors so to achieve continuous and optimal torque.

A gas turbine engine includes a compressor. A turbine is mechanically connected to the compressor by a shaft. An air-driven auxiliary turbine is in fluid communication with the compressor and is configured to receive pressurized air from the compressor. An auxiliary generator is operably connected to the auxiliary turbine. The auxiliary generator is configured to generate electrical energy in response to an operation of the auxiliary turbine. An energy storage device is in electrical communication with the auxiliary generator.

A power generating unit, control unit and modular power generating system. A power generating unit includes an engine-generator set including an engine that produces mechanical power and a generator mechanically coupled to the engine. The generator converts the mechanical power to electrical power provided to a DC link. The control unit includes at least one controller configured to control fuel flow to the engine based on a voltage of the DC link.

Turbine-generator systems having an auxiliary power source and methods of operating turbine-generator systems having auxiliary power sources in a high, intermittent load environment are provided. The turbine may be sized to meet substantially all the power required by the intermittent load. The auxiliary power source may have a power rating approximately equal to the power required to rotate the unloaded generator at an operational speed. The method may include decoupling the turbine from the generator, removing the load from the generator, coupling the auxiliary power source to the unloaded generator, and maintaining the operational rotational speed of the generator with the auxiliary power source.

An embodiment of a pumping unit includes a gas turbine engine, an enclosure housing the engine, an exhaust assembly connected to the engine, an air intake duct connected to the engine, and an air treatment system connected to the air intake duct. The air treatment system including one or more inlet pre-cleaners configured to eject debris. Each of the inlet pre-cleaners having a cylindrical tubular portion configured to channel air toward the air intake duct. In addition, the pumping unit includes a gearbox operatively coupled to the engine and a drive shaft having a first end operatively coupled to the gearbox. Further, the pumping unit includes a pump comprising an input shaft operatively coupled to a second end of the drive shaft, wherein the engine, the gearbox, the drive shaft, and the pump are disposed along a longitudinal axis of the pumping unit.

A mechanical flywheel used to power an aircraft system. In one example, the flywheel is used to rotate a rotor shaft in the aircraft's engine and prevent bowing of the rotor shaft caused by a thermal gradient. In another example, the mechanical flywheel provides electrical power at peak demand times. In yet another example, the flywheel is used as a load source or sink by the engine's control system so as to aid engine operability and engine acceleration rates during abnormal flight conditions.

An embodiment of a pumping unit includes a gas turbine engine, an enclosure housing the engine, an exhaust assembly connected to the engine, an air intake duct connected to the engine, and an air treatment system connected to the air intake duct. The air treatment system including one or more inlet pre-cleaners configured to eject debris. Each of the inlet pre-cleaners having a cylindrical tubular portion configured to channel air toward the air intake duct. In addition, the pumping unit includes a gearbox operatively coupled to the engine and a drive shaft having a first end operatively coupled to the gearbox. Further, the pumping unit includes a pump comprising an input shaft operatively coupled to a second end of the drive shaft, wherein the engine, the gearbox, the drive shaft, and the pump are disposed along a longitudinal axis of the pumping unit.

A hybrid power drive system for an aircraft comprises a rotor that receives power and a first power drive sub-system including at least one engine in connection with the rotor is configured to provide a first power to the rotor. Further, the hybrid power drive system also includes a second power drive sub-system connected in parallel to the first power drive sub-system. The second power drive sub-system is configured to provide a second power to the rotor a second power drive sub-system connected in parallel to the first power drive sub-system and configured to provide a second power to the rotor when the first power provided by the first power drive sub-system is less than a power demand of the rotor.