Abstract: In some examples, a stator assembly includes a stator body including a base portion and a plurality of stator teeth projecting radially inward from the base portion. The stator assembly further includes an electrically conductive member wound about a tooth of the plurality of stator teeth to define a winding about the tooth, the winding comprising a single layer of the conductive member and including a plurality of turns of the electrically conductive member, wherein the electrically conductive member has a thickness in the radial direction that is less than its width in a direction perpendicular to the radial direction.

Abstract: In some examples, a stator assembly includes a stator body including a base portion and a plurality of stator teeth projecting radially inward from the base portion. The stator assembly further includes an electrically conductive member wound about a tooth of the plurality of stator teeth to define a winding about the tooth, the winding comprising a single layer of the conductive member and including a plurality of turns of the electrically conductive member, wherein the electrically conductive member has a thickness in the radial direction that is less than its width in a direction perpendicular to the radial direction.

Abstract: A method for forming a squirrel cage rotor includes stacking a plurality of coated laminates to form a stacked laminate core preform. The stacked laminate core preform defines a plurality of open cavities. Each coated laminate of the plurality of coated laminates includes a laminate coated with a precursor layer. The precursor layer includes a binder and glass particles. The method further includes firing the stacked laminate core preform at a temperature above the softening point of the glass particles to form a low porosity rotor core. The method further includes casting a conductive material into the plurality of open cavities formed in the rotor core to define a conductive squirrel cage structure in the low porosity rotor core.

Abstract: A disconnect assembly for an input shaft and an output shaft includes a sleeve configured to be disposed about the input shaft and the output shaft. A cam is disposed about the sleeve. A cam follower is configured to contact the cam. An interfacing element is configured to operatively interface the sleeve, the input shaft, and the output shaft. The sleeve, the cam, the cam follower, and the interfacing element are configured to move between a respective connect position and a respective disconnect position.

Abstract: A disconnect assembly for an input shaft and an output shaft includes a sleeve configured to be disposed about the input shaft and the output shaft. A cam is disposed about the sleeve. A cam follower is configured to contact the cam. An interfacing element is configured to operatively interface the sleeve, the input shaft, and the output shaft. The sleeve, the cam, the cam follower, and the interfacing element are configured to move between a respective connect position and a respective disconnect position.

Abstract: The present disclosure broadly relates to apparatuses and methods for generating electric power. More particularly, the present disclosure relates to a self-excited electric generator. The self-excited electric generator may include auxiliary windings to provide a source of electricity to an associated generator control unit (GCU). The apparatuses and methods of the present invention may provide added benefits of reducing excitation requirements from the GCU. Thereby, the apparatuses and methods may reduce cost, weight, and size of an electric generator, and may increase reliability of associated systems.

Abstract: An electrical generating system for an aircraft may include a first shaft connected with an engine gearbox, a second shaft connected with a generator of the aircraft, and a connection unit in which the first and second shafts are selectively engageable with one another. The connection unit may include a solenoid coil, an armature co-axial with the first and the second shafts, a plurality of balls positioned around the armature. The armature may include a first cylindrical segment and a second cylindrical segment. The armature may be selectively movable between a first axial position and a second axial position. When the armature is in a first axial position, the balls are positioned to transmit torque forces between the first shaft and the second shaft. When the armature is in a second axial position, the first shaft and the second shaft are free to rotate independently.

Abstract: The present disclosure broadly relates to apparatuses and methods for generating electric power. More particularly, the present disclosure relates to a self-excited electric generator. The self-excited electric generator may include auxiliary windings to provide a source of electricity to an associated generator control unit (GCU). The apparatuses and methods of the present invention may provide added benefits of reducing excitation requirements from the GCU. Thereby, the apparatuses and methods may reduce cost, weight, and size of an electric generator, and may increase reliability of associated systems.

Abstract: An electrical generating system for an aircraft may include a first shaft connected with an engine gearbox, a second shaft connected with a generator of the aircraft, and a connection unit in which the first and second shafts are selectively engageable with one another. The connection unit may include a solenoid coil, an armature co-axial with the first and the second shafts, a plurality of balls positioned around the armature. The armature may include a first cylindrical segment and a second cylindrical segment. The armature may be selectively movable between a first axial position and a second axial position. When the armature is in a first axial position, the balls are positioned to transmit torque forces between the first shaft and the second shaft. When the armature is in a second axial position, the first shaft and the second shaft are free to rotate independently.

Abstract: A method of increasing the operational efficiency of an operating gas turbine engine includes supplying mechanical power from a first spool of the operating gas turbine engine to a first electrical machine to thereby generate electrical power using the first electrical machine and supplying mechanical power from a second spool of the operating gas turbine engine to a second electrical machine to thereby generate electrical power using the second electrical machine. The method further includes sensing one or more operational parameters of the operating gas turbine engine and, based on the one or more sensed operational parameters, ceasing to generate electrical power using the second electrical machine, and instead supplying at least a part of the electrical power generated by the first electrical machine to the second electrical machine to operate in motoring mode and to thereby generate and supply mechanical output power to the second spool of the engine.

Abstract: The mechanical output power of a turbine engine can be electrically boosted by using a power control system which may include a power source, an electric machine, a prime mover coupled to the electric machine, and a power control module coupled to the power source and the electric machine. The power control module may be configured to operate the electric machine between a motoring mode driving a mechanical load and a generator mode supplying power to an electrical load at speeds normally associated with generating modes only.