Abstract: A method for generating electrical power may include the steps of rotating a rotor of a generator at a speed in excess of about 12,000 revolutions per minute (rpm) to about 25,000 rpm and producing power with the generator at a rate in excess of about 800 kilowatts (kW). The generator has a power/weight ratio no smaller than about 3 kW/lbs. A rotor is cooled with cooling oil internally circulated through the rotor of the generator so that contact of cooling oil with external surfaces of the rotor may be precluded. The stator is also cooled with oil that is prevented from contacting the external surfaces of the rotor. Pressurized airflow may be produced in a gap between the rotor and a stator of the generator to preclude entry of cooling oil into the gap.

Abstract: A system for driving an environmental control system (ECS) of a vehicle with ground-based electrical power may include a turbine engine on board the vehicle, coupled to the ECS to pneumatically drive the ECS, and an electric machine, on board the aircraft, mechanically coupled to the turbine engine, to drive the turbine engine. A control system such that the electric machine provides motoring assistance to the turbine engine, and that the motoring assistance is limited to match the available current from the ground-based electrical power.

Abstract: A method for generating electrical power may include the steps of rotating a rotor of a generator at a speed in excess of about 12,000 revolutions per minute (rpm) to about 25,000 rpm and producing power with the generator at a rate in excess of about 800 kilowatts (kW). The generator has a power/weight ratio no smaller than about 3 kW/lbs. A rotor is cooled with cooling oil internally circulated through the rotor of the generator so that contact of cooling oil with external surfaces of the rotor may be precluded. The stator is also cooled with oil that is prevented from contacting the external surfaces of the rotor. Pressurized airflow may be produced in a gap between the rotor and a stator of the generator to preclude entry of cooling oil into the gap.

Abstract: A method for generating electrical power may include the steps of rotating a rotor of a generator at a speed in excess of about 12,000 revolutions per minute (rpm) to about 25,000 rpm and producing power with the generator at a rate in excess of about 800 kilowatts (kW). The generator has a power/weight ratio no smaller than about 3 kW/lbs. A rotor is cooled with cooling oil internally circulated through the rotor of the generator so that contact of cooling oil with external surfaces of the rotor may be precluded. The stator is also cooled with oil that is prevented from contacting the external surfaces of the rotor. Pressurized airflow may be produced in a gap between the rotor and a stator of the generator to preclude entry of cooling oil into the gap.

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: A high efficiency multifunction power system for an aircraft is provided. The system includes an AC generator and a multifunction power converter-controller module including at least one multifunction power converter-controller. The at least one multifunction power converter-controller is configured to function as a power converter and a controller to perform multiple operation modes.

Abstract: An electrical system for an aircraft with an electric taxi system (ETS), the electrical system may include at least one traction motor, a DC link and at least one traction-motor bidirectional DC-AC converter interposed between the at least one traction motor and the DC link. An engine-driven power source may be configured to provide DC power to the DC link or extract DC power from the DC link. A battery unit may be configured to provide DC power to the DC link or extract DC power from the DC link. An adaptive power controller may be interconnected with the power source, the battery unit and the at least one traction-motor bidirectional DC-AC converter and configured to regulate voltage of DC power delivered to the DC link.

Abstract: A system for driving an environmental control system (ECS) of a vehicle with ground-based electrical power may include a turbine engine on board the vehicle, coupled to the ECS to pneumatically drive the ECS, and an electric machine, on board the aircraft, mechanically coupled to the turbine engine, to drive the turbine engine. A control system such that the electric machine provides motoring assistance to the turbine engine, and that the motoring assistance is limited to match the available current from the ground-based electrical power.

Abstract: A method for generating electrical power may include the steps of rotating a rotor of a generator at a speed in excess of about 12,000 revolutions per minute (rpm) to about 25,000 rpm and producing power with the generator at a rate in excess of about 800 kilowatts (kW). The generator has a power/weight ratio no smaller than about 3 kW/lbs. A rotor is cooled with cooling oil internally circulated through the rotor of the generator so that contact of cooling oil with external surfaces of the rotor may be precluded. The stator is also cooled with oil that is prevented from contacting the external surfaces of the rotor. Pressurized airflow may be produced in a gap between the rotor and a stator of the generator to preclude entry of cooling oil into the gap.

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: Apparatus for controlling a turbine aircraft engine may include apparatus to determine an amount of secondary power extraction from the engine, a secondary load processor configured to receive and condition secondary power extraction data. An electronic engine controller (EEC) may be configured to receive secondary load data from the secondary load processor and produce commands to open bleed-air valves of the engine, said commands being based on the secondary load data.

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: An electrical system for an aircraft with an electric taxi system (ETS), the electrical system may include at least one traction motor, a DC link and at least one traction-motor bidirectional DC-AC converter interposed between the at least one traction motor and the DC link. An engine-driven power source may be configured to provide DC power to the DC link or extract DC power from the DC link. A battery unit may be configured to provide DC power to the DC link or extract DC power from the DC link. An adaptive power controller may be interconnected with the power source, the battery unit and the at least one traction-motor bidirectional DC-AC converter and configured to regulate voltage of DC power delivered to the DC link.

Abstract: A high efficiency multifunction power system for an aircraft is provided. The system includes an AC generator and a multifunction power converter-controller module including at least one multifunction power converter-controller. The at least one multifunction power converter-controller is configured to function as a power converter and a controller to perform multiple operation modes.

Abstract: An electrical power distribution system (EPDS) for an aircraft, the EPDS may include a DC bus, a power source port, a solid state power controller (SSPC) of a first type interposed between the power source port and the DC bus, at least one load port and an SSPC of a second type interposed between the load port and the DC bus. Power input to the SSPC of the first type may be connected to a unidirectional solid state switching device (SSSD) of the SSPC of the first type. The SSPC of the first type may have forward and reverse current conducting capability and forward and reverse current blocking capability. Power input to the SSPC of the second type may be connected to a unidirectional SSSD of the SSPC of the second type. The SSPC of the second type may have forward and reverse current conducting capability and capability of blocking current from only one direction.

Abstract: Apparatus for controlling a turbine aircraft engine may include apparatus to determine an amount of secondary power extraction from the engine, a secondary load processor configured to receive and condition secondary power extraction data. An electronic engine controller (EEC) may be configured to receive secondary load data from the secondary load processor and produce commands to open bleed-air valves of the engine, said commands being based on the secondary load data.

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: A wedge cooling apparatus and method for cooling a rotating machine, such as a generator, disperses a spray of cooling fluid into the wedges of the generator. The spray cooling method results in a high heat transfer coefficient of about 2000-3000 W/m2C as opposed to conventional conduction cooling, which has a heat transfer coefficient of about 200-300 W/m2C. The apparatus and method of the present invention efficiently removes heat from high powered, high current density designed generators.

Abstract: An electrical power distribution system (EPDS) for an aircraft, the EPDS may include a DC bus, a power source port, a solid state power controller (SSPC) of a first type interposed between the power source port and the DC bus, at least one load port and an SSPC of a second type interposed between the load port and the DC bus. Power input to the SSPC of the first type may be connected to a unidirectional solid state switching device (SSSD) of the SSPC of the first type. The SSPC of the first type may have forward and reverse current conducting capability and forward and reverse current blocking capability. Power input to the SSPC of the second type may be connected to a unidirectional SSSD of the SSPC of the second type. The SSPC of the second type may have forward and reverse current conducting capability and capability of blocking current from only one direction.