Abstract: A retention component for retaining a coil in a slot of a stator for a generator having a rotor includes a first segment and a second segment, both of which are configured to be inserted into the slot. At least one of the first and second segments is made entirely of laminated sheets that together form a unitary structure of magnetic material. At least one of the first and second segments has an interfacing surface configured to directly interface a rotor surface in the absence of a structure therebetween. A channel is between the first and second segments, and a third segment that extends along and within the channel. The third segment is less magnetic or non-magnetic than at least one of the first and second elements.

Abstract: A propulsion and electric power generation system includes a gas turbine propulsion engine, an electrical generator, an aircraft power distribution system, a plurality of auxiliary fans, and a controller. The gas turbine propulsion engine includes at least a low-pressure turbine coupled to a fan via a low-pressure spool, and the low-pressure turbine is configured to generate mechanical power. The electrical generator is directly connected to the low-pressure spool and generates a total amount of electrical power (Pe). The aircraft power distribution system receives a first fraction (Pa) of the total amount of electrical power. The auxiliary fans receive a second fraction (Pf) of the total amount of electrical power. The controller is configured to control a ratio of Pf to Pa (Pf/Pa) such that the ratio spans a range from less than 0.6 to at least 0.9.

Abstract: A hybrid electric aircraft propulsion system at least includes a motor with induction effect to drive a propeller or propulsion fan. The motor is directly supplied from the electrical output of a generator. The generator is driven by a variable speed engine and as such the generator has a output frequency proportional to the speed of the engine. A controller is operatively coupled to the motor, the generator and the engine. The controller is operable to control a speed of the engine and the excitation of the generator to provide an output at a target voltage and frequency to drive the motor at a desired torque and speed.

Abstract: A system for providing compressed air to pneumatic loads in a vehicle such as an aircraft is disclosed. The system may include a gas turbine engine having; a) an engine compressor with an air inlet coupled to an interior of a cabin of the vehicle; and b) a load compressor coupled to the gas turbine engine having a compressed air outlet coupled to one or more pneumatic loads of the vehicle. One or more electrically-driven cabin air compressors (CACs) have compressed air outlets coupled to the one or more pneumatic loads.

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 providing compressed air to pneumatic loads in a vehicle such as an aircraft, the system includes a gas turbine engine having; a) an engine compressor with an air inlet coupled to an interior of a cabin of the vehicle; and b) a load compressor coupled to the gas turbine engine having a compressed air outlet coupled to one or more pneumatic loads of the vehicle. One or more electrically driven cabin air compressors (CAC) have compressed air outlets coupled to the one or more pneumatic loads.

Abstract: A retention component for retaining a coil in a slot of a stator for a generator having a rotor includes a first segment and a second segment, both of which are configured to be inserted into the slot. At least one of the first and second segments is made entirely of laminated sheets that together form a unitary structure of magnetic material. At least one of the first and second segments has an interfacing surface configured to directly interface a rotor surface in the absence of a structure therebetween. A channel is between the first and second segments, and a third segment that extends along and within the channel. The third segment is less magnetic or non-magnetic than at least one of the first and second elements.

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: A propulsion and electric power generation system includes a gas turbine propulsion engine, an electrical generator, an aircraft power distribution system, a plurality of auxiliary fans, and a controller. The gas turbine propulsion engine includes at least a low-pressure turbine coupled to a fan via a low-pressure spool, and the low-pressure turbine is configured to generate mechanical power. The electrical generator is directly connected to the low-pressure spool and generates a total amount of electrical power (Pe). The aircraft power distribution system receives a first fraction (Pa) of the total amount of electrical power. The auxiliary fans receive a second fraction (Pf) of the total amount of electrical power. The controller is configured to control a ratio of Pf to Pa (Pf/Pa) such that the ratio spans a range from less than 0.6 to at least 0.9.

Abstract: A propulsion and electric power generation system includes a dual-spool turbofan gas turbine engine and an electrical generator. The dual-spool turbofan gas turbine engine includes at least a low-pressure turbine coupled to a fan via a low-pressure spool. The low-pressure turbine is configured to generate mechanical power. The electrical generator is directly connected to the low-pressure spool and is disposed downstream of the low-pressure turbine. A first fraction of the mechanical power generated by the low-pressure turbine is controllably supplied to the fan for propulsive power generation (Pt). A second fraction of the mechanical power generated by the low-pressure turbine is controllably supplied to the electrical generator for electrical power generation (Pe). A ratio of Pe to Pt (Pe/Pt), during operation of the dual-spool turbofan gas turbine engine, controllably spans a range from less than about 0.06 to at least 0.18.

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 hybrid electric aircraft propulsion system at least includes a motor with induction effect to drive a propeller or propulsion fan. The motor is directly supplied from the electrical output of a generator. The generator is driven by a variable speed engine and as such the generator has a output frequency proportional to the speed of the engine. A controller is operatively coupled to the motor, the generator and the engine. The controller is operable to control a speed of the engine and the excitation of the generator to provide an output at a target voltage and frequency to drive the motor at a desired torque and speed.

Abstract: A system for providing compressed air to pneumatic loads in a vehicle such as an aircraft, the system includes a gas turbine engine having; a) an engine compressor with an air inlet coupled to an interior of a cabin of the vehicle; and b) a load compressor coupled to the gas turbine engine having a compressed air outlet coupled to one or more pneumatic loads of the vehicle. One or more electrically driven cabin air compressors (CAC) have compressed air outlets coupled to the one or more pneumatic loads.

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.