Abstract: An aircraft engine thermal management system includes a body having a coolant passage in thermal communication with an electronic device, wherein the body and the electronic device are located in a first portion of the aircraft. A generator is fluidically connected by a coolant path to the coolant passage wherein the generator is located in a second portion of the aircraft, with at least a portion of the coolant path is located within a cooling location having a lower average temperature than either the first portion or the second portion of the aircraft.

Abstract: A seal includes a carbon seal that is disposed about an axis and extends between a first axial end and a second axial end. The second axial end includes a seal surface and a radially outer edge of the seal surface is axially spaced from a radially inner edge of the seal surface along the axis.

Abstract: A system including a thermal management body attached to an electronics equipment, a cavity within the thermal management body storing a coolant, and a cold plate separating the cavity and the electronics equipment.

Abstract: A starter/generator arrangement includes a starter/generator, a power converter electrically connected to the starter/generator, and coolant circuit with a pump and a condenser in fluid communication with the power converter. The power converter is arranged to flow start mode electrical power in a first direction in a start mode and a second direction in a generate mode. The coolant circuit fluidly couples the pump to the condenser for storing heat in a coolant disposed within the coolant circuit while flowing the start mode electrical power in the first direction. Gas turbine engines and methods of cooling starter/generator arrangements are also described.

Abstract: A cabin air compressor assembly includes a cabin air compressor, and a cabin air compressor motor operably connected to the cabin air compressor. The cabin air compressor motor includes a rotor and a stator having a plurality of end windings. A cabin air compressor housing includes at least one cooling airflow hole formed therein. A motor cooling flow is movable across a portion of the cabin air compressor motor to cool the stator and the end windings. A duct extends from the cabin air compressor housing to an adjacent end winding such that a cooling outlet flow provided via the at least one cooling air flow hole is arranged in fluid communication with the end winding.

Abstract: An aircraft engine thermal management system includes a body having a coolant passage in thermal communication with an electronic device, wherein the body and the electronic device are located in a first portion of the aircraft. A generator is fluidically connected by a coolant path to the coolant passage wherein the generator is located in a second portion of the aircraft, with at least a portion of the coolant path is located within a cooling location having a lower average temperature than either the first portion or the second portion of the aircraft.

Abstract: An thermal management system including, a body having a coolant passage in thermal communication with an electronic device, a first heat exchanger fluidically connected to the coolant passage configured to receive the coolant from the coolant passage, a second heat exchanger fluidically connected to the first heat exchanger, and a generator fluidically connected to the second heat exchanger.

Abstract: An electrical power unit cooling system including at least one cooling fin configured to be thermally connected to a bus housing of the electrical power unit, the bus housing being configured to be attached to a surface of an aircraft fan housing such that the at least one cooling fin protrudes through the fan housing in order to be cooled by air flow within the fan housing.

Abstract: A system including a thermal management body attached to an electronics equipment, a cavity within the thermal management body storing a coolant, and a cold plate separating the cavity and the electronics equipment.

Abstract: A starter/generator arrangement includes a starter/generator, a power converter electrically connected to the starter/generator, and coolant circuit with a pump and a condenser in fluid communication with the power converter. The power converter is arranged to flow start mode electrical power in a first direction in a start mode and a second direction in a generate mode. The coolant circuit fluidly couples the pump to the condenser for storing heat in a coolant disposed within the coolant circuit while flowing the start mode electrical power in the first direction. Gas turbine engines and methods of cooling starter/generator arrangements are also described.

Abstract: A system including a variable frequency generator (VFG) including a generator configured to conduct alternating current to a first rectifier configured to convert alternating current from the VFG to direct current and drive it to an HVDC Bus Network, a variable frequency second generator including a second generator configured to conduct alternating current to a second rectifier configured to convert alternating current from the second generator to direct current and conduct it to the HVDC Bus Network, a speed correcting gearbox operatively connected to the VFG configured to align generator frequency to the second generator frequency, and a VFG control unit operatively connected to the generator configured to control the VFG, and a second generator control unit operatively connected to the second generator and the HVDC Bus Network configured to control the second generator.

Abstract: An electrical power unit cooling system including at least one cooling fin configured to be thermally connected to a bus housing of the electrical power unit, the bus housing being configured to be attached to a surface of an aircraft fan housing such that the at least one cooling fin protrudes through the fan housing in order to be cooled by air flow within the fan housing.

Abstract: A system including a variable frequency generator (VFG) including a generator configured to conduct alternating current to a first rectifier configured to convert alternating current from the VFG to direct current and drive it to an HVDC Bus Network, a variable frequency second generator including a second generator configured to conduct alternating current to a second rectifier configured to convert alternating current from the second generator to direct current and conduct it to the HVDC Bus Network, a speed correcting gearbox operatively connected to the VFG configured to align generator frequency to the second generator frequency, and a VFG control unit operatively connected to the generator configured to control the VFG, and a second generator control unit operatively connected to the second generator and the HVDC Bus Network configured to control the second generator.

Abstract: A seal includes a carbon seal that is disposed about an axis and extends between a first axial end and a second axial end. The second axial end includes a seal surface and a radially outer edge of the seal surface is axially spaced from a radially inner edge of the seal surface along the axis.

Abstract: An electrical machine includes a winding core with a plurality of end slots. A winding is seated in the end slots with end windings where the winding crosses from end slot to end slot. A slot insulator is seated in two of the end slots. The slot insulator includes a first slot liner seated in a first one of the two end slots with a winding slot defined therethrough in an axial direction. A second slot liner is seated in a second one of the two end slots with a winding slot defined therethrough in the axial direction, wherein the second slot liner is spaced apart in a lateral direction relative to the axial direction from the first slot liner by a gap. The slot insulator includes a span portion bridging across the gap to connect the first and second slot liners.

Abstract: In accordance with at least one aspect of this disclosure, a stationary housing for a rotational mechanical device includes an interior sealing surface configured to receive a rotationally stationary seal assembly that is allowed to move axially to track a journal shaft, wherein the interior sealing surface includes an anti-frictional coating.

Abstract: An automatic disconnect coupling includes a retainer and a biasing member. The biasing member is coupled to the retainer and is arranged to communicate excitation from a generator input member to the retainer. The retainer and the biasing member have a fundamental frequency tuned to the rotational speed of the generator input member to automatically disconnect the input member from a drive member when rotating unbalance of the input member exceeds a predetermined level.

Abstract: An automatic disconnect coupling includes a retainer and a biasing member. The biasing member is coupled to the retainer and is arranged to communicate excitation from a generator input member to the retainer. The retainer and the biasing member have a fundamental frequency tuned to the rotational speed of the generator input member to automatically disconnect the input member from a drive member when rotating unbalance of the input member exceeds a predetermined level.

Abstract: An end band and method of forming an end band for a rotor. The end band includes a hollow cylindrical band, wherein at least a portion of the band has a grain flow in a direction parallel to the hoop stress of the band. The end band also includes at least a portion having a grain flow in a direction perpendicular to the hoop stress of the band.

Abstract: A mist cooling system that includes a casing and a liquid inlet. The casing is configured to receive a liquid flow from a source through the liquid inlet and then provide the liquid flow as a mist to a housing of a motor so as to increase a cooling of the motor and prevent any failure of the motor due to overheating.