Abstract: A cooling system for an engine of an aircraft of a having hybrid-electric propulsion system including a nacelle body including a bottom cooling air intake disposed below a propeller hub for supplying air to an oil-air cooler, wherein the bottom cooling air intake includes a splitter dividing the bottom cooling air intake into a first channel and a second channel.

Abstract: An electric machine system described herein comprises a first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors driven using electric power having a first phase. The second electric machine has a plurality of second rotors driven using electric power having a second phase. The second phase differs from the first phase. Each of one or more shafts connects a first rotor with a second rotor. The first rotor is coaxial with and axially spaced apart from the second rotor.

Abstract: An electric machine system described herein comprises a first electric machine rotor, a first gear and a second gear. The first gear is connected to the first electric machine rotor and to a first input/output shaft. The second gear is connected to the first electric machine rotor and to a second input/output shaft. The first electric machine rotor is disposed between the first gear and the second gear.

Abstract: An electric machine system disclosed herein comprises first and second electric machines configured to drive a load. The first electric machine has a plurality of first rotors. The second electric machine has a plurality of second rotors. At least one of the second rotors is indexed relative to a respective one of the first rotors to, in use, provide a torque phase offset between the first and second electric machines. A shaft is coupled to the load and connects the respective one of the first rotors with the at least one of the second rotors. The respective one of the first rotors is coaxial with and axially spaced apart from the at least one of the second rotors.

Abstract: Methods and systems for operating a hybrid electric aircraft propulsion system mounted to an aircraft. The method comprises driving a first rotating propulsor from a first electric motor operatively connected to a generator, driving a second rotating propulsor from a second electric motor operatively connected to the generator, and driving a third rotating propulsor from a thermal engine, the thermal engine operatively connected to the generator and configured to drive the generator.

Abstract: An aircraft comprising a hybrid electric aircraft propulsion system. The system comprises a first sub-assembly having a first electric propulsor assembly and a first thermal propulsor assembly, the first thermal propulsor assembly having a first thermal engine, a first generator and a first rotating propulsor, the first electric propulsor assembly attached to the aircraft at a first location and the first thermal propulsor assembly attached to the aircraft at a second location. The system also comprises a second sub-assembly having a second electric propulsor assembly and a second thermal propulsor assembly, the second thermal propulsor assembly having a second thermal engine, a second generator and a second rotating propulsor, the second electric propulsor assembly attached to the aircraft at a third location and the second thermal propulsor assembly attached to the aircraft at a fourth location.

Abstract: Methods and systems for operating a hybrid electric aircraft propulsion system. The method comprises providing alternating current (AC) electric power to a first electric motor to drive a first rotating propulsor, providing the first electric motor with AC electric power from at least one motor inverter operatively coupled to a direct current (DC) power source, detecting a failure in a path to the first electric motor, and selectively rearranging a first switching arrangement between the generator, the at least one motor inverter, and the first electric motor.

Abstract: There is described a method and system for operating a hybrid electric aircraft propulsion system. The method comprises modulating AC electric power applied to a first electric propulsor or a second electric propulsor from at least one motor inverter to synchronize the frequency of the first electric propulsor or the second electric propulsor with the frequency of a generator.

Abstract: There is provided a hybrid electric aircraft propulsion system and method for operating same. The method comprises providing, to a first electric motor and a second electric motor, alternating current (AC) electric power from a generator, the generator receiving rotational power from a thermal engine, providing, to the first electric motor and the second electric motor, AC electric power from at least one motor inverter, the at least one motor inverter configured to convert DC electric power from a DC power source into AC electric power, and selectively driving the first and second electric motors from the generator, the at least one motor inverter, or a combination thereof, wherein the first electric motor drives a first rotating propulsor and the second electric motor drives a second rotating propulsor.

Abstract: A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.

Abstract: The external rotor for an electric machine includes a cylindrically shaped receptacle having a peripheral wall and a magnet-receiving assembly including segments assembled to the inner surface of the peripheral wall so as to define a cylindrically shaped stack. The segments are shaped so as to yield magnet-receiving portions in the ring-shaped stack, and permanent magnets are secured to the magnet-receiving portion of the magnet receiving assembly.

Abstract: An electric machine is described herein. The electric machine includes a casing, a stator, a rotor generally coaxial with the stator, an enclosed cooling assembly circulating a first cooling fluid within the casing, and an open cooling assembly through which a second cooling assembly can flow; the open cooling assembly cooling both the stator and the first cooling fluid.

Abstract: An embodiment of a liquid cooled electric machine is provided with an enclosed stator and includes a cooling assembly so configured as to allow cooling liquid to flow in the coil receiving slots of the enclosed stator to thereby cool the coils positioned therein.

Abstract: A cooling arrangement cast into a generally cylindrical stator having longitudinal channels provided on an internal surface thereof is described herein. The cast cooling arrangement comprising a cast heat-storing element and conduits defining a cooling path having an inlet and an outlet.

Abstract: A cooling arrangement cast into a generally cylindrical stator having longitudinal channels provided on an internal surface thereof is described herein. The cast cooling arrangement comprising a cast heat-storing element and conduits defining a cooling path having an inlet and an outlet.

Abstract: The external rotor for an electric machine includes a cylindrically shaped receptacle having a peripheral wall and a magnet-receiving assembly including segments assembled to the inner surface of the peripheral wall so as to define a cylindrically shaped stack. The segments are shaped so as to yield magnet- receiving portions in the ring-shaped stack, and permanent magnets are secured to the magnet-receiving portion of the magnet receiving assembly.

Abstract: An embodiment of a liquid cooled external rotor electric machine includes a stator, a generally cylindrical liquid cooling assembly secured to the stator therein, a rotor including a generally cylindrical shaped support having permanent magnets secured to its inner surface, an output shaft coaxially mounted to the rotor therein and a coupling assembly that biases the cooling assembly onto the stator and operatively mounts together the stator and cooling assembly to the output shaft. Mounting the shaft to the rotor and to the liquid cooling system yields a compact assembly where no housing is required for the alignment of the stator and rotor.

Abstract: A temporary interconnection element to be installed between the rotor and the stator of a bearingless electric machine, for example during its transport, storage or assembly is described herein. The interconnection element is so designed that the rotor may be secured to an external assembly, such as for example the shaft of an internal combustion engine, before the element is removed from its interconnection position.

Abstract: A centrifugal air/oil separation system communicates with bearing cavities of the engine and substantially isolates separated oil from contacting the gearbox.

Abstract: A temporary interconnection element to be installed between the rotor and the stator of a bearingless electric machine, for example during its transport, storage or assembly is described herein. The interconnection element is so designed that the rotor may be secured to an external assembly, such as for example the shaft of an internal combustion engine, before the element is removed from its interconnection position.