Abstract: A device includes a first rotor segment and a second rotor segment, wherein the first rotor segment and the second rotor segment are configured to be directly coupled together about a shaft to form at least a portion of a unitary rotor. The device also includes a first stator segment and a second stator segment, wherein the first stator segment and the second stator segment are configured to be directly coupled together to form at least a portion of a unitary stator.

Abstract: An electric propulsion system for an aircraft includes a nacelle and an electric machine. The electric machine includes a stator positioned in the nacelle, and a rotor and fan assembly positioned in a primary flow path through the nacelle. The rotor and fan assembly includes a cylindrical fan shroud, a plurality of rotor magnets positioned on an outer surface of the fan shroud, and a fan hub mounted on a central support shaft via one or more bearings. A plurality of fan blades extend between an inner surface of the fan shroud and an outer surface of the fan hub. The rotor magnets may be loaded in compression in a radial direction when the rotor and fan assembly is at rest. The fan blades may be pre-stressed in a radial direction when the rotor and fan assembly is at rest.

Abstract: A system includes a first electric motor that when in operation imparts rotation to a fan stage of an engine. The system also includes a combustion section of the engine comprising a combustor that when in operation generates combustion gas through ignition of fuel and compressed air. The system further includes a turbine of the engine coupled to a shaft of the engine, wherein the turbine when in operation receives the combustion gas from the combustion section and imparts rotation to the shaft using the combustion gas.

Abstract: A device includes a first rotor segment and a second rotor segment, wherein the first rotor segment and the second rotor segment are configured to be directly coupled together about a shaft to form at least a portion of a unitary rotor. The device also includes a first stator segment and a second stator segment, wherein the first stator segment and the second stator segment are configured to be directly coupled together to form at least a portion of a unitary stator.

Abstract: A device includes a first rotor segment and a second rotor segment, wherein the first rotor segment and the second rotor segment are configured to be directly coupled together about a shaft to form at least a portion of a unitary rotor. The device also includes a first stator segment and a second stator segment, wherein the first stator segment and the second stator segment are configured to be directly coupled together to form at least a portion of a unitary stator.

Abstract: An electric propulsion system for an aircraft includes a nacelle and an electric machine. The electric machine includes a stator positioned in the nacelle, and a rotor and fan assembly positioned in a primary flow path through the nacelle. The rotor and fan assembly includes a cylindrical fan shroud, a plurality of rotor magnets positioned on an outer surface of the fan shroud, and a fan hub mounted on a central support shaft via one or more bearings. A plurality of fan blades extend between an inner surface of the fan shroud and an outer surface of the fan hub. The rotor magnets may be loaded in compression in a radial direction when the rotor and fan assembly is at rest. The fan blades may be pre-stressed in a radial direction when the rotor and fan assembly is at rest.

Abstract: A device includes a first rotor segment and a second rotor segment, wherein the first rotor segment and the second rotor segment are configured to be directly coupled together about a shaft to form at least a portion of a unitary rotor. The device also includes a first stator segment and a second stator segment, wherein the first stator segment and the second stator segment are configured to be directly coupled together to form at least a portion of a unitary stator.

Abstract: An electric propulsion system for an aircraft includes a nacelle and an electric machine. The electric machine includes a stator positioned in the nacelle, and a rotor and fan assembly positioned in a primary flow path through the nacelle. The rotor and fan assembly includes a cylindrical fan shroud, a plurality of rotor magnets positioned on an outer surface of the fan shroud, and a fan hub mounted on a central support shaft via one or more bearings. A plurality of fan blades extend between an inner surface of the fan shroud and an outer surface of the fan hub. The rotor magnets may be loaded in compression in a radial direction when the rotor and fan assembly is at rest. The fan blades may be pre-stressed in a radial direction when the rotor and fan assembly is at rest.

Abstract: An electric propulsion system for an aircraft includes a nacelle and an electric machine. The electric machine includes a stator positioned in the nacelle, and a rotor and fan assembly positioned in a primary flow path through the nacelle. The rotor and fan assembly includes a cylindrical fan shroud, a plurality of rotor magnets positioned on an outer surface of the fan shroud, and a fan hub mounted on a central support shaft via one or more bearings. A plurality of fan blades extend between an inner surface of the fan shroud and an outer surface of the fan hub. The rotor magnets may be loaded in compression in a radial direction when the rotor and fan assembly is at rest. The fan blades may be pre-stressed in a radial direction when the rotor and fan assembly is at rest.