A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.

A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.

Disclosed is a system for a gas turbine engine, the gas turbine engine comprising a primary shaft, the system including a rotor shaft; a plurality of components connected to the rotor shaft, including a wound field synchronous main machine (MM) and a permanent magnet generator (PMG); and wherein the PMG, alone or with the MM provide torque to change rotational speed of the rotor shaft, thereby changing rotational speed of the primary shaft.

Disclosed is a system for a gas turbine engine, the gas turbine engine comprising a primary shaft, the system including a rotor shaft; a plurality of components connected to the rotor shaft, including a wound field synchronous main machine (MM) and a permanent magnet generator (PMG); and wherein the PMG, alone or with the MM provide torque to change rotational speed of the rotor shaft, thereby changing rotational speed of the primary shaft.

A rotary propulsion system includes a fan arranged along a rotation axis, an electric motor having windings and a permanent magnet arranged along the rotation axis and operatively connected to the fan, and a reduction gear set. The reduction gear set extends about the rotation axis and couples the electric motor to the fan. The permanent magnet is rotatable relative to the windings and the fan to rotate the fan using the electric motor at a rotational speed that is lower than a rotational speed of the permanent magnet. Aircraft and methods of propelling aircraft are also described.

A rotary propulsion system includes a fan arranged along a rotation axis, an electric motor having windings and a permanent magnet arranged along the rotation axis and operatively connected to the fan, and a reduction gear set. The reduction gear set extends about the rotation axis and couples the electric motor to the fan. The permanent magnet is rotatable relative to the windings and the fan to rotate the fan using the electric motor at a rotational speed that is lower than a rotational speed of the permanent magnet. Aircraft and methods of propelling aircraft are also described.

In some embodiments, a system may include an electrical motor including a cylindrical rotor including an inner circumferential magnetic array and an outer circumferential magnetic array spaced apart by an air gap. The electrical motor may further include a stator including a circumferential array of coils sized to fit within the air gap and a plurality of power electronic circuits. Each power electronic circuit of the plurality of power electronic circuits may independently control current to one or more coils of the circumferential array of coils.

In some embodiments, a system may include an electrical motor including a cylindrical rotor including an inner circumferential magnetic array and an outer circumferential magnetic array spaced apart by an air gap. The electrical motor may further include a stator including a circumferential array of coils sized to fit within the air gap and a plurality of power electronic circuits. Each power electronic circuit of the plurality of power electronic circuits may independently control current to one or more coils of the circumferential array of coils.

An object of the invention is to provide a power converter that can be reduced in size. To achieve this, a power converter according to the invention includes: water passages arranged radially from an assumed central axis, each being trapezoid-shaped in cross section; and power modules placed between the water passages such that each of the power modules is sandwiched from both surfaces thereof by the water passages. Each of the power modules has an output terminal and positive and negative terminals on an end face located in a centrifugal direction side with respect to the assumed central axis. Any of the power modules and an adjacent one of the power modules are set in a front-back inverted manner.

A mounting system for mounting a supplemental alternator, as well as methods of assembling the same, is provided. The mounting system includes a top mounting bracket that is configured to align with a top flange aperture of the additional alternator. The mounting system also includes a bottom mounting bracket having a bracket aperture that aligns with an aperture of an existing alternator mount and also having a flange aperture that aligns with the foot flange aperture of the additional alternator. The mounting system further includes a shaft that couples to the additional alternator.