CPC H02K 21/24 (2013.01) [B64C 29/0033 (2013.01); B64D 27/24 (2013.01); H02K 1/145 (2013.01); H02K 3/24 (2013.01); H02K 2201/12 (2013.01); H02K 2213/03 (2013.01)] | 20 Claims |
1. A transverse flux electrical machine for coupling to a rotating shaft of a propulsor of an aircraft, the transverse flux electrical machine comprising:
a rotor having a plurality of circumferentially distributed permanent magnets that form a number, NP, of rotor poles, wherein the rotor poles have a pole pitch angle, Pθ, equal to 2π divided by the number of rotor poles, NP;
a stator having a plurality of current-carrying coils configured to interact with the rotor poles of the rotor to produce a torque; and
an air gap separating the rotor from the stator by an air gap distance, GAir,
wherein a machine parameter,
![]() ![]() is less than 100 micro radian-meters,
wherein an active parts torque density, ρact, of the transverse flux electrical machine is defined as:
![]() wherein τpeak is a peak rated torque of the transverse flux electrical machine and mact is an active parts mass of the transverse flux electrical machine,
wherein the active parts mass is a cumulated mass of components of the transverse flux electrical machine that contribute to producing the torque, and
wherein ρact is in a range of 50 to 165 Nmkg−1.
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