CPC H02K 21/04 (2013.01) [H02K 1/17 (2013.01); H02K 1/27 (2013.01); H02K 1/278 (2013.01); H02K 3/28 (2013.01); H02K 21/48 (2013.01); B60L 50/10 (2019.02); B60L 2200/10 (2013.01)] | 17 Claims |
1. A generator arranged to be driven by an aircraft engine, the generator comprising:
a stator, comprising:
a stator core having a substantially annular cross section and having a plurality of slots longitudinally extending in a direction of a longitudinal axis of the stator, for receiving conductors to form windings of the stator;
a plurality of power channels, wherein each power channel comprises a set of windings having a plurality of phase windings, each of the phase windings comprising a set of coils comprising a plurality of conductors wound in a lap winding configuration, the set of coils having a split phase belt such that the set of coils comprises at least a first coil and a second coil, the first coil being mechanically shifted with respect to the second coil by a predetermined number of slots of the stator, and wherein the set of windings of each power channel continuously extend around a portion of a circumference of the stator core, and are arranged such that the set of windings of each power channel are mechanically shifted with respect to the set of windings of an adjacent power channel; and
a rotor, wherein the rotor comprises a permanent magnet segmented in at least one direction to thereby reduce eddy-current losses.
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