| CPC H02K 3/28 (2013.01) [H02K 1/165 (2013.01); H02K 3/12 (2013.01); H02K 2213/03 (2013.01)] | 18 Claims |

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1. An electrical machine for use in an aircraft, comprising:
a rotor, wherein the rotor comprises a plurality of rotor poles; and
a stator comprising a plurality of phases, wherein each respective phase occupies at least one elementary block, the at least one elementary block of each phase comprising a set of conductors of the respective phase wound around a plurality of slots of the respective elementary block in a concentrated winding configuration;
wherein a mechanical shift angle between the respective concentrated windings of each pair of adjacent elementary blocks is greater than a rotor pole pitch, the rotor pole pitch being an angle between adjacent poles of the rotor; and
wherein each elementary block comprises a plurality of slots arranged to house two conductors of the respective concentrated winding to define an inner layer and an outer layer, and wherein the stator further comprises a further intermediate slot arranged to house one conductor configured to provide a return path connecting the inner layer and the outer layer of each respective elementary block.
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