CPC H02K 9/20 (2013.01) [B64D 27/24 (2013.01); B64D 33/08 (2013.01); H02K 3/22 (2013.01); H02K 5/20 (2013.01)] | 20 Claims |
19. An aircraft electric motor comprising:
a motor unit having a rotor and a stator, wherein the stator includes a plurality of windings and cooling channels arranged to provide cooling to the plurality of windings;
a means for driving operation of the motor unit; and
a cooling system comprising:
at least one cooling channel integrally formed within at least one winding, wherein the at least one cooling channel comprises an inlet to receive a two-phase cooling fluid and an outlet configured to discharge the two-phase cooling fluid, wherein the at least one cooling channel defines a means for accommodating a change in phase of the two-phase fluid as it passes through the at least one cooling channel.
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