US 11,817,761 B2
Aircraft electric motor
Abbas A. Alahyari, Glastonbury, CT (US); Joseph Turney, Amston, CT (US); Jagadeesh Kumar Tangudu, South Windsor, CT (US); and Kimberly Rae Saviers, Glastonbury, CT (US)
Assigned to HAMILTON SUNDSTRAND CORPORATION, Charlotte, NC (US)
Filed by Hamilton Sundstrand Corporation, Charlotte, NC (US)
Filed on Nov. 5, 2021, as Appl. No. 17/519,749.
Prior Publication US 2023/0141526 A1, May 11, 2023
Int. Cl. H02K 9/20 (2006.01); H02K 5/20 (2006.01); H02K 11/33 (2016.01); B64D 27/24 (2006.01); B64D 33/08 (2006.01); H02K 21/22 (2006.01)
CPC H02K 5/203 (2021.01) [B64D 27/24 (2013.01); B64D 33/08 (2013.01); H02K 9/20 (2013.01); H02K 11/33 (2016.01); H02K 21/22 (2013.01)] 20 Claims
OG exemplary drawing
 
1. 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 drive unit configured to drive operation of the motor unit; and
a cooling system comprising:
at least one directional feature forming a portion of at least one cooling channel, the at least one directional feature configured to prevent backflow of a cooling fluid that passes through the at least one cooling channel,
wherein the at least one cooling channel defines an inlet portion comprising an inlet, a mid-channel portion, and an outlet portion comprising an outlet,
wherein the at least one directional feature comprises at least one feature in the inlet portion and at least one feature in the outlet portion, and
wherein the at least one feature within the inlet portion is different from the at least one feature in the outlet portion.