US 11,884,409 B2
Aircraft electric motor with integrated cooling system
Abbas A Alahyari, Glastonbury, CT (US); Kimberly Rae Saviers, Glastonbury, CT (US); Joseph Turney, Amston, CT (US); and Jagadeesh Kumar Tangudu, South Windsor, CT (US)
Assigned to HAMILTON SUNDSTRAND CORPORATION, Charlotte, NC (US)
Filed by Hamilton Sundstrand Corporation, Charlotte, NC (US)
Filed on Nov. 1, 2021, as Appl. No. 17/515,934.
Prior Publication US 2023/0138133 A1, May 4, 2023
Int. Cl. H02K 9/197 (2006.01); H02K 7/16 (2006.01); H02K 1/20 (2006.01); H02K 1/30 (2006.01); B64D 27/24 (2006.01); B64D 33/08 (2006.01)
CPC B64D 27/24 (2013.01) [B64D 33/08 (2013.01); H02K 9/197 (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:
a working fluid arranged within a cooling fluid flow path, wherein the cooling fluid flow path includes a liquid cooling path configured to direct flow of the working fluid through, at least, the cooling channels of the motor unit and a vapor cooling path configured to direct flow of the working fluid through the drive unit; and
a separator arranged upstream of each of the liquid cooling path and the vapor cooling path and configured to direct a liquid portion of the working fluid into the liquid cooling path and configured to direct a vapor portion of the working fluid into the vapor cooling path.