US 11,912,427 B2
Thermal management system and method of use
Debabrata Pal, Hoffman Estates, IL (US); Tom A. Utecht, Cherry Valley, IL (US); and Craig R. LeGros, Rockford, IL (US)
Assigned to Hamilton Sundstrand Corporation, Charlotte, NC (US)
Filed by Hamilton Sundstrand Corporation, Charlotte, NC (US)
Filed on May 14, 2021, as Appl. No. 17/321,345.
Claims priority of provisional application 63/025,948, filed on May 15, 2020.
Prior Publication US 2022/0001997 A1, Jan. 6, 2022
Int. Cl. F02C 7/18 (2006.01); B64D 33/08 (2006.01)
CPC B64D 33/08 (2013.01) [F02C 7/18 (2013.01); F05D 2220/323 (2013.01); F05D 2260/213 (2013.01)] 12 Claims
OG exemplary drawing
 
1. An aircraft engine thermal management system comprising:
a coolant path extending between a belly fairing and an engine nacelle of an aircraft;
a generator power electronics module in thermal communication with a body, the body having a coolant passage, fluidically connected to the coolant path, wherein the generator power electronics module and the body are located in the belly fairing of the aircraft;
a generator fluidically connected to the coolant path wherein the generator is located in the engine nacelle, and wherein at least a portion of the coolant path is located within a wing of the aircraft, having a lower average temperature than either the belly fairing or engine nacelle; and
a heat exchanger fluidically connected to the body and fluidically connected to the generator by way of the coolant path.