US 12,448,919 B2
Aircraft engine oil distribution system
Michel Bousquet, Longueuil (CA); Kevin Nguyen, Montréal (CA); Christopher Gover, Longueuil (CA); and Jeremie Barberger, Montreal (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Jun. 8, 2023, as Appl. No. 18/207,252.
Prior Publication US 2024/0410318 A1, Dec. 12, 2024
Int. Cl. F02C 7/06 (2006.01); F16N 39/00 (2006.01); F16N 39/02 (2006.01)
CPC F02C 7/06 (2013.01) [F16N 39/002 (2013.01); F16N 39/02 (2013.01); F05D 2260/98 (2013.01); F16N 2210/08 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An aircraft engine oil distribution system, comprising:
a system container having one or more walls enclosing an internal volume;
an oil reservoir disposed in the internal volume of the system container and defining an oil-receiving cavity therein for storing liquid oil and a mist of air and oil, the oil reservoir having an oil inlet defined through a wall of the oil reservoir, the oil reservoir having a plurality of fins protruding from an inner surface of the wall and extending into the oil-receiving cavity, the plurality of fins disposed below the oil inlet relative to gravity, the plurality of fins extending from bases to tips, the tips being spaced apart from the inner surface of the wall, the plurality of fins extending peripherally around the oil-receiving cavity in a direction being transverse to an oil flow flowing downwardly from the oil inlet towards a bottom of the oil-receiving cavity; and
a heat exchanger disposed in the internal volume of the system s, the heat exchanger including:
a cooling fluid passage extending between a cooling fluid inlet and a cooling fluid outlet, the cooling fluid passage defined between the one or more walls of the system container and the wall of the oil reservoir and permitting flow of a cooling fluid therein; and
a matrix disposed in the cooling fluid passage in heat transfer relationship with the plurality of fins of the oil reservoir.