Method And System For Cooling Aircraft Engine Fluid

Abstract: A self-contained lubrication fluid circulation system (200, 300, 400) for use with a gas turbine engine (10) defining a core air flowpath (37) includes a sump (100) configured to collect lubrication fluid and a heat source (108, 110, 116) coupled in fluid communication with the sump and configured to transfer heat to the lubrication fluid. The system also includes a heat sink (204, 304, 154) positioned within the sump and coupled in fluid communication with the heat source. A lubrication fluid conduit (202, 410) of the system is configured to channel the lubrication fluid between the heat source and the heat sink, wherein the lubrication fluid conduit is positioned entirely within the sump.

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