CPC F01D 25/18 (2013.01) [F01D 25/125 (2013.01); F16N 39/02 (2013.01); F05D 2260/207 (2013.01); F05D 2260/232 (2013.01); F16N 2210/14 (2013.01); F28D 2021/0021 (2013.01)] | 19 Claims |
1. An aircraft engine circulation system, comprising:
a conduit arranged to communicate a lubricant to and from one or more bearings, said conduit comprising a central tube defining a passage for communicating lubricant and a peripheral tube surrounding the central tube and defining a space between the outer surface of the central tube and an inner surface of the peripheral tube, wherein the space includes a thermally induced phase changing material arranged to change phase when heated; and
a heat exchanger arranged to receive lubricant from the central tube.
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