Patent ID: 11965697
Assignee: GENERAL ELECTRIC COMPANY
Field: Thermal processes and apparatus (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. A heat exchanger for use in an aircraft engine, the heat exchanger comprising:
a first wall manifold;
a second wall manifold spaced apart from the first wall manifold;
a plurality of vanes extending between the first wall manifold and the second wall manifold; and
a plurality of fluid circuits defined within the heat exchanger, each fluid circuit in the plurality of fluid circuits comprising:
an inlet channel portion and an outlet channel portion defined within the first wall manifold;
a return channel portion defined within the second wall manifold; and
at least one passage portion of a plurality of passage portions defined within each vane of the plurality of vanes, wherein the at least one passage portion extends between the return channel portion and one of the inlet channel portion and the outlet channel portion.