| CPC F02C 7/10 (2013.01) [F28D 7/103 (2013.01); F28D 21/0003 (2013.01); F05D 2260/221 (2013.01)] | 20 Claims |
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1. An aircraft propulsion system, comprising:
a turbine engine configured to produce exhaust gases during combustion; and
an exhaust gas heat exchanger extending axially along a central axis between a forward end and an aft end, the exhaust gas heat exchanger disposed to receive the exhaust gases from the turbine engine, the exhaust gas heat exchanger including:
a central conduit disposed radially inside of a plurality of fluid conduits;
a fluid port configured to provide fluid communication between a source of fluid to be heated and the central conduit;
an outer radial plenum disposed radially outside of the plurality of fluid conduits;
the plurality of fluid conduits disposed in a nested arrangement, each fluid conduit having an inner radial wall and an outer radial wall, the inner radial wall and the outer radial wall each extending axially between the forward end and the aft end, and the inner radial wall radially separated from the outer radial wall to form an internal fluid passage therebetween, wherein each said fluid conduit of the plurality of fluid conduits is radially spaced apart from adjacent said fluid conduits to define an axially extending exhaust gas passage disposed between adjacent said fluid conduits;
a plurality of inter-conduit passages, including at least one said inter-conduit passage configured to provide fluid communication between the central conduit and a first said fluid conduit of the plurality of fluid conduits, and at least one said inter-conduit passage configured to provide fluid communication between the first said fluid conduit and a second said fluid conduit of the plurality of fluid conduits;
wherein a serpentine fluid flow path extends from the central conduit, axially through the plurality of fluid conduits, the plurality of inter-conduit passages, and the outer radial plenum.
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