Aircraft propulsion system with turbine engine and exhaust heat exchanger

Abstract

An aircraft propulsion system is provided that includes a turbine engine and an exhaust gas heat exchanger. The exhaust gas heat exchanger includes a central conduit, an outer radial plenum, fluid conduits, and inter-conduit passages. The fluid conduits are disposed in a nested arrangement. Each fluid conduit has inner and outer radial walls that extend axially between the forward and aft ends. The inner and outer radial walls are radially separated to form an internal fluid passage. Each fluid conduit is radially spaced apart from adjacent fluid conduits to define an axially extending exhaust gas passages. The inter-conduit passages include at least one inter-conduit passage that provides fluid communication between the central conduit and a first fluid conduit, and at least one inter-conduit passage that provides fluid communication between first and second fluid conduits. A serpentine fluid flow path extends through the fluid conduits and the inter-conduit passages.