| CPC F02K 1/822 (2013.01) [B64D 33/04 (2013.01); F01D 25/32 (2013.01); F05D 2220/323 (2013.01)] | 19 Claims |
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1. An aircraft propulsion system, comprising:
a turbine engine configured to exhaust gases during combustion, the exhaust gases including water vapor; and
an exhaust gas condenser that extends lengthwise along a central axis, the exhaust gas condenser including:
a housing extending lengthwise between a forward end and an aft end, the housing having an interior cavity, a top side, a bottom side opposite the top side, a first lateral side, and a second lateral side opposite the first lateral side, wherein the first lateral side and the second lateral side both extend between the top side and the bottom side;
a nozzle in communication with the housing and disposed at the aft end;
a plurality of air scoops attached to the housing and open to ambient air; and
a plurality of exhaust gas conduit banks disposed in the interior cavity of the housing, wherein the exhaust gas conduit banks are configured to form an interior bypass air chamber within the housing interior cavity, and wherein each said exhaust gas conduit bank includes a plurality of exhaust gas conduits and a plurality of bypass air passages, wherein the exhaust gas conduits and the bypass air passages are disposed relative to one another in an alternating configuration;
wherein the exhaust gas conduits extend axially between the forward end and the aft end, and the exhaust gas conduits are open at the forward end to receive the exhaust gases from the turbine engine and open at the nozzle; and
wherein the bypass air passages are configured to receive bypass air from the plurality of air scoops and direct the bypass air between the exhaust gas conduits and into the interior bypass air chamber, and the interior bypass air chamber is in fluid communication with the nozzle.
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