CPC B64D 33/04 (2013.01) [F02K 1/822 (2013.01)] | 20 Claims |
19. An exhaust gas condenser for an aircraft turbine engine, the exhaust gas condenser extending along a central axis, comprising:
a housing extending lengthwise between a forward end and an aft end, the housing having an interior cavity and a plurality of sides extending between the forward end and aft end;
a nozzle in communication with the housing and disposed at the aft end;
a plurality of air scoops attached to the housing;
a bank of exhaust gas conduits disposed in the interior cavity of the housing, wherein the bank of exhaust gas conduits includes a plurality of exhaust gas conduits and a plurality of bypass air passages, wherein ones of the plurality of exhaust gas conduits and ones of the plurality of bypass air passages are disposed relative to one another in an alternating configuration; and
a center collection channel disposed radially inside of the bank of exhaust gas conduits, the center collection channel in fluid communication with the nozzle;
wherein the plurality of exhaust gas conduits and the plurality of bypass air passages extend spirally along the central axis between the forward end and the aft end, the plurality of exhaust gas conduits are open at the forward end to receive the exhaust gases from the turbine engine and the plurality of exhaust gas conduits are open at the nozzle; and
wherein each one of said plurality of bypass air passages is in fluid communication with at least one of the plurality of air scoops and each one of the plurality of bypass air passages are in fluid communication with the center collection channel.
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