An aircraft propulsion system (20) is provided that includes a turbine engine (24) and an exhaust gas condenser (28). The exhaust gas condenser (28) includes a housing (46), a nozzle (44), a plurality of air scoops (50, 52, 54), and a plurality of exhaust gas conduit banks (56, 58, 60). The housing (46) has an interior cavity (48), a bottom side (66), and first and second lateral sides (70, 72). The exhaust gas conduit banks (56, 58, 60) are disposed in the interior cavity (48) of the housing (46) and are configured to form an interior bypass air chamber (92). Each exhaust gas conduit bank (56, 58, 60) includes alternating exhaust gas conduits (80, 88) and bypass air passages (82, 90). The exhaust gas conduits (80, 88) extend axially between forward and aft ends (62, 64) of the housing (46), and are configured to conduct exhaust gases to the nozzle (44). The bypass air passages (82, 90) are configured to receive bypass air from the air scoops (50, 52, 54) and direct the bypass air between the exhaust gas conduits (80, 88) and into the interior bypass air chamber (92).
AIRCRAFT PROPULSION SYSTEM WITH TURBINE ENGINE AND EXHAUST CONDENSER
FLUGZEUGANTRIEBSSYSTEM MIT TURBINENMOTOR UND ABGASKONDENSATOR
SYSTÈME DE PROPULSION D'AÉRONEF AVEC MOTEUR À TURBINE ET CONDENSEUR D'ÉCHAPPEMENT
2024-12-25
Patent
Electronic Resource
English
IPC: | F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke |
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