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), inlet and outlet air scoops (50), and an exhaust gas conduit bank. The housing (46) has an interior cavity (48), top and bottom sides (68, 70), and first and second lateral sides (64, 66). The exhaust gas conduit bank is disposed in the interior cavity (48) of the housing (46). The exhaust gas conduit bank includes a plurality of exhaust gas conduits (54) and bypass air passages (82) that are disposed in an alternating configuration. The exhaust gas conduits (54) extend axially between the forward and aft ends (56, 58), are open at the forward end (56) and at the nozzle (44). The bypass air passages (82) receive bypass air from the inlet air scoop (50) and direct the bypass air laterally across the condenser (28) to the outlet air scoop (52).
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: | F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02K JET-PROPULSION PLANTS , Strahltriebwerke |
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