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 (48), a nozzle (46), air scoops (52, 54, 62), a bank of exhaust gas conduits (56), and a center collection channel (86). The housing (48) includes an interior cavity (50), top and bottom sides (66, 64), and first and second lateral sides (68, 70). The bank of exhaust gas conduits (56) is disposed in the interior cavity (50) of the housing (48) and includes exhaust gas conduits (56) and bypass air passages (84). The exhaust gas conduits (56) and bypass air passages (84) are disposed in an alternating configuration. The center collection channel (86) is disposed radially inside of the bank of exhaust conduits (56). The exhaust gas conduits (56) and bypass air passages (84) extend spirally along the central axis (30) between the forward and aft ends (58). Each bypass air passage (84) is in fluid communication with an air scoop (52, 54, 62) and the center collection channel (86).
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
25.12.2024
Patent
Elektronische Ressource
Englisch
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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