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).


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    Title :

    AIRCRAFT PROPULSION SYSTEM WITH TURBINE ENGINE AND EXHAUST CONDENSER


    Additional title:

    FLUGZEUGANTRIEBSSYSTEM MIT TURBINENMOTOR UND ABGASKONDENSATOR
    SYSTÈME DE PROPULSION D'AÉRONEF AVEC MOTEUR À TURBINE ET CONDENSEUR D'ÉCHAPPEMENT


    Contributors:

    Publication date :

    2024-12-25


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    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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    SMITH SCOTT / STRATTON RUSSELL | European Patent Office | 2024

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    Free access

    AIRCRAFT PROPULSION SYSTEM WITH TURBINE ENGINE AND EXHAUST CONDENSER

    SMITH SCOTT / STRATTON RUSSELL | European Patent Office | 2024

    Free access