A propulsion system for an aircraft includes an engine assembly and a turbocompressor. The engine assembly includes an engine and an interburner. The engine includes an engine output shaft. The engine is configured to drive rotation of a propulsor with the engine output shaft. The interburner is configured to mix and burn an exhaust gas from the engine with fuel to form a combustion gas. The turbocompressor includes a turbine and a compressor. The turbine and the compressor form a rotational assembly. The rotational assembly includes a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor. The turbine is connected in fluid communication with the interburner to receive the combustion gas. The compressor is connected in fluid communication with the engine to direct a compressed air to the engine. The rotational assembly is mechanically independent of the engine output shaft.


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    Title :

    AIRCRAFT PROPULSION SYSTEM


    Contributors:

    Publication date :

    2025-08-07


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64U / 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



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