A dual flow path exhaust assembly for use with a combined turbofan and ramjet engine includes a turbofan engine exhaust duct, a ramjet engine exhaust duct, a combined outlet, and door configured to move between an open position and a closed position to selectively isolate the turbofan engine exhaust duct from the combined outlet.


    Access

    Download


    Export, share and cite



    Title :

    Dual flowpath exhaust for fuel cooling in a hypersonic propulsion system


    Contributors:

    Publication date :

    2022-05-24


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



    Modeling Plasma and MHD Effects in Hypersonic Propulsion Flowpath

    Shneider, Mikhail / Macheret, Sergey | AIAA | 2005


    Modeling Plasma and MHD Effects in Hypersonic Propulsion Flowpath

    Shneider, M. N. / Macheret, S. O. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2005


    Flowpath optimization for hypersonic vehicles

    ORTWERTH, P. / MATHUR, A. / BROWN, C. | AIAA | 1991


    Air-Breathing Propulsion Flowpath Applications

    Joslin, Ronald D. / Miller, Daniel N. | AIAA | 2009


    Global Design Optimization for Hypersonic Scramjet Propulsive Flowpath

    Xian Yu, Wu / Shi Bin, Luo / Xiao Qian, Chen et al. | AIAA | 2006