Firing test of a hypersonic turbojet engine installed on a flight test vehicle

Hideyuki Taguchi, Kenya Harada, Hiroaki Kobayashi, Takayuki Kojima, Motoyuki Hongoh, Daisaku Masaki, Shujiro Sawai, Yusuke Maru, Tetsuya Satou

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    14 Citations (Scopus)

    Abstract

    Hypersonic turbojet engine with pre-cooling system is tested under sea level static condition. The engine is installed on a flight test vehicle, which will fly at Mach 2 speed by a free fall experiment from a stratospheric balloon. Liquid hydrogen fuel and gas hydrogen fuel is supplied to the engine from a tank and cylinders installed in the vehicle. Designated operation of major components of the engine is confirmed. Corrected rotation speed, corrected air flow rate and pressure ratio of the compressor is raised by pre-cooling with liquid hydrogen fuel. Corrected air flow rate and pressure ratio at the pre-cooling operation is reduced comparing from that without pre-cooling on the same corrected rotation speed. There is a deep temperature distortion at the inlet of the compressor and it may cause the performance reduction. Large amount of liquid hydrogen is supplied to the pre-cooler in order to obtain enough pre-cooling performance for Mach 5 flight. Then, fuel rich combustion at the after-burner is adopted. Cowl part of variable geometry nozzle is made with C/C composite material and it has no damage after the combustion test. Operation of the core engine by liquid hydrogen is attained by using a control valve with small effective diameter.

    Original languageEnglish
    Title of host publication16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
    Publication statusPublished - 2009
    Event16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference - Bremen
    Duration: 2009 Oct 192009 Oct 22

    Other

    Other16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
    CityBremen
    Period09/10/1909/10/22

    Fingerprint

    Turbojet engines
    Hypersonic aerodynamics
    Hydrogen fuels
    Engines
    Cooling
    Liquid fuels
    Mach number
    Compressors
    Flow rate
    Hydrogen
    Upper atmosphere
    Gas fuels
    Balloons
    Sea level
    Liquids
    Engine cylinders
    Air
    Cooling systems
    Fuel burners
    Nozzles

    ASJC Scopus subject areas

    • Engineering(all)

    Cite this

    Taguchi, H., Harada, K., Kobayashi, H., Kojima, T., Hongoh, M., Masaki, D., ... Satou, T. (2009). Firing test of a hypersonic turbojet engine installed on a flight test vehicle. In 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference [2009-7311]

    Firing test of a hypersonic turbojet engine installed on a flight test vehicle. / Taguchi, Hideyuki; Harada, Kenya; Kobayashi, Hiroaki; Kojima, Takayuki; Hongoh, Motoyuki; Masaki, Daisaku; Sawai, Shujiro; Maru, Yusuke; Satou, Tetsuya.

    16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. 2009. 2009-7311.

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    Taguchi, H, Harada, K, Kobayashi, H, Kojima, T, Hongoh, M, Masaki, D, Sawai, S, Maru, Y & Satou, T 2009, Firing test of a hypersonic turbojet engine installed on a flight test vehicle. in 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference., 2009-7311, 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, Bremen, 09/10/19.
    Taguchi H, Harada K, Kobayashi H, Kojima T, Hongoh M, Masaki D et al. Firing test of a hypersonic turbojet engine installed on a flight test vehicle. In 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. 2009. 2009-7311
    Taguchi, Hideyuki ; Harada, Kenya ; Kobayashi, Hiroaki ; Kojima, Takayuki ; Hongoh, Motoyuki ; Masaki, Daisaku ; Sawai, Shujiro ; Maru, Yusuke ; Satou, Tetsuya. / Firing test of a hypersonic turbojet engine installed on a flight test vehicle. 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. 2009.
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    abstract = "Hypersonic turbojet engine with pre-cooling system is tested under sea level static condition. The engine is installed on a flight test vehicle, which will fly at Mach 2 speed by a free fall experiment from a stratospheric balloon. Liquid hydrogen fuel and gas hydrogen fuel is supplied to the engine from a tank and cylinders installed in the vehicle. Designated operation of major components of the engine is confirmed. Corrected rotation speed, corrected air flow rate and pressure ratio of the compressor is raised by pre-cooling with liquid hydrogen fuel. Corrected air flow rate and pressure ratio at the pre-cooling operation is reduced comparing from that without pre-cooling on the same corrected rotation speed. There is a deep temperature distortion at the inlet of the compressor and it may cause the performance reduction. Large amount of liquid hydrogen is supplied to the pre-cooler in order to obtain enough pre-cooling performance for Mach 5 flight. Then, fuel rich combustion at the after-burner is adopted. Cowl part of variable geometry nozzle is made with C/C composite material and it has no damage after the combustion test. Operation of the core engine by liquid hydrogen is attained by using a control valve with small effective diameter.",
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    AU - Hongoh, Motoyuki

    AU - Masaki, Daisaku

    AU - Sawai, Shujiro

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    AU - Satou, Tetsuya

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