Starting characteristics of hypersonic pre-cooled turbojet inlet

Takayuki Kojima, Hideyuki Taguchi, Hiroaki Kobayashi, Tetsuya Satou

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

    Abstract

    In this study, bypass door area for the Hypersonic Precooled Turbojet Engine to restart the variable intake is estimated. Total pressure recovery and mass capture ratio of the variable air intake is acquired by the supersonic wind tunnel testing of the half scale intake model. Pressure loss and temperature effectiveness of the precooler is acquired by direct connect firing tests of the engine. Using these results, area of the bypass door by which the intake can start is estimated. The bypass door area to restart the intake depends on the precooler’s cooling capability. If the engine runs on liquid hydrogen, area of the bypass door is 1800mm2~2000mm2(Abyp_eng/A0=0.26~0.29). If the liquid nitrogen is used for the coolant of the precooler, area of the bypass door is 2600mm2~2700mm2(Abyp_eng/A0=0.37~0.39).

    Original languageEnglish
    Title of host publication20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
    PublisherAIAA American Institute of Aeronautics and Astronautics
    ISBN (Print)9781624103209
    Publication statusPublished - 2015
    Event20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015 - Glasgow, United Kingdom
    Duration: 2015 Jul 62015 Jul 9

    Other

    Other20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015
    CountryUnited Kingdom
    CityGlasgow
    Period15/7/615/7/9

    Fingerprint

    bypasses
    hypersonics
    Hypersonic aerodynamics
    bypass
    engine
    engines
    turbojet engines
    test firing
    supersonic wind tunnels
    Turbojet engines
    pressure recovery
    Engines
    air intakes
    liquid
    liquid hydrogen
    Air intakes
    coolants
    Liquid nitrogen
    wind tunnel
    liquid nitrogen

    ASJC Scopus subject areas

    • Aerospace Engineering
    • Space and Planetary Science
    • Control and Systems Engineering

    Cite this

    Kojima, T., Taguchi, H., Kobayashi, H., & Satou, T. (2015). Starting characteristics of hypersonic pre-cooled turbojet inlet. In 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015 AIAA American Institute of Aeronautics and Astronautics.

    Starting characteristics of hypersonic pre-cooled turbojet inlet. / Kojima, Takayuki; Taguchi, Hideyuki; Kobayashi, Hiroaki; Satou, Tetsuya.

    20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015. AIAA American Institute of Aeronautics and Astronautics, 2015.

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

    Kojima, T, Taguchi, H, Kobayashi, H & Satou, T 2015, Starting characteristics of hypersonic pre-cooled turbojet inlet. in 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015. AIAA American Institute of Aeronautics and Astronautics, 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015, Glasgow, United Kingdom, 15/7/6.
    Kojima T, Taguchi H, Kobayashi H, Satou T. Starting characteristics of hypersonic pre-cooled turbojet inlet. In 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015. AIAA American Institute of Aeronautics and Astronautics. 2015
    Kojima, Takayuki ; Taguchi, Hideyuki ; Kobayashi, Hiroaki ; Satou, Tetsuya. / Starting characteristics of hypersonic pre-cooled turbojet inlet. 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference, 2015. AIAA American Institute of Aeronautics and Astronautics, 2015.
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    title = "Starting characteristics of hypersonic pre-cooled turbojet inlet",
    abstract = "In this study, bypass door area for the Hypersonic Precooled Turbojet Engine to restart the variable intake is estimated. Total pressure recovery and mass capture ratio of the variable air intake is acquired by the supersonic wind tunnel testing of the half scale intake model. Pressure loss and temperature effectiveness of the precooler is acquired by direct connect firing tests of the engine. Using these results, area of the bypass door by which the intake can start is estimated. The bypass door area to restart the intake depends on the precooler’s cooling capability. If the engine runs on liquid hydrogen, area of the bypass door is 1800mm2~2000mm2(Abyp_eng/A0=0.26~0.29). If the liquid nitrogen is used for the coolant of the precooler, area of the bypass door is 2600mm2~2700mm2(Abyp_eng/A0=0.37~0.39).",
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