Design and fabrication of variable nozzle for precooled turbojet engine

Takayuki Kojima, Hiroaki Kobayashi, Hideyuki Taguchi, Ken Goto, Tetsuya Satou

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

    6 Citations (Scopus)

    Abstract

    The afterburner and the variable nozzle for the small precooled turbojet engine (S-engine) are fabricated and firing tests of the engine were conducted. The nozzle adopts rectangular configuration because throat area of the nozzle must vary for 2.5 times. A regenerative cooling is adopted on the ramp of the afterburner and fuel of the afterburner (liquid hydrogen) is reheated at the wall. C/C-Si composite material is adopted on the sidewall and the cowl of the nozzle, for weight reduction. After the structure tests of the C/C-Si subscale components, the sidewall and the cowl made of C/C-Si are designed and fabricated which has 12 mm of wall thickness. Four series of firing experiments are conducted for the S-engine by now. In these experiments, the afterburner was used at three experiments. Afterburner was turned on for approximately 10 sec for each firing tests. As a result of the experiments, we confirmed that temperature inside the afterburner was uniform. For the fuel rich combustor, it is important to pass the stoichiometric fuel flow rate during ignition to prevent the wall from overheating. However, if fuel flow rate increases rapidly, ignition fails.

    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
    Nozzles
    Fabrication
    Ignition
    Experiments
    Flow rate
    Combustors
    Engines
    Cooling
    Hydrogen
    Composite materials
    Liquids
    Temperature

    ASJC Scopus subject areas

    • Engineering(all)

    Cite this

    Kojima, T., Kobayashi, H., Taguchi, H., Goto, K., & Satou, T. (2009). Design and fabrication of variable nozzle for precooled turbojet engine. In 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference [2009-7312]

    Design and fabrication of variable nozzle for precooled turbojet engine. / Kojima, Takayuki; Kobayashi, Hiroaki; Taguchi, Hideyuki; Goto, Ken; Satou, Tetsuya.

    16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. 2009. 2009-7312.

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

    Kojima, T, Kobayashi, H, Taguchi, H, Goto, K & Satou, T 2009, Design and fabrication of variable nozzle for precooled turbojet engine. in 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference., 2009-7312, 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference, Bremen, 09/10/19.
    Kojima T, Kobayashi H, Taguchi H, Goto K, Satou T. Design and fabrication of variable nozzle for precooled turbojet engine. In 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. 2009. 2009-7312
    Kojima, Takayuki ; Kobayashi, Hiroaki ; Taguchi, Hideyuki ; Goto, Ken ; Satou, Tetsuya. / Design and fabrication of variable nozzle for precooled turbojet engine. 16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. 2009.
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    abstract = "The afterburner and the variable nozzle for the small precooled turbojet engine (S-engine) are fabricated and firing tests of the engine were conducted. The nozzle adopts rectangular configuration because throat area of the nozzle must vary for 2.5 times. A regenerative cooling is adopted on the ramp of the afterburner and fuel of the afterburner (liquid hydrogen) is reheated at the wall. C/C-Si composite material is adopted on the sidewall and the cowl of the nozzle, for weight reduction. After the structure tests of the C/C-Si subscale components, the sidewall and the cowl made of C/C-Si are designed and fabricated which has 12 mm of wall thickness. Four series of firing experiments are conducted for the S-engine by now. In these experiments, the afterburner was used at three experiments. Afterburner was turned on for approximately 10 sec for each firing tests. As a result of the experiments, we confirmed that temperature inside the afterburner was uniform. For the fuel rich combustor, it is important to pass the stoichiometric fuel flow rate during ignition to prevent the wall from overheating. However, if fuel flow rate increases rapidly, ignition fails.",
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