Design and fabrication of variable nozzle for precooled turbojet engine

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

研究成果: Conference contribution

6 引用 (Scopus)

抜粋

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.

元の言語English
ホスト出版物のタイトル16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
出版物ステータスPublished - 2009 12 1
イベント16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference - Bremen, Germany
継続期間: 2009 10 192009 10 22

出版物シリーズ

名前16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference

Conference

Conference16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference
Germany
Bremen
期間09/10/1909/10/22

ASJC Scopus subject areas

  • Engineering(all)

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  • これを引用

    Kojima, T., Kobayashi, H., Taguchi, H., Goto, K., & Sato, T. (2009). Design and fabrication of variable nozzle for precooled turbojet engine. : 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).