Visualization of flames in combustion chamber of hybrid rocket engine with multi-section swirl injection method

Hiroshi Tada, Shigeru Aso, Yasuhiro Tani, Sho Ohyama, Kentaro Araki, Kengo Ohe, Masato Mizuchi, Toru Shimada

研究成果: 著書/レポートタイプへの貢献会議での発言

5 引用 (Scopus)

抄録

In order to clarify combustion phenomena of hybrid rocket engines with multi-section swirl injection method, visualization tests of combustion flames has been conducted. In the present paper, paraffin fuel whose regression rate is high was used, and several types of placement of ports which inject oxygen into combustion chamber were compared. The number of the ports in each section had marginal effect on a combustion phenomenon. On the other hand the distance between each cross-section affected performance and combustion phenomena. In multi-section opposite injection method, the flow toward downstream of combustion chamber was observed. In both methods, enlarging the surface area that high temperature gas flows along was very important to increase regression rate.

元の言語英語
ホスト出版物のタイトル50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014
出版者American Institute of Aeronautics and Astronautics Inc.
ISBN(電子版)9781624103032
DOI
出版物ステータス出版済み - 1 1 2014
イベント50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014 - Cleveland, 米国
継続期間: 7 28 20147 30 2014

出版物シリーズ

名前50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014

その他

その他50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014
米国
Cleveland
期間7/28/147/30/14

Fingerprint

Rocket engines
Combustion chambers
Visualization
Paraffins
Flow of gases
Oxygen
Temperature

All Science Journal Classification (ASJC) codes

  • Energy Engineering and Power Technology
  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Mechanical Engineering

これを引用

Tada, H., Aso, S., Tani, Y., Ohyama, S., Araki, K., Ohe, K., ... Shimada, T. (2014). Visualization of flames in combustion chamber of hybrid rocket engine with multi-section swirl injection method. : 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014 (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2014-3850

Visualization of flames in combustion chamber of hybrid rocket engine with multi-section swirl injection method. / Tada, Hiroshi; Aso, Shigeru; Tani, Yasuhiro; Ohyama, Sho; Araki, Kentaro; Ohe, Kengo; Mizuchi, Masato; Shimada, Toru.

50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc., 2014. (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014).

研究成果: 著書/レポートタイプへの貢献会議での発言

Tada, H, Aso, S, Tani, Y, Ohyama, S, Araki, K, Ohe, K, Mizuchi, M & Shimada, T 2014, Visualization of flames in combustion chamber of hybrid rocket engine with multi-section swirl injection method. : 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014, American Institute of Aeronautics and Astronautics Inc., 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and exhibit 2014, Cleveland, 米国, 7/28/14. https://doi.org/10.2514/6.2014-3850
Tada H, Aso S, Tani Y, Ohyama S, Araki K, Ohe K その他. Visualization of flames in combustion chamber of hybrid rocket engine with multi-section swirl injection method. : 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc. 2014. (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014). https://doi.org/10.2514/6.2014-3850
Tada, Hiroshi ; Aso, Shigeru ; Tani, Yasuhiro ; Ohyama, Sho ; Araki, Kentaro ; Ohe, Kengo ; Mizuchi, Masato ; Shimada, Toru. / Visualization of flames in combustion chamber of hybrid rocket engine with multi-section swirl injection method. 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014. American Institute of Aeronautics and Astronautics Inc., 2014. (50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2014).
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abstract = "In order to clarify combustion phenomena of hybrid rocket engines with multi-section swirl injection method, visualization tests of combustion flames has been conducted. In the present paper, paraffin fuel whose regression rate is high was used, and several types of placement of ports which inject oxygen into combustion chamber were compared. The number of the ports in each section had marginal effect on a combustion phenomenon. On the other hand the distance between each cross-section affected performance and combustion phenomena. In multi-section opposite injection method, the flow toward downstream of combustion chamber was observed. In both methods, enlarging the surface area that high temperature gas flows along was very important to increase regression rate.",
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