2021年
単一噴射器シミュレーションによる回転デトネーションエンジンの噴射圧力損失予測手法の提案
宇宙航空研究開発機構特別資料 JAXA-SP-(Web)
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- 巻
- JAXA-SP-20-008
- 号
- 20-008
- 開始ページ
- 1
- 終了ページ
- 10
- 記述言語
- 日本語
- 掲載種別
- DOI
- 10.2514/6.2020-3879
- 出版者・発行元
- 宇宙航空研究開発機構(JAXA)
流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2020オンライン (2020年9月28日-30日. 日本航空宇宙学会 : 宇宙航空研究開発機構(JAXA)オンライン会議)
Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online (September 28-30, 2020. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting)
Prediction of pressure loss in the injector for rotating detonation engine (RDE) needs to reproduce friction loss, entry loss, and shock wave back-propagation in injectors. This is challenging because calculation cost is high when whole region of RDE is studied. This paper proposes a new prediction method, ''single-element simulation'' to estimate pressure loss in injector with lower computational load. The calculation domain is limited to single-element of injector and its plenum in this method. The time-evolving boundary condition at injector outlet gives the effects of combustion chamber including the detonation propagation. In this paper, the single-element simulations are carried out for the rectangle injector and the chamfered injector for validation of the new method. The error of pressure loss prediction is less than 0.6%, which is 32-50 times faster than full-scale simulation.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
資料番号: AA2030013022
レポート番号: JAXA-SP-20-008
Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online (September 28-30, 2020. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting)
Prediction of pressure loss in the injector for rotating detonation engine (RDE) needs to reproduce friction loss, entry loss, and shock wave back-propagation in injectors. This is challenging because calculation cost is high when whole region of RDE is studied. This paper proposes a new prediction method, ''single-element simulation'' to estimate pressure loss in injector with lower computational load. The calculation domain is limited to single-element of injector and its plenum in this method. The time-evolving boundary condition at injector outlet gives the effects of combustion chamber including the detonation propagation. In this paper, the single-element simulations are carried out for the rectangle injector and the chamfered injector for validation of the new method. The error of pressure loss prediction is less than 0.6%, which is 32-50 times faster than full-scale simulation.
形態: カラー図版あり
Physical characteristics: Original contains color illustrations
資料番号: AA2030013022
レポート番号: JAXA-SP-20-008
- リンク情報
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- DOI
- https://doi.org/10.2514/6.2020-3879
- J-GLOBAL
- https://jglobal.jst.go.jp/detail?JGLOBAL_ID=202102224194637977
- CiNii Research
- https://cir.nii.ac.jp/crid/1050292561246271744?lang=ja
- Scopus
- https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85091308627&origin=inward
- Scopus Citedby
- https://www.scopus.com/inward/citedby.uri?partnerID=HzOxMe3b&scp=85091308627&origin=inward
- URL
- http://id.nii.ac.jp/1696/00047330/
- ID情報
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- DOI : 10.2514/6.2020-3879
- ISSN : 2433-2232
- J-Global ID : 202102224194637977
- CiNii Articles ID : 120006954820
- CiNii Research ID : 1050292561246271744
- SCOPUS ID : 85091308627