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Propulsive Performance and Heating Environment of Rotating Detonation Engine with Various Nozzles
http://hdl.handle.net/2237/00030377
http://hdl.handle.net/2237/000303772002bcbf-c400-4d31-962e-eb4090db05e3
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
revised_manuscript_Goto (3.1 MB)
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| Item type | 学術雑誌論文 / Journal Article(1) | |||||
|---|---|---|---|---|---|---|
| 公開日 | 2019-05-29 | |||||
| タイトル | ||||||
| タイトル | Propulsive Performance and Heating Environment of Rotating Detonation Engine with Various Nozzles | |||||
| 言語 | en | |||||
| 著者 |
Goto, Keisuke
× Goto, Keisuke× Nishimura, Junpei× Kawasaki, Akira× Matsuoka, Ken× Kasahara, Jiro× Matsuo, Akiko× Funaki, Ikkoh× Nakata, Daisuke× Uchiumi, Masaharu× Higashino, Kazuyuki |
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| アクセス権 | ||||||
| アクセス権 | open access | |||||
| アクセス権URI | http://purl.org/coar/access_right/c_abf2 | |||||
| 権利 | ||||||
| 言語 | en | |||||
| 権利情報 | Copyright © 2018 by Nagoya University. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the ISSN 0748-4658 (print) or 1533-3876 (online) to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp. | |||||
| 抄録 | ||||||
| 内容記述タイプ | Abstract | |||||
| 内容記述 | Geometric throats are commonly applied to rocket combustors to increase pressure and specific impulse. This paper presents the results from thrust measurements of an ethylene/gas-oxygen rotating detonation engine with various throat geometries in a vacuum chamber to simulate varied backpressure conditions in a range of 1.1–104 kPa. For the throatless case, the detonation channel area was regarded to be equivalent the throat area, and three throat-contraction ratios were tested: 1, 2.5, and 8. Results revealed that combustor pressure was approximately proportional to equivalent throat mass flux for all test cases. Specific impulse was measured for a wide range of pressure ratios, defined as the ratio of the combustor pressure to the backpressure in the vacuum chamber. The rotating detonation engine could achieve almost the same level of optimum specific impulse for each backpressure, whether or not flow was squeezed by a geometric throat. In addition, heat-flux measurements using heat-resistant material are summarized. Temporally and spatially averaged heat flux in the engine were roughly proportional to channel mass flux. Heat-resistant material wall compatibility with two injector shapes of doublet and triplet injection is also discussed. | |||||
| 言語 | en | |||||
| 内容記述 | ||||||
| 内容記述タイプ | Other | |||||
| 内容記述 | Published online: 12 November 2018 | |||||
| 言語 | en | |||||
| 出版者 | ||||||
| 出版者 | American Institute of Aeronautics and Astronautics | |||||
| 言語 | en | |||||
| 言語 | ||||||
| 言語 | eng | |||||
| 資源タイプ | ||||||
| 資源タイプresource | http://purl.org/coar/resource_type/c_6501 | |||||
| タイプ | journal article | |||||
| 出版タイプ | ||||||
| 出版タイプ | AM | |||||
| 出版タイプResource | http://purl.org/coar/version/c_ab4af688f83e57aa | |||||
| DOI | ||||||
| 関連タイプ | isVersionOf | |||||
| 識別子タイプ | DOI | |||||
| 関連識別子 | https://doi.org/10.2514/1.B37196 | |||||
| ISSN（print） | ||||||
| 収録物識別子タイプ | PISSN | |||||
| 収録物識別子 | 0748-4658 | |||||
| 書誌情報 |
en : Journal of Propulsion and Power 巻 35, 号 1, p. 213-223, 発行日 2019-01 |
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| 著者版フラグ | ||||||
| 値 | author | |||||
