| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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|
タイトル |
水素酸素ロケット燃焼室内の拡散燃焼シミュレーション |
| 言語 |
|
|
言語 |
jpn |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_18gh |
|
資源タイプ |
technical report |
| その他のタイトル（英） |
|
|
その他のタイトル |
Numerical Simulation Method for Combustion in a Oxyhydrogen Rocket Motor |
| 著者 |
滝, 史郎
藤原, 俊隆
Taki, Shiro
Fujiwara, Toshitaka
|
| 著者所属 |
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|
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福井大学工学部 |
| 著者所属 |
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名古屋大学工学部 |
| 著者所属（英） |
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|
en |
|
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Department of Mechanical Engineering , Fukui University |
| 著者所属（英） |
|
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|
en |
|
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Department of Aerospace Engineering, Nagoya University |
| 出版者 |
|
|
出版者 |
航空宇宙技術研究所 |
| 出版者（英） |
|
|
出版者 |
National Aerospace Laboratory(NAL) |
| 書誌情報 |
航空宇宙技術研究所特別資料
en : Special Publication of National Aerospace Laboratory SP-3
巻 3,
p. 131-140,
発行日 1984-11
|
| 抄録（英） |
|
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内容記述タイプ |
Other |
|
内容記述 |
Numerical simulations of unsteady phenomena in the combustion chamber of an oxyhydrogen rocket motor were made in an attempt to develop a computer code for use in investigating such phenomena as vibrating combustion. The combustion in this system is controlled by diffusion, the effect of which works much slower than sound or pressure waves, so that diffusions are usually solved using the implicit finite difference method for unlimited time step size caused by stability criterion. However, the gases flow so fast, accompanied by unsteady pressure waves, that an explicit method is adopted to solve this problem. The way of modeling the turbulent diffusion combustion is very important in this simulation. The fine structures of turbulence and diffusion flame could not be calculated by a finite difference method because of the limited ability of computers. It is presumed that the size of the space difference should be less than or the same order as that of the small eddies. In the present example of simulation, eddy equations are not solved; rather the reasonable transport coefficients for small eddies are simply used. Chemical reactions are also simplified. The gases assumed consist of three components, i. e., fuel, oxidizer and product. In turbulent diffusion burning, rate constants for chemical reactions are to be smaller than those in premixed gas, for the composition at a lattice point is not exact but averaged. Especially for diffusion combustion, the artificial diffusion included in the finite difference scheme must be smaller than the actual diffusion. A brief estimation shows that the space mesh size should be the same order as the turbulent diffusion coefficient divided by flow velocity. An example of simulation using MacCormack's explicit method is shown, where vibrations appear after ignition, followed by attenuation. The results indicate the possibility of numerical simulation of unsteady phenomena in an oxyhydrogen rocket motor, though it is still necessary to make comparisons with experiments to fix some parameters. |
| ISSN |
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収録物識別子タイプ |
ISSN |
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収録物識別子 |
0289-260X |
| 書誌レコードID |
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収録物識別子タイプ |
NCID |
|
収録物識別子 |
AN10097345 |
| 資料番号 |
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|
内容記述タイプ |
Other |
|
内容記述 |
資料番号: NALSP0003016 |
| レポート番号 |
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|
内容記述タイプ |
Other |
|
内容記述 |
レポート番号: NAL SP-3 |
nalsp0003016.pdf (721.1 kB)
