| タイトル | Liquid propellant rocket engine combustion simulation with a time-accurate CFD method |
| 本文（外部サイト） | http://hdl.handle.net/2060/19950017025 |
| 著者（英） | Hutt, J.; Shang, H. M.; Chen, Y. S.; Liaw, Paul |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 1993-07-01 |
| 言語 | eng |
| 内容記述 | Time-accurate computational fluid dynamics (CFD) algorithms are among the basic requirements as an engineering or research tool for realistic simulations of transient combustion phenomena, such as combustion instability, transient start-up, etc., inside the rocket engine combustion chamber. A time-accurate pressure based method is employed in the FDNS code for combustion model development. This is in connection with other program development activities such as spray combustion model development and efficient finite-rate chemistry solution method implementation. In the present study, a second-order time-accurate time-marching scheme is employed. For better spatial resolutions near discontinuities (e.g., shocks, contact discontinuities), a 3rd-order accurate TVD scheme for modeling the convection terms is implemented in the FDNS code. Necessary modification to the predictor/multi-corrector solution algorithm in order to maintain time-accurate wave propagation is also investigated. Benchmark 1-D and multidimensional test cases, which include the classical shock tube wave propagation problems, resonant pipe test case, unsteady flow development of a blast tube test case, and H2/O2 rocket engine chamber combustion start-up transient simulation, etc., are investigated to validate and demonstrate the accuracy and robustness of the present numerical scheme and solution algorithm. |
| NASA分類 | FLUID MECHANICS AND HEAT TRANSFER |
| レポートNO | 95N23445 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/108102 |
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