| タイトル | Hot-Gas-Slide and Coolant-Side Heat Transfer in Liquid Rocket Engine Combustors |
| 著者（英） | Wang, Ten-See; Luong, Van |
| 著者所属（英） | NASA Marshall Space Flight Center |
| 発行日 | 1994-07-01 |
| 言語 | eng |
| 内容記述 | The objectives of this article are to develop a multidisciplinary, computational methodology to predict the hot-gas-side and coolant-side heat transfer in film cooling assisted, regeneratively cooled liquid rocket engine combustors, and to use it in parametric studies to recommend optimized design of the coolant channels for a developmental combustor. An integrated numerical model which incorporates computational fluid dynamics (CFD) for the hot-gas thermal environment, and thermal analysis for the liner and coolant channels, was developed. This integrated CFD/thermal model was validated by comparing predicted heat fluxes with those of hot-firing test and industrial design methods for a 40-k calorimeter thrust chamber and the Space Shuttle Main Engine main combustion chamber. Parametric studies were performed for the advanced main combustion chamber to find a strategy for a proposed coolant channel design. |
| NASA分類 | Spacecraft Propulsion and Power |
| レポートNO | 97N70753
AIAA Paper 92-3151
NASA-TM-112106
NAS 1.15:112106 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/542031 |
