| タイトル | Thermal stratification potential in rocket engine coolant channels |
| 本文（外部サイト） | http://hdl.handle.net/2060/19920016373 |
| 著者（英） | Kacynski, Kenneth J. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1992-05-01 |
| 言語 | eng |
| 内容記述 | The potential for rocket engine coolant channel flow stratification was computationally studied. A conjugate, 3-D, conduction/advection analysis code (SINDA/FLUINT) was used. Core fluid temperatures were predicted to vary by over 360 K across the coolant channel, at the throat section, indicating that the conventional assumption of a fully mixed fluid may be extremely inaccurate. Because of the thermal stratification of the fluid, the walls exposed to the rocket engine exhaust gases will be hotter than an assumption of full mixing would imply. In this analysis, wall temperatures were 160 K hotter in the turbulent mixing case than in the full mixing case. The discrepancy between the full mixing and turbulent mixing analyses increased with increasing heat transfer. Both analysis methods predicted identical channel resistances at the coolant inlet, but in the stratified analysis the thermal resistance was negligible. The implications are significant. Neglect of thermal stratification could lead to underpredictions in nozzle wall temperatures. Even worse, testing at subscale conditions may be inadequate for modeling conditions that would exist in a full scale engine. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 92N25616
NASA-TM-4378
E-6135
NAS 1.15:4378 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/126975 |
|
