| タイトル | LOX cooled thrust chamber technology developments |
| 著者（英） | Rousar, D. C.; Price, H. G.; Spencer, R. G. |
| 著者所属（英） | Aerojet Liquid Rocket Co.|NASA Lewis Research Center |
| 発行日 | 1978-07-01 |
| 言語 | eng |
| 内容記述 | An experimental LOX heat-transfer study and a LOX-cooled thrust-chamber demonstration program are summarized. Heat transfer to supercritical oxygen was investigated at 17 to 34.5 MPa (2460 to 5000 psia), and heat fluxes up to 90 MW/sq m (55 Btu/sq in.-sec). Experimental data obtained previously were correlated along with these recent data, and a design equation was derived which correlates 95% of the data within + or - 30%. Liquid-oxygen-cooled thrust chambers have been designed using this correlation and are currently being fabricated. A test program is planned for evaluating the LOX-cooled design concept using NASA test facilities. The purpose of these tests is to verify the LOX cooling correlation in a high-pressure liquid rocket engine and to determine the effects of a LOX coolant leak. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 78A43564
AIAA PAPER 78-1035 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/431910 |
