タイトル | Reliability and effective thermal conductivity of three metallic-ceramic composite insulating coatings on cooled hydrogen-oxygen rockets |
本文(外部サイト) | http://hdl.handle.net/2060/19740002610 |
著者(英) | Schacht, R. L.; Price, H. G., Jr.; Quentmeyer, R. J. |
著者所属(英) | NASA Lewis Research Center |
発行日 | 1973-11-01 |
言語 | eng |
内容記述 | An experimental investigation of the structural integrity and effective thermal conductivity of three metallic-ceramic composite coatings was conducted. These coatings were plasma sprayed onto the combustion side of water-cooled, 12.7-centimeter throat diameter, hydrogen-oxygen rocket thrust chambers operating at 2.07 to 4.14 meganewtons per square meter chamber pressure. The metallic-ceramic composites functioned for six to 17 cycles and for as long as 213 seconds of rocket operations and could have probably provided their insulating properties for many additional cycles. The effective thermal conductivity of all the coatings was in the range of 0.7472 to 4.483 w/(m)(K), which makes the coatings a very effective thermal barrier. Photomicrographic studies of cross-sectioned coolant tubes seem to indicate that the effective thermal conductivity of the coatings is controlled by contact resistance between the particles, as a result of the spraying process, and not the thermal conductivity of the bulk materials. |
NASA分類 | PROPULSION SYSTEMS |
レポートNO | 74N10723 NASA-TN-D-7392 E-7461 |
権利 | No Copyright |
URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/196965 |