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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NO74N10723
NASA-TN-D-7392
E-7461
権利No Copyright
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/196965


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