| タイトル | Ceramic thermal-barrier coatings for cooled turbines |
| 本文（外部サイト） | http://hdl.handle.net/2060/19760023477 |
| 著者（英） | Stepka, F. S.; Liebert, C. H. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1976-01-01 |
| 言語 | eng |
| 内容記述 | Coating systems consisting of a plasma sprayed layer of zirconia stabilized with either yttria, magnesia or calcia over a thin alloy bond coat have been developed, their potential was analyzed and their durability and benefits evaluated in a turbojet engine. The coatings on air cooled rotating blades were in good condition after completing as many as 500 two-minute cycles of engine operation between full power at a gas temperature of 1644 K and flameout, or as much as 150 hours of steady state operation on cooled vanes and blades at gas temperatures as high as 1644 K with 35 start and stop cycles. On the basis of durability and processing cost, the yttria stabilized zirconia was considered the best of the three coatings investigated. |
| NASA分類 | MECHANICAL ENGINEERING |
| レポートNO | 76N30565
E-8766
NASA-TM-X-73426 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/184746 |
