| タイトル | Review of NASA progress in thermal barrier coatings for stationary gas turbines |
| 本文（外部サイト） | http://hdl.handle.net/2060/19820009461 |
| 著者（英） | Gedwill, M. A.; Hodge, P. E.; Zaplatynsky, I.; Miller, R. A. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1981-01-01 |
| 言語 | eng |
| 内容記述 | Ceramic thermal barrier coatings for industrial/utility gas turbines were investigated. In burner rig tests of a zirconia yttria/nickel chromium aluminum yttrium ZrO2-12w/0Y2O3/NiCrAlY coating system on air cooled superalloy specimens, ceramic coating life (spallation) was sensitive to Na and V concentration in the fuel. The locations of coating spallation correspond to areas where combustion products were predicted to condense. Three new thermal barrier coating systems were identified. These are based on calcium silicate, ZrO2-8w/0Y2O3, and a MgO-NiCrAlY cermet. The spall resistance can be increased by reducing the ceramic layer thickness from 0.038 to 0.013 cm and by the use of more oxidation/corrosion resistant bond coats. |
| NASA分類 | METALLIC MATERIALS |
| レポートNO | 82N17335
E-749
NASA-TM-81716
DOE/NASA/2593-25 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/167039 |
