| タイトル | Prolonging thermal barrier coated specimen life by thermal cycle management |
| 著者（英） | Hendricks, R. C.; Poolos, N. P.; Mcdonald, G. |
| 著者所属（英） | NASA Lewis Research Center|Harvard Univ. |
| 発行日 | 1981-04-01 |
| 言語 | eng |
| 内容記述 | Thermal barrier coatings applied to the heated side of engine components such as seals, combustor, and blades of a gas turbine offer a potential increase in efficiency through the use of higher gas temperatures or less cooling air or benefits arising from extended component life by reducing component metal temperatures. The considered investigation has the objective to show that while a thermal barrier coated (TBC) specimen can be brought to a fixed temperature using various fuel-air ratio (F/A) values, lower calculated stresses are associated with lower (F/A) values. This implies that control of (F/A) values (i.e., rates of heat input) during the starting transient and to a lesser extent during shutdown and operation, offers a potential method of improving TBC lifetime through thermal cycle management. |
| NASA分類 | NONMETALLIC MATERIALS |
| レポートNO | 81A44658 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/415442 |
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