| タイトル | Coolant passage heat transfer with rotation |
| 本文（外部サイト） | http://hdl.handle.net/2060/19850002660 |
| 著者（英） | Rohde, J. E. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1982-10-01 |
| 言語 | eng |
| 内容記述 | Although the effects of the coriolis and buoyancy forces due to rotation on coolant-side heat transfer are generally not included in the design methods for blades, the influence of these forces could be large. Comparisons of nonrotating heat transfer data and extrapolations of available correlation for the average heat transfer coefficients with radial outflow of cooling air showed that neglecting rotation at gas turbine engine conditions result in variations in the heat transfer coefficient by as much as 45 percent. This, in effect, results in blade metal temperatures running as much as 100 F different from predicted values. This also may explain why rotating blade metal temperatures in engine tests are often higher than expected from results obtained in nonrotating cascade tests. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 85N10968 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/567160 |
