| タイトル | Turbine vane leading edge gas film cooling with spanwise angled coolant holes |
| 著者（英） | Hanus, G. J.; Lecuyer, M. R. |
| 著者所属（英） | Purdue Univ. |
| 発行日 | 1976-01-01 |
| 言語 | eng |
| 内容記述 | An experimental film cooling study was conducted on a 3x size model turbine vane. Injection at the leading edge was from a single row of holes angled in a spanwise direction for two configurations of holes at 18 or 35 deg to the surface. The reduction in the local Stanton number for injection at a coolant-to-mainstream density ratio of 2.18 was calculated from heat flux measurements downstream of injection. Results indicate that optimum cooling occurs near a coolant-to-mainstream velocity ratio of 0.5. Shallow injection angles appear to be most beneficial when injecting into a highly accelerated mainstream. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 76A18754
AIAA PAPER 76-43 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/444478 |
