| タイトル | Stagnation region gas film cooling for turbine blade leading edge applications |
| 著者（英） | Winstanley, D. K.; Hanus, G. J.; Lecuyer, M. R.; Luckey, D. W. |
| 著者所属（英） | Purdue Univ. |
| 発行日 | 1976-07-01 |
| 言語 | eng |
| 内容記述 | An experimental investigation was conducted to model the film-cooling performance for a turbine-vane leading edge using the stagnation region of a cylinder in cross flow. Experiments were conducted with a single row of spanwise-angled coolant holes for a range of the coolant blowing ratio with a freestream-to-wall temperature ratio of about 2.1 and a Reynolds number of 170,000, characteristic of the gas-turbine environment. Data from local heat-flux measurements are presented for coolant-hole injection angles of 25, 35, and 45 deg with the row of holes located at three positions relative to the stagnation line on the cylinder. Results show the spanwise (hole-to-hole) variation of heat-flux reduction due to film cooling and indicate conditions for the optimum film-cooling performance. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 76A38233
AIAA PAPER 76-728 |
| 権利 | Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/442541 |
|
