| タイトル | Experimental heat transfer and flow results of a chordwise-finned turbine vane with impingement, film, and convection cooling |
| 本文（外部サイト） | http://hdl.handle.net/2060/19720015290 |
| 著者（英） | Gauntner, J. W.; Lane, J. M.; Hickel, R. O.; Dengler, R. P. |
| 著者所属（英） | Army Air Mobility Research and Development Lab.|NASA Lewis Research Center |
| 発行日 | 1972-04-01 |
| 言語 | eng |
| 内容記述 | Experimental heat transfer data are presented for a vane tested in a turbojet engine at turbine inlet gas temperatures to 1644 K (2500 F), coolant temperatures to 700 K (800 F), and coolant-to-gas flow ratios to 0.187. Methods are presented for correlating heat transfer data and obtaining coolant flow distribution through the vane. Calculated and measured coolant flow distributions and vane metal temperatures are compared. |
| NASA分類 | THERMODYNAMICS AND COMBUSTION |
| レポートNO | 72N22940
NASA-TM-X-2472
E-6547 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/203548 |
