| タイトル | Flow visualization of discrete hole film cooling for gas turbine applications |
| 本文（外部サイト） | http://hdl.handle.net/2060/19750018939 |
| 著者（英） | Russell, L. M.; Colladay, R. S. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1975-01-01 |
| 言語 | eng |
| 内容記述 | Film injection from discrete holes in a three row staggered array with 5-diameter spacing is studied. The boundary layer thickness-to-hole diameter ratio and Reynolds number are typical of gas turbine film cooling applications. Two different injection locations are studied to evaluate the effect of boundary layer thickness on film penetration and mixing. Detailed streaklines showing the turbulent motion of the injected air are obtained by photographing neutrally buoyant helium filled soap bubbles which follow the flow field. The bubble streaklines passing downstream injection locations are clearly identifiable and can be traced back to their origin. Visualization of surface temperature patterns obtained from infrared photographs of a similar film cooled surface are also included. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 75N27011
NASA-TM-X-71766
E-8418 |
| 権利 | No Copyright |
