| タイトル | Composite wall concept for high temperature turbine shrouds: Heat transfer analysis |
| 本文（外部サイト） | http://hdl.handle.net/2060/19800018861 |
| 著者（英） | Stepka, F. S.; Ludwig, L. P. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1980-01-01 |
| 言語 | eng |
| 内容記述 | A heat transfer analysis was made of a composite wall shroud consisting of a ceramic thermal barrier layer bonded to a porous metal layer which, in turn, is bonded to a metal base. The porous metal layer serves to mitigate the strain differences between the ceramic and the metal base. Various combinations of ceramic and porous metal layer thicknesses and of porous metal densities and thermal conductivities were investigated to determine the layer thicknesses required to maintain a limiting temperature in the porous metal layer. Analysis showed that the composite wall offered significant air cooling flow reductions compared to an all impingement air cooled, all metal shroud. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 80N27362
NASA-TM-81539
E-402 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/172023 |
