| タイトル | Heat flux measurement in SSME turbine blade tester |
| 本文（外部サイト） | http://hdl.handle.net/2060/19910001892 |
| 著者（英） | Liebert, Curt H. |
| 著者所属（英） | NASA Lewis Research Center |
| 発行日 | 1990-11-01 |
| 言語 | eng |
| 内容記述 | Surface heat flux values were measured in the turbine blade thermal cycling tester located at NASA-Marshall. This is the first time heat flux has been measured in a space shuttle main engine turbopump environment. Plots of transient and quasi-steady state heat flux data over a range of about 0 to 15 MW/sq m are presented. Data were obtained with a miniature heat flux gage device developed at NASA-Lewis. The results from these tests are being incorporated into turbine design models. Also, these gages are being considered for airfoil surface heat flux measurement on turbine vanes mounted in SSME turbopump test bed engine nozzles at Marshall. Heat flux effects that might be observed on degraded vanes are discussed. |
| NASA分類 | INSTRUMENTATION AND PHOTOGRAPHY |
| レポートNO | 91N11205
E-5719
NAS 1.15:103274
NASA-TM-103274 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/135562 |
