| タイトル | Rocket thrust chamber thermal barrier coatings |
| 本文（外部サイト） | http://hdl.handle.net/2060/19860011026 |
| 著者（英） | Batakis, A. P.; Vogan, J. W. |
| 著者所属（英） | Solar Turbines, Inc. |
| 発行日 | 1985-07-01 |
| 言語 | eng |
| 内容記述 | A research program was conducted to generate data and develop analytical techniques to predict the performance and reliability of ceramic thermal barrier coatings in high heat flux environments. A finite element model was used to analyze the thermomechanical behavior of coating systems in rocket thrust chambers. Candidate coating systems (using a copper substrate, NiCrAlY bond coat and ZrO2.8Y2O3 ceramic overcoat) were selected for detailed study based on photomicrographic evaluations of experimental test specimens. The effects of plasma spray application parameters on the material properties of these coatings were measured and the effects on coating performance evaluated using the finite element model. Coating design curves which define acceptable operating envelopes for seleted coating systems were constructed based on temperature and strain limitations. Spray gun power levels was found to have the most significant effect on coating structure. Three coating systems were selected for study using different power levels. Thermal conductivity, strain tolerance, density, and residual stress were measured for these coatings. Analyses indicated that extremely thin coatings ( 0.02 mm) are required to accommodate the high heat flux of a rocket thrust chamber and ensure structural integrity. |
| NASA分類 | SPACECRAFT PROPULSION AND POWER |
| レポートNO | 86N20497
NAS 1.26:175022
NASA-CR-175022
SR85-R-5052-16 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/154653 |
