| タイトル | Energy efficient engine, high pressure turbine thermal barrier coating. Support technology report |
| 本文（外部サイト） | http://hdl.handle.net/2060/19850026886 |
| 著者（英） | Agarwal, P.; Duderstadt, E. C. |
| 著者所属（英） | General Electric Co. |
| 発行日 | 1983-05-01 |
| 言語 | eng |
| 内容記述 | This report describes the work performed on a thermal barrier coating support technology task of the Energy Efficient Engine Component Development Program. A thermal barrier coating (TBC) system consisting of a Ni-Cr-Al-Y bond cost layer and ZrO2-Y2O3 ceramic layer was selected from eight candidate coating systems on the basis of laboratory tests. The selection was based on coating microstructure, crystallographic phase composition, tensile bond and bend test results, erosion and impact test results, furnace exposure, thermal cycle, and high velocity dynamic oxidation test results. Procedures were developed for applying the selected TBC to CF6-50, high pressure turbine blades and vanes. Coated HPT components were tested in three kinds of tests. Stage 1 blades were tested in a cascade cyclic test rig, Stage 2 blades were component high cycle fatigue tested to qualify thermal barrier coated blades for engine testing, and Stage 2 blades and Stage 1 and 2 vanes were run in factory engine tests. After completion of the 1000 cycle engine test, the TBC on the blades was in excellent condition over all of the platform and airfoil except at the leading edge above midspan on the suction side of the airfoil. The coating damage appeared to be caused by particle impingement; adjacent blades without TBC also showed evidence of particle impingement. |
| NASA分類 | AIRCRAFT PROPULSION AND POWER |
| レポートNO | 85N35199
NASA-CR-168037
NAS 1.26:168037
R82AEB293 |
| 権利 | No Copyright |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/155631 |
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