高栋,刘燚栋,张国栋,黄爱华.电子束物理气相沉积Yb掺杂Gd2Zr2O7/8YSZ双陶瓷层热障涂层性能研究[J].表面技术,2025,54(6):134-142.
GAO Dong,LIU Yidong,ZHANG Guodong,HUANG Aihua.Investigation to the Properties of Yb Doped Gd2Zr2O7/8YSZ Double Ceramic Layered Thermal Barrier Coatings Prepared by Electron Beam-Physical Vapor Deposition[J].Surface Technology,2025,54(6):134-142 |
| 电子束物理气相沉积Yb掺杂Gd2Zr2O7/8YSZ双陶瓷层热障涂层性能研究 |
| Investigation to the Properties of Yb Doped Gd2Zr2O7/8YSZ Double Ceramic Layered Thermal Barrier Coatings Prepared by Electron Beam-Physical Vapor Deposition |
| 投稿时间：2024-04-23 修订日期：2024-09-23 |
| DOI：10.16490/j.cnki.issn.1001-3660.2025.06.012 |
| 中文关键词: Yb-GZO/8YSZ双陶瓷层涂层 热循环 热导率 热稳定性 热腐蚀 |
| 英文关键词:Yb-GZO/8YSZ DCL coating thermal cycling thermal conductivity thermal stability hot corrosion |
| 基金项目: |
|
|
| Author | Institution |
| GAO Dong | AECC Commercial Aircraft Engine Co., Ltd., Shanghai 200241, China |
| LIU Yidong | AECC Commercial Aircraft Engine Co., Ltd., Shanghai 200241, China |
| ZHANG Guodong | AECC Commercial Aircraft Engine Co., Ltd., Shanghai 200241, China |
| HUANG Aihua | AECC Commercial Aircraft Engine Co., Ltd., Shanghai 200241, China |
|
| 摘要点击次数: |
| 全文下载次数: |
| 中文摘要: |
| 目的 分析电子束物理气相沉积Yb掺杂Gd2Zr2O7(简称为Yb-GZO)/8YSZ双陶瓷层涂层的关键性能，推动涂层工艺优化和质量提升。方法 采用镀铂渗铝在单晶合金试样表面制备金属黏结层，随后在黏结层上采用电子束物理气相沉积制备Yb-GZO/8YSZ双陶瓷层涂层，对涂层的高温相稳定性、热导率、燃气热腐蚀和热循环寿命等进行表征。结果 所制备的Yb-GZO/8YSZ双陶瓷涂层具有典型的柱状晶结构，涂层具有良好的应变容限，有利于延长涂层的热循环寿命，1 100 ℃下试样级涂层的热循环寿命不低于1 250个循环;陶瓷面层在1 450 ℃下具有良好的高温相稳定性;相对于8YSZ涂层，Yb-GZO涂层的热导率相对较低，在25~1 200 ℃范围内仅相当于8YSZ涂层的80%左右;900 ℃下Yb-GZO/8YSZ双陶瓷层涂层的燃气热腐蚀速率平均增重速率仅为0.018 g/(m2.h)，具有良好的抗热腐蚀能力;热循环失效的结果表明，贯穿性裂纹和层状分层剥落是涂层热循环失效的主要形式，TGO层内应力的增加和张应力松弛释放，以及黏结层附近高温塑性变形的耦合作用是造成热循环过程中热障涂层失效的主要原因。结论 Yb-GZO/8YSZ双陶瓷层热障涂层具有优异的高温服役性能，拥有更广泛的应用前景。 |
| 英文摘要: |
| With the efficiency and performance improvement of modern aircraft engines, the turbine inlet temperature (TIT) rises drastically over 2 000 K, leading to the result that conventional 8wt.% yttria stabilized zirconia (8YSZ) thermal barrier coatings (TBCs) which can only withstand long-term operation at temperatures of up to ~1 500 K are unable to meet the insulation requirements of the turbine blades, so it is imperative to develop new TBCs materials with better thermal stability and better thermal insulation properties. Gadolinium zirconate is considered as one of the most promising material systems for this application and the investigation to its properties is of great importance to promote its engineering application in the field of aircraft engines and gas turbines. Yb doped gadolinium zirconate (Yb-GZO)/8YSZ double ceramic layer (DCL) TBCs were prepared by electron beam-physical vapor deposition process (EB-PVD) in the present work and the critical properties, such as thermal stability, thermal conductivity, hot corrosion resistance and thermal cycling life, were tested, and the failure mechanism of the DCL coatings after furnace cycling test (FCT) was analyzed. Nickel-based single-crystal super alloy was used as substrate, and platinum aluminide bond coats were prepared on the surface of substrates by platinum electroplating and chemical vapor deposition aluminizing method sequentially, and a high temperature low activity (HTLA) aluminizing process was conducted under 1 045 ℃ for 4 hours. Then, the Yb-GZO/8YSZ DCL coating was deposited on the bond coats by EB-PVD method, and the high-temperature phase stability under 1 450 ℃, thermal conductivity, hot corrosion resistance, and thermal cycling life of the prepared DCL coating were investigated. The prepared Yb-GZO top coats was mainly composed of fluorite phase and a small amount of pyrochlore phases could be identified, and the thermal exposure test results indicated that the DCL coating had an excellent high-temperature phase stability up to 1 450 ℃ and no visible phase changes could be identified from the XRD patterns after high-temperature exposure for 300 hours. Additionally, the thermal conductivity of the Yb-GZO coating was significantly lower than that of the 8YSZ coating, which was only equivalent to about 80% of the latter in the temperature range from 25 ℃ to 1 200 ℃. In addition, the DCL coating had excellent hot corrosion resistance, and the weight gain rate was only 0.018 g/(m2.h) under exposure to 900℃ hot corrosion environment. On the other hand, the prepared Yb-GZO/8YSZ DLC had a typical columnar crystal structure, and its unique high strain tolerance characteristics were beneficial for improving the service life of the coating, and the FCT test results indicated that the thermal cycling life of the prepared coating was longer than 1 250 cycles for test under 1 100 ℃. The thermal cycling test results indicated that penetrating cracks and layer delamination were the main form of thermal cycling failure, and the coupling effect between the increase of stress inside the TGO layer and the release of tensile stress relaxation, as well as the high-temperature plastic deformation near the bonding layer, were the main reason for the failure of thermal barrier coatings during thermal cycling. The above research results indicate that the excellent properties of the DCL coating contribute to its further promotion and application. |
| 查看全文 查看/发表评论 下载PDF阅读器 |
| 关闭 |
|
|
|
渝公网安备 50010702501715号