韩志勇,张涛,郭万森,王者,丁坤英.服役环境对涡轮导向叶片热障涂层失效模式的影响[J].表面技术,2023,52(4):261-271.
HAN Zhi-yong,ZHANG Tao,GUO Wan-sen,WANG Zhe,DING Kun-ying.Effects of Service Environment on Failure Modes of Thermal Barrier Coatings on Turbine Guide Blades[J].Surface Technology,2023,52(4):261-271 |
| 服役环境对涡轮导向叶片热障涂层失效模式的影响 |
| Effects of Service Environment on Failure Modes of Thermal Barrier Coatings on Turbine Guide Blades |
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| DOI：10.16490/j.cnki.issn.1001-3660.2023.04.023 |
| 中文关键词: 涡轮导向叶片 热障涂层 区域化 温度场 失效模式 |
| 英文关键词:turbine guide blade thermal barrier coating regionalization temperature field failure mode |
| 基金项目:中央高校基本科研业务经费重点项目(3122019189);天津市研究生科研创新项目(2021YJSO2B08) |
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| Author | Institution |
| HAN Zhi-yong | Tianjin Key Laboratory for Civil Aircraft Airworthiness and Maintenance, Civil Aviation University of China, Tianjin 300300, China |
| ZHANG Tao | Tianjin Key Laboratory for Civil Aircraft Airworthiness and Maintenance, Civil Aviation University of China, Tianjin 300300, China |
| GUO Wan-sen | Tianjin Key Laboratory for Civil Aircraft Airworthiness and Maintenance, Civil Aviation University of China, Tianjin 300300, China |
| WANG Zhe | Tianjin Key Laboratory for Civil Aircraft Airworthiness and Maintenance, Civil Aviation University of China, Tianjin 300300, China |
| DING Kun-ying | Tianjin Key Laboratory for Civil Aircraft Airworthiness and Maintenance, Civil Aviation University of China, Tianjin 300300, China |
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| 中文摘要: |
| 目的 基于服役环境下热障涂层失效行为的复杂性，分析服役环境对涡轮导向叶片热障涂层的影响，并总结涡轮导向叶片热障涂层的失效模式。方法 针对服役环境下某型民用航空发动机涡轮导向叶片，使用UG软件建模，并且采用FLUENT软件对其进行三维共轭传热计算，结合热障涂层宏微观形貌、钙镁铝硅酸盐(CMAS)侵蚀行为、热生长氧化物(TGO)的生长情况，以及孔隙率和硬度的变化，通过引入涂层损伤系数，建立一种新的热障涂层区域失效评估模式，综合分析服役环境对涡轮导向叶片热障涂层区域化失效模式的影响。结果 在经历了8 500 h服役后，涡轮导向叶片表面热障涂层的失效模式因服役环境的局部差异而不同。叶片前缘区域最高温度达到1 501.69 K，发生了严重的低熔点氧化物侵蚀，导致陶瓷层的孔隙率降至11.909%，TGO等效厚度生长至1.870 μm。后缘区域的最低温度为980.46 K，未见CMAS侵蚀，陶瓷层的孔隙率降至13.701%，TGO等效厚度生长至2.676 μm。叶盆、叶背表面平均温度分别为1 363.47 K和1 264.14 K，发生了轻度低熔点氧化物侵蚀，陶瓷层的孔隙率分别降至12.176%和13.371%，TGO等效厚度生长至6.959 μm和3.742 μm。结论 叶片前缘涂层烧结损伤系数为1.021 2，TGO损伤系数为0.269 1，主要失效模式为陶瓷层烧结。叶片后缘涂层烧结损伤系数为0.599 8，TGO损伤系数为0.385 0，失效模式为以烧结为主、TGO增厚为辅的联合失效，叶盆、叶背涂层烧结损伤系数分别为0.958 6和0.677 4，TGO损伤系数分别为1.001 6和0.538 4，主要失效模式均为烧结与TGO增厚并行的联合失效。 |
| 英文摘要: |
| As the service environment of turbine guide vanes becomes more and more severe, more and more attention is paid to the thermal barrier coating failure problem. However, there are still some shortcomings in the structure and performance evolution and failure behavior of the surface thermal barrier coating of turbine guide blades under real operating conditions. It is necessary to further improve the failure mechanism of the surface thermal barrier coating of turbine guide blades, and it is important to study different damage behaviors to establish a regionalized failure mode of the thermal barrier coating. In this paper, UG software was used to model and FLUENT software was used to calculate the three-dimensional conjugate heat transfer of a civil aero-engine turbine guide blade under service environment. Corresponding constant temperature test was conducted by collecting the temperature of flow field in each region. And scanning electron microscope and energy spectrometer were used to investigate the macro-microscopic morphology of the thermal barrier coating. The thermal barrier coating was subject to 0 h, 20 h, 50 h and 100 h of constant temperature oxidation. The macro and micro morphology of thermal barrier coating, the erosion behavior of calcium-magnesium-aluminosilicate (CMAS) and the growth of thermal growth oxide (TGO) as well as the changes of porosity and hardness were measured with scanning electron microscopy and energy spectroscopy. A new regional failure assessment model of thermal barrier coating was established by introducing coating damage coefficients, and the effects of service environment on the regionalized failure mode of the thermal barrier coating of aero-engine turbine guide blades was comprehensively analyzed. The results showed that after 8 500 hours of service, the failure mode of the thermal barrier coating on the surface of the turbine guide blade varied according to the local differences of the service environment. The highest temperature in the leading edge of the blade was 1 501.69 K, where severe low melting point oxide erosion occurred, resulting in the porosity of the ceramic layer dropping to 11.909% and the TGO equivalent thickness grew to 1.870 μm; The lowest temperature in the trailing edge was 980.46 K, where no CMAS erosion was observed and the porosity of the ceramic layer dropped to 13.701% and the TGO equivalent thickness grew to 2.676 μm. The average temperature of leaf basin and leaf back surface was 1 363.47 K and 1 264.14 K, respectively, and mild low melting point oxide erosion occurred, the porosity of ceramic layer decreased to 12.176% and 13.371%, respectively. The TGO equivalent thickness grew to 6.959 μm and 3.742 μm, respectively. The complex operating conditions of the final turbine guide blade led to different structural evolution and failure modes of the coating in each region. The leading edge of the blade coating had increased the oxygen diffusion activation energy to QO=105.6 kJ/mol due to severe CMAS erosion. The sintering damage factor is 1.021 2 and the TGO damage factor is 0.269 1, and the main failure mode is ceramic layer sintering. The sintering damage factor of the blade trailing edge coating is 0.599 8 and the TGO damage factor is 0.385 0, and the failure mode is a joint failure with sintering as the main factor and TGO thickening as the secondary factor. The sintering damage coefficient of leaf basin and leaf back coating is 0.958 6 and 0.677 4 respectively, and the TGO damage coefficient is 1.001 6 and 0.538 4 respectively, the main failure mode is the joint failure of sintering and TGO thickening. According to the above regionalized failure mode of turbine guide blade thermal barrier coating, each area of the blade can be treated with different modes of damage resistance in the future to provide direction for the subsequent life extension of turbine guide blades. |
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