| 高 栋，刘燚栋，张国栋，黄爱华.面向产品研制需求的单晶涡轮叶片热障涂层考核验证[J].航空发动机,2025,51(2):142-149 |
| 面向产品研制需求的单晶涡轮叶片热障涂层考核验证 |
| Verification of Thermal Barrier Coatings for Single-Crystal Turbine Blades Orientated forProduct Development Requirements |
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| DOI： |
| 中文关键词: 热障涂层 技术需求 单晶涡轮叶片 试验验证 航空发动机 |
| 英文关键词:thermal barrier coating technical requirement single-crystal turbine blade test verification aeroengine |
| 基金项目:航空动力基础研究项目资助 |
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| 摘要点击次数: 1487 |
| 全文下载次数: 671 |
| 中文摘要: |
| 为建立适用于商用航空发动机单晶涡轮叶片热障涂层的正向研发体系，形成热障涂层的系统研制路径，加快单晶涡轮
叶片热障涂层研发进度，系统分析了发动机高压涡轮叶片热障涂层的工作场景，并充分考虑适航条款对涂层材料及工艺的要求，
在此基础上建立了发动机产品对单晶叶片热障涂层的完整需求。针对所形成的需求逐项分解至热障涂层的技术指标，并对指标
的验证策略进行分析，构建了涵盖材料级、试样级、零件级、部件级的单晶涡轮叶片热障涂层试验验证数据三角形，并基于PtAl+
8YSZ热障涂层体系对各项试验方法的适用性进行了初步验证。结果表明：在材料级试验验证中，连续10个批次靶材的CPk值为
2.33，即靶材质量一致性较高。在试样级试验验证中，涂层的热导率随温度上升而下降，温度高于600 ℃时涂层热导率在1.7 W/
（m·K）以下；涂层厚度对服役寿命有显著影响，1100 ℃下厚度为 0.35 mm涂层热循环寿命约为0.15 mm厚度涂层的1/4；CMAS腐蚀
对涂层寿命影响显著，1250 ℃下300个热冲击CMAS循环后，涂层柱状晶结构明显退化。零件级和部件级试验验证进一步明确了
涂层性能的符合性和改进方向。所构建的考核验证体系基本满足商用航空发动机产品研制的需求，确定的考核验证方法适用性
较强，可支撑产品研制过程。 |
| 英文摘要: |
| To establish a forward R&D system tailored for thermal barrier coatings (TBCs) on single-crystal turbine blades in com?
mercial aeroengines, formulate a systematic R&D approach, and expedite the R&D progress of these coatings. A comprehensive analysis of
the operational scenarios of TBCs on high-pressure turbine blades was systematically conducted while meticulously incorporating airworthi?
ness requirements for coating materials and processes. Based on this, a holistic set of requirements for single-crystal blade TBCs in
aeroengine products was delineated. The requirements were decomposed into specific technical indicators for TBCs, and the verification
strategies for these indicators were analyzed. A test verification data pyramid chart for TBCs on single-crystal turbine blades was
constructed, spanning material-level, specimen-level, part-level, and component-level. The applicability of these testing methods was
preliminarily verified based on the PtAl+8YSZ thermal barrier coating system. The material-level test verification results show that the
CPk value of ten consecutive batches of target materials is 2.33, indicating high consistency in target material quality. In the specimen-
level test verification, the thermal conductivity of the coating decreases with increasing temperature, and the coating thermal conductivity is
below 1.7 W/(m·K) when the temperature is higher than 600 ℃; the coating thickness has a significant impact on the service life, at
1100 ℃, the thermal cyclic life of the coating with a thickness of 0.35 mm is about 1/4 of that of the coating with a thickness of 0.15 mm;
CMAS corrosion has a significant effect on the coating life, with 300 thermal shock CMAS cycles at 1250 ℃ causing notable deterioration of
the columnar crystal structure of the coating. The results of part-level and component-level test verification further clarify the compliance
and improvement directions of the coating performance. The verification results show that the established verification system basically
meets the product development requirements of commercial aeroengines, and the determined verification methods have strong applicability
and can support the product development process. |
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