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应用于航空发动机涡轮叶片的热障涂层材料研究Title: Research on Thermal Barrier Coating Materials for Turbine Blades in Aircraft EnginesIntroduction:In recent decades, the aviation industry has witnessed significant advancements in the field of aerospace engines, leading to improved efficiency and performance. One critical area of focus in engine development is the use of thermal barrier coatings (TBCs) on turbine blades. TBCs are essential in protecting turbine blades from excessive heat and harsh operating environments, ultimately enhancing the longevity and reliability of the engine. This article aims to explore the research and development of TBC materials and their application in aircraft engines.1. Significance of Thermal Barrier Coatings:Turbine blades in aircraft engines operate in extreme conditions, exposed to high temperatures, thermal cycling, and corrosive gases. The application of TBCs addresses these challenges by creating a protective layer that insulates the blade from the high-temperature combustion gases, reducing the heat transfer to the blade itself.2. Composition and Characteristics of TBC Materials: The current generation of TBCs primarily consists of a multilayered structure, typically composed of a metallic bond coat, a thermally grown oxide (TGO) layer, and a ceramic topcoat. The bond coat is usually made of materials like nickel-chromium-aluminum alloys, which provide oxidationresistance. The TGO layer is formed between the bond coat and the ceramic topcoat, comprising alumina and other oxides. The topcoat, typically yttria-stabilized zirconia (YSZ), is the primary thermal insulator.3. Thermal Resistance Mechanisms:Thermal barrier coatings exhibit thermal resistance through several mechanisms. Firstly, the low thermal conductivity of ceramic materials acts as a barrier to heat transfer. Secondly, the topcoat's strain tolerance and low thermal expansion coefficient prevent cracking caused by thermal cycling. Lastly, the TGO layer acts as a diffusion barrier, preventing the migration of harmful species from the bond coat to the topcoat.4. Challenges in TBC Development:The development of TBC materials faces several challenges. High-temperature corrosion, including hot corrosion and erosion, poses a significant threat to TBC performance. Additionally, the delamination of TBCs due to thermal stresses and interfacial defects requires further attention. Moreover, the limited understanding of TBCs' long-term behavior in service conditions necessitates ongoing research.5. Research on New TBC Materials:Various research efforts have been focused on exploring alternative materials for TBCs. Novel ceramic materials like rare-earth zirconates and hafnia-based oxides show improved thermal and chemical stability compared to YSZ. The use of bond coat modifications, such as diffusion barrier layers and protective overlays, has also been investigated to enhance TBC performance.6. Advanced TBC Manufacturing Techniques:Advancements in manufacturing techniques play a crucial rolein improving TBC performance and reliability. Techniques like electron beam physical vapor deposition (EBPVD) and advanced thermal spray methods offer enhanced coating quality, reduced spallation, and improved strain tolerance. Advanced manufacturing processes are continuously being developed to meet the increasing demands of TBC applications.7. Future Directions and Conclusion:The research and development of TBC materials for aircraft engine turbine blades are essential for the continued advancement of aviation technology. Further research is needed to improve TBC performance under extreme operating conditions, such as high-temperature corrosion and strain tolerance. Exploring emerging materials and manufacturing techniques will undoubtedly contribute to the development of more durable and efficient TBCs.In conclusion, thermal barrier coatings play a crucial role in protecting turbine blades in aircraft engines. Ongoing research efforts are focused on developing new TBC materials and advanced manufacturing techniques to enhance their performance and reliability. Overcoming challenges such as high-temperature corrosion and delamination will ensure continued progress in the aviation industry, leading to higher efficiency, reliability, and safety of aircraft engines.。
第52卷第11期表面技术2023年11月SURFACE TECHNOLOGY·139·航空发动机涡轮叶片热障涂层研究现状贾宜委，王鹤峰*，王宇迪，赵帅，昂康（太原理工大学 机械与运载工程学院，太原 030024）摘要：热障涂层是一种可以有效保障航空发动机涡轮叶片正常工作，同时显著提高其工作效率和服役时间的表面防护技术。
热障涂层的性能在很大程度上影响叶片的承温和抗腐蚀能力，进而间接影响航空发动机的服役性能。
涂层性能主要受其结构和材料2个方面的影响。
介绍了涂层结构的优缺点和研究进展，当前常见的结构形式有双层结构、多层结构和梯度结构；介绍了粘结层材料的研究进展；对陶瓷层材料的研究进展进行了详述，如YSZ的掺杂改性、A2B2O7型化合物、钙钛矿结构材料以及近年来兴起的几种高熵陶瓷材料，其中高熵陶瓷材料包括：高熵稀土钽酸盐、铝酸盐、锆/铪酸盐、磷酸盐、硅酸盐以及高熵稀土氧化物，分别从热导率、热膨胀系数、断裂韧性、热循环寿命和抗腐蚀能力等方面对其进行介绍；概述了热障涂层常见的几种失效形式如：TGO失效、CMAS腐蚀以及高温烧结，并且对其发生机理进行简要的介绍；展望了热障涂层未来的发展趋势和方向。
关键词：航空发动机；热障涂层；涂层结构；涂层材料；涂层失效形式中图分类号：TG174 文献标识码：A 文章编号：1001-3660(2023)11-0139-16DOI：10.16490/ki.issn.1001-3660.2023.11.011Research Status on Thermal Barrier Coating ofAircraft Engine Turbine BladeJIA Yi-wei, WANG He-feng*, WANG Yu-di, ZHAO Shuai, ANG Kang(College of Mechanical and vehicle Engineering, Taiyuan University of Technology, Taiyuan 030024, China)ABSTRACT: With the continuous development of the aviation industry, people are putting forward higher requirements for the performance of aircraft engines. Thermal barrier coating is a surface protection technology and depositing it on the engine turbine blade surface can significantly isolate high temperature and reduce thermal shock and thermal corrosion impact, to ensure the normal operation of aircraft engine turbine blade in harsh and complex environment, and can also significantly improve engine efficiency and service time. The performance of the thermal barrier coating largely affects the bearing and corrosion resistance of the blade, which in turn has an impact on the service capabilities of the aircraft engine. The performance of the coatings is mainly affected by their structure and material system. Firstly, several structural systems of thermal barrier coatings are briefly described in terms of their advantages, disadvantages and research advances. Currently common structural收稿日期：2022-08-13；修订日期：2023-03-01Received：2022-08-13；Revised：2023-03-01基金项目：山西省回国留学人员科研项目“动态压剪条件下南极固定冰屈服行为的研究”（2020-030）；中国—白俄罗斯电磁环境效应“一带一路”联合实验室（ZBKF2022031101）Fund：Research Project of Returned Overseas Students in Shanxi Province, "Study of Antarctic Fixed Ice Yielding Behavior under Dynamic Compressive Shear" (2020-030); China-Belarus Electromagnetic Environmental Effects "One Belt, One Road" Joint Laboratory (ZBKF2022031101)引文格式：贾宜委, 王鹤峰, 王宇迪, 等. 航空发动机涡轮叶片热障涂层研究现状[J]. 表面技术, 2023, 52(11): 139-154.JIA Yi-wei, WANG He-feng, WANG Yu-di, et al. Research Status on Thermal Barrier Coating of Aircraft Engine Turbine Blade[J]. Surface Technology, 2023, 52(11): 139-154.*通信作者（Corresponding author）·140·表面技术 2023年11月forms include: double-layer structures, multi-layer structures and gradient structures. The classical double-layer structure is still most widely used. The preparation process of multi-layer and gradient structures is more complex and both multi-layer and dual ceramic layer structures are prone to interfacial bonding problems in use, which limits their widespread application. Secondly, the current research status of binder layer materials for thermal barrier coatings is summarized. The current research on MCrAlY alloy and NiAl alloy mainly focuses on the modification of doping elements and MCrAlY alloy still needs to be improved in terms of interfacial bonding and high temperature oxidation resistance, while the advantage of NiAl alloy mainly lies in its creep resistance and oxidation resistance, which can be used as a more ideal binder layer material after modification. At the same time, the research progress of several ceramic layer materials is introduced, such as the doping modification of YSZ, A2B2O7-type compounds, chalcogenide structural materials and several high-entropy ceramic materials that have emerged in recent years. The high-entropy ceramic materials mainly include: high-entropy rare-earth tantalates, high-entropy rare-earth aluminates, high-entropy rare-earth zirconates/hafniumates, high-entropy rare-earth phosphates, high-entropy rare-earth silicates and high-entropy rare-earth oxides, in terms of thermophysical attributes such as thermal cycle life and CTE. Currently, among the doping modifications of YSZ, multi-oxide doping provides more comprehensive performance enhancement. Doping modifications of A2B2O7-type compounds have also yielded good results, but the strength and fracture toughness of the materials need further improvement. Among the high-entropy ceramic materials, high-entropy rare-earth zirconates and high-entropy rare-earth oxides are highly promising materials for ceramic layers. In order to meet the increasing requirements for engine performance, the improvement of the performance of thermal barrier coatings still needs to be continuously explored.Common forms of failure of thermal barrier coatings, such as TGO failure, CMAS corrosion, salt spray corrosion and high temperature sintering, are reviewed and the mechanisms by which they occur are briefly described. Finally, future trends and directions for thermal barrier coatings are presented. In future research, attention should be paid to improving the mechanical properties of coatings, as well as to investigating the mechanisms behind changes in coating performance, and to achieving more accurate predictions of coating life based on current research.KEY WORDS: aircraft engines; thermal barrier coatings; coating structures; coating materials; coating failure forms随着我国航空工业的不断进步，人们对飞行器服役性能等方面的要求在逐渐提高。
航空发动机涡轮叶片热障涂层研究现状【1】航空发动机涡轮叶片热障涂层研究现状【2】概述航空发动机是现代航空运输的核心组件，而涡轮叶片则是发动机中最重要的零部件之一。
涡轮叶片承受着高温高压的工作环境，需要具备优异的耐热性和耐腐蚀性能。
为了提高涡轮叶片的寿命和性能，热障涂层技术应运而生。
本文将对航空发动机涡轮叶片热障涂层的研究现状进行探讨。
【3】热障涂层的作用热障涂层技术是通过在涡轮叶片表面涂覆一层耐高温材料，形成热障层，以减少叶片表面的工作温度，提高叶片的耐热性能和抗氧化能力。
热障涂层能够有效减少涡轮叶片的热应力和热疲劳损伤，延长叶片的使用寿命，并提高发动机的工作效率和可靠性。
【4】热障涂层研究的发展历程热障涂层技术在航空领域的发展可以追溯到上世纪50年代，最初采用的是金属涂层。
然而，金属涂层存在着氧化、粘结力差等问题，限制了其应用。
随着陶瓷涂层材料的研究和发展，陶瓷涂层逐渐取代金属涂层成为主流。
目前，热障涂层的研究重点主要集中在材料性能的优化、工艺改进以及涂层与基底材料之间的耦合问题等方面。
【5】热障涂层材料的选择航空发动机涡轮叶片的热障涂层材料需要具备优异的耐高温性能、热膨胀系数匹配性和抗氧化能力。
目前常用的涂层材料主要有氧化铝、氧化锆和复合材料等。
不同的涂层材料具有各自的特点和优势，在应用中需要根据具体的工作环境和性能要求来选择合适的材料。
【6】研究热障涂层的关键技术热障涂层的研究涉及到材料制备、涂层工艺、热处理和性能评价等多个方面。
其中，材料制备的关键技术包括热喷涂和物理气相沉积等方法，涂层工艺的关键技术包括预处理、喷涂参数控制和后处理等。
涂层与基底材料之间的耦合问题也是热障涂层研究中的一个重要方向。
【7】热障涂层的性能评价热障涂层的性能评价主要包括热稳定性、热膨胀性、抗氧化性和机械性能等指标。
常用的测试方法有热循环试验、热膨胀系数测试、高温氧化试验和机械性能测试等。
通过对涂层性能的评价，可以为进一步改进和优化涂层设计提供参考和依据。
- 18 -高 新 技 术０ 前言当前，我国的航空产业高速发展，对于各种大型、新型飞机的需求不断增加。
高推重比航空发动机具有较大的推重比、良好的燃油利用性成为现今航空发动机产业重要的发展方向，为提高航空发动机的推重比提高航空发动机涡轮叶片的承温能力以使得温度更高的压缩空气能够进入到航空发动机中是航空发动机推重比提高的重要方式之一。
通过热障涂层应用将能够使得航空发动机涡轮叶片具有更高的承温能力。
１ 热障涂层简述热障涂层指的是通过使用陶瓷等材料在物体表面通过喷涂等的工艺方式使其沉积在高温合金或是耐高温金属表面，通过陶瓷等耐高温材料所形成的热障涂层来隔离外部热量，降低基底的温度，据研究表明，通过应用热障涂层将能够有效提高被涂覆物体约60%的热效率。
热障涂层技术实施关键是要通过喷涂等技术将陶瓷等耐热材料以涂层形式与基体进行复合，从而使得基体具有耐高温、耐腐蚀、耐磨损性能。
热障涂层技术的发展和应用关键是要做好耐高温材料等的研究和耐高温材料喷涂和涂层的沉积用以在高温合金基体表面形成隔热障层。
热障涂层是一种表面涂覆技术，其在零部件表面所喷涂材料属于具有低导热系数的材料，在工作的过程中利用材料低热传导特性在材料内外表面形成降温，用以完成对于喷涂零部件的热屏障保护。
一般来说热障涂层所使用材料主要为陶瓷类材料，由陶瓷面层和金属黏结层沟通构成零部件表面陶瓷热障涂层。
热障涂层技术发展至今经过了多次演变，且制备设备也在不断地更新用以满足越来越高的性能指标要求。
总体来说现今应用较多也较为广泛的热障涂层制备法主要有等离子喷涂法和电子束物理气相沉积法。
等离子喷涂法具有喷涂速度快、生产效率高以及可以对多种类型和规格的零部件进行喷涂加工。
但是等离子喷涂法也存在着一定的不足，其对于复杂零部件表面的热障涂层喷涂无法取得良好的喷涂效果，且在喷涂作业中对于热障涂层喷涂的厚度和均匀度也无法进行较为良好的控制，从而导致等离子喷涂法在完成零部件表面的喷涂作业后容易出现厚度不均、表面粗糙等的缺陷。
涂层技术在航空发动机中的应用(一)涂层技术在航空发动机中的应用1. 提高发动机效率•热障涂层（TBC）热障涂层是一种高温耐受能力极强的陶瓷涂层，在航空发动机中有广泛应用。
它可以有效降低高温燃烧室和涡轮内部的表面温度，减少热量传递到其他部件，提高燃烧效率和涡轮的使用寿命。
热障涂层采用涂敷的方式施加在发动机部件表面，形成一层隔热层，同时具备优异的耐热性、耐腐蚀性和耐磨性。
•摩擦涂层摩擦涂层是一种能够减少摩擦阻力、降低能耗和延长机械部件寿命的涂层技术。
在航空发动机中，喷涂摩擦涂层可以应用于涡轮叶片表面以减少摩擦热造成的能量损耗，提高发动机效率。
该涂层通常由涂料和固化剂组成，喷涂后会形成一层耐磨、耐热的涂层，提供涡轮叶片所需的低摩擦系数。
2. 保护发动机结构•防腐蚀涂层发动机作为飞机的核心部件，其表面容易受到腐蚀的影响。
防腐蚀涂层能够降低发动机金属部件受到酸性气体、高温、湿度等因素的腐蚀程度，提高其耐久性。
航空发动机中使用的防腐蚀涂层通常采用环氧树脂和特殊添加剂，能够有效隔离金属与外界环境，降低腐蚀速度，同时具备耐温性能。
•降噪涂层航空发动机产生的噪音是对航空乘客和地面居民造成的主要干扰。
降噪涂层是一种能够减少发动机噪音输出的技术。
该涂层通常由吸声材料和表面粗糙度调整剂构成，能够通过吸收噪音和改变噪音传播路径来降低发动机产生的噪音水平。
降噪涂层的应用可以有效改善乘客舒适度，减少航空噪声对环境的影响。
3. 增强结构强度•硬质涂层硬质涂层是一种附着在金属表面的高硬度涂层，可以提供结构件的抗磨损和抗腐蚀能力。
在航空发动机中，硬质涂层通常应用于涡轮轴承、气门、活塞等部件表面，能够减少零部件间的摩擦和磨损，提高结构件的使用寿命。
常见的硬质涂层材料包括碳化硅、氮化硼等。
•纳米涂层纳米涂层是一种厚度在纳米级别的超薄涂层，它能够提供出色的防腐蚀和防磨损性能。
航空发动机中的纳米涂层可应用于活塞环、气缸内壁等部件表面，能够减少部件摩擦和磨损，提高结构件的使用寿命。
航空发动机涡轮叶片热障涂层研究现状一、引言航空发动机是现代航空器的重要组成部分，其性能直接影响到飞机的安全和经济性。
涡轮叶片作为航空发动机的重要组件之一，承受着高温和高速气流的冲击，对其表面进行热障涂层的研究成为了发展的热点之一。
本文将综述航空发动机涡轮叶片热障涂层的研究现状，并对未来的研究方向进行展望。
二、背景在航空发动机中，高温气流是涡轮叶片面临的主要问题之一。
高温气流的冲击会导致涡轮叶片的热膨胀、氧化和烧蚀等问题，进而降低了发动机的性能和寿命。
为了解决这一问题，研究人员提出了热障涂层的概念。
三、热障涂层的种类热障涂层可以分为传统热障涂层和新型热障涂层两大类。
1. 传统热障涂层传统热障涂层主要包括YSZ (Yttria Stabilized Zirconia) 和 GCO (Gadolinium Cerium Oxide) 等。
YSZ涂层被广泛应用于航空发动机中，具有优异的热障效果和氧化屏障性能。
GCO涂层相比于YSZ涂层，具有更好的机械和热损伤修复能力，但研究相对较少。
2. 新型热障涂层新型热障涂层主要包括二氧化铝涂层、钨合金涂层等。
经过改良的二氧化铝涂层具有更好的耐腐蚀性能和较低的热导率，但是其热障效果相对较差。
钨合金涂层则具有更好的高温性能和耐烧蚀能力，但是涂层的结构和制备工艺仍面临挑战。
四、热障涂层的制备工艺热障涂层的制备工艺对涂层性能的影响至关重要。
目前，常见的热障涂层制备工艺包括物理气相沉积（Physical Vapor Deposition，PVD）、化学气相沉积（Chemical Vapor Deposition，CVD）和高速火焰喷涂（High VelocityOxygen/Fuel，HVOF）等。
1. PVDPVD技术通过物理手段将材料从固态直接转变为气态，然后沉积到基底上。
PVD制备的热障涂层具有致密的结构、低孔隙率和较高的结合强度，但是制备成本较高。
2. CVDCVD技术是利用化学反应将气态前驱体沉积在基底上，形成热障涂层。
