Vasile Bogdan Stefan, Birca Alexandra Catalina, Surdu Vasile Adrian, Neacsu Ionela Andreea, Nicoară Adrian Ionut
National Research Center for Micro and Nanomaterials, University Politehnica of Bucharest, 010164 Bucharest, Romania.
Department of Science and Engineering of Oxide Materials and nanomaterials, Faculty of Applied Chemistry and Materials Science, University Politehnica of Bucharest, 010164 Bucharest, Romania.
Nanomaterials (Basel). 2020 Feb 20;10(2):370. doi: 10.3390/nano10020370.
This paper is focused on the basic properties of ceramic composite materials used as thermal barrier coatings in the aerospace industry like SiC, ZrC, ZrB etc., and summarizes some principal properties for thermal barrier coatings. Although the aerospace industry is mainly based on metallic materials, a more attractive approach is represented by ceramic materials that are often more resistant to corrosion, oxidation and wear having at the same time suitable thermal properties. It is known that the space environment presents extreme conditions that challenge aerospace scientists, but simultaneously, presents opportunities to produce materials that behave almost ideally in this environment. Used even today, metal-matrix composites (MMCs) have been developed since the beginning of the space era due to their high specific stiffness and low thermal expansion coefficient [1]. These types of composites possess properties such as high-temperature resistance and high strength, and those potential benefits led to the use of MMCs for supreme space system requirements in the late 1980s. Electron beam physical vapor deposition (EB-PVD) is the technology that helps to obtain the composite materials that ultimately have optimal properties for the space environment, and ceramics that broadly meet the requirements for the space industry can be silicon carbide that has been developed as a standard material very quickly, possessing many advantages. One of the most promising ceramics for ultrahigh temperature applications could be zirconium carbide (ZrC) because of its remarkable properties and the competence to form unwilling oxide scales at high temperatures, but at the same time it is known that no material can have all the ideal properties []. Another promising material in coating for components used for ultra-high temperature applications as thermal protection systems is zirconium diboride (ZrB), due to its high melting point, high thermal conductivities, and relatively low density [3]. Some composite ceramic materials like carbon-carbon fiber reinforced SiC, SiC-SiC, ZrC-SiC, ZrB-SiC, etc., possessing low thermal conductivities have been used as thermal barrier coating (TBC) materials to increase turbine inlet temperatures since the 1960s. With increasing engine efficiency, they can reduce metal surface temperatures and prolong the lifetime of the hot sections of aero-engines and land-based turbines.
本文聚焦于航空航天工业中用作热障涂层的陶瓷复合材料（如碳化硅、碳化锆、硼化锆等）的基本特性，并总结了热障涂层的一些主要特性。尽管航空航天工业主要基于金属材料，但陶瓷材料代表了一种更具吸引力的方法，这些陶瓷材料通常更耐腐蚀、抗氧化和耐磨，同时具有合适的热性能。众所周知，太空环境呈现出极端条件，这对航空航天科学家构成了挑战，但同时也为生产在这种环境中几乎表现理想的材料提供了机会。自太空时代开始以来就已开发出金属基复合材料（MMC），即使在今天仍被使用，因为它们具有高比刚度和低热膨胀系数[1]。这类复合材料具有耐高温和高强度等特性，这些潜在优势促使在20世纪80年代末将MMC用于最高级别的太空系统要求。电子束物理气相沉积（EB-PVD）是一种有助于获得最终对太空环境具有最佳性能的复合材料的技术，而能广泛满足航天工业要求的陶瓷可以是碳化硅，它很快就被开发为标准材料，具有许多优点。碳化锆（ZrC）因其卓越的性能以及在高温下形成不希望有的氧化皮的能力，可能是超高温应用中最有前途的陶瓷之一，但同时也知道没有一种材料能具备所有理想性能[]。作为热防护系统用于超高温应用部件涂层的另一种有前途的材料是二硼化锆（ZrB），因为它具有高熔点、高导热率和相对较低的密度[3]。自20世纪60年代以来，一些具有低热导率的复合陶瓷材料，如碳 - 碳纤维增强碳化硅、碳化硅 - 碳化硅、碳化锆 - 碳化硅、硼化锆 - 碳化硅等，已被用作热障涂层（TBC）材料以提高涡轮进口温度。随着发动机效率的提高，它们可以降低金属表面温度并延长航空发动机和陆基涡轮机热段的寿命。
