纳米锆酸镧团聚体特性及等离子涂层性能的研究

采用喷雾干燥法制备了纳米锆酸镧团聚体粉末,采用大气等离子喷涂制备了纳米锆酸镧涂层,并用扫描电镜和XRD对涂层的微观组织结构进行了研究。结果表明:喷雾干燥法制备的纳米La_2Zr_2O_7团聚体,粒度接近正态分布,流动性好,松装密度较大。采用大气等离子喷涂制备纳米锆酸镧涂层中存在一定量的孔隙和微裂纹,利于隔热。纳米锆酸镧热障涂层在1473K烧蚀8h后的相结构稳定。     

梯度热障涂层热冲击性能研究

采用等离子喷涂的方法,分别获得了２ｍｍ ＺｒＯ２－ＮｉＣｒＡｌ和ＺｒＯ２－Ｎｉ／Ａｌ系梯度热障涂层。热冲击实验结果表明,两种涂层具有不同的失效机理。ＺｒＯ２－ＮｉＣｒＡｌ系的失效是由于基于基体氧化引起的涂层整体脱落;而ＺｒＯ２－Ｎｉ／Ａｌ系的失效是支径向裂纹扩展到Ｎｉ／Ａｌ底层氧化共同作用的结果。     

激光重熔处理工艺对等离子喷涂热障涂层组织的影响

研究了激光不同工艺参数对等离子喷涂ＺｒＯ２热障涂层组织结构的影响,结果表明：随着激光输出功率的增大,重熔组织由单一柱晶结构变为等轴晶＋柱晶双层结构。ＺｒＯ２层最高显微硬度也随之增大,这与等轴晶的存在有关。对两种不同晶体相结构进行ＸＲＤ分析表明：柱晶结构表现出一定的择优取向。     

等离子喷涂-物理气相沉积防护涂层及其失效机理研究进展

防护涂层在航空发动机和燃气涡轮发动机免受水氧腐蚀和盐雾侵蚀、耐高温、抗冲刷和服役寿命方面发挥着重要的作用。等离子喷涂-物理气相沉积(PS-PVD)技术以其大功率、喷射范围广、能够使粉末原料以气相甚至离子化和非视线沉积特性等特点被广泛应用在热/环境障涂层制备领域,形成的涂层具有沉积效率高、孔隙率较高、热导率低、应变容限高等特点。首先,对PS-PVD热障涂层的表面形貌、柱状晶特点和等离子射流特性进行了探讨。然后,讨论了PS-PVD YSZ热障涂层表面镀铝改性对涂层抗CMAS侵蚀、减少孔隙和裂纹、TGO的生成和提高热循环寿命方面的重要作用,结果表明表面镀铝能显著减少涂层表面孔隙、凹坑、微裂纹和熔融盐对于热障涂层的不利影响。其次,简要概述了近年来SiC_f/SiC CMCs代替镍基高温合金在航空发动机基体上抗高温高压和快速失效方面发挥的重要作用。SiC_f/SiC CMCs与T/EBCs的结合,有效延长了航空发动机的使用寿命,是我国航空事业的又一次重大突破。此外,重点介绍了PS-PVD非视线沉积特性和涂层阴影效应在涂层沉积方面这一特色,总结了TGO、残余...     

纳米Al2O3粉体材料激光烧结成型基础试验研究

基于激光烧结快速成型技术 ,利用CO2 激光对纳米Al2 O3 粉体材料进行激光烧结成型的试验并用扫描电镜(SEM)和X射线衍射仪等对烧结样品进行分析。结果表明 ,在适当的工艺参数下 ,对Al2 O3 粉体的激光烧结可获得一定形状的、致密的陶瓷块体 ,块体内部晶粒保持在纳米尺度     

微弧等离子喷涂制备莫来石/金属复合热障涂层

运用微弧等离子喷涂制备了莫来石/金属复合热障涂层.研究了涂层的微观结构、结合强度、隔热性能和抗热震性能.复合涂层结构为莫来石颗粒被"包裹"在金属层片状结构中;涂层的结合强度大于30 MPa.随着涂层中莫来石含量的增加,涂层的隔热性能有所提高,随涂层表面温度的升高,涂层的隔热温度也不断提高,涂层的最高隔热温度为125℃.1 150℃的水淬热震试验表明,基体变形是导致涂层失效的重要原因之一,随着涂层中莫来石含量的增加,涂层的抗热震次数先增加后减小,粉末中莫来石含量为40%的涂层的抗热震性能最好,抗热震次数最多为72次.     

Investigating the thermal,mechanical and thermal cyclic properties of plasma-sprayed Al2O3-7YSZ/7YSZ double ceramic layer TBCs

Double ceramic layer (DCL) TBCs consisting of a top 20 wt.% Al₂O₃-7YSZ layer and a bottom 7YSZ layer were desirably designed to achieve preferable performance while the thermal, mechanical and thermal cyclic properties were comprehensively investigated. Compared to the conventional 7YSZ TBCs, the thermal insulation properties of the DCL coating were significantly improved due to the increased oxygen vacancy concentration induced by Al₂O₃ addition while the thickness of the thermally grown oxides was diminished by the decreased oxygen diffusion rate. Furthermore, the improved fracture toughness of the DCL coating also prolonged the thermal cyclic life.     

脱粘裂纹扩展诱发热障涂层陶瓷层温度场演变与烧结行为研究

目的 研究等离子喷涂热障涂层(APS-TBCs)内部脱粘裂纹尺寸对陶瓷层温度场与烧结行为的影响.方法 采用有限元模型研究不同尺寸脱粘裂纹对其上方陶瓷层温度场变化规律的影响,并通过梯度热循环试验对裂纹上方陶瓷层烧结行为进行研究,采用扫描电子显微镜(SEM)分析陶瓷层表面和断面的组织形貌,并使用图片法对裂纹上方陶瓷层不同区域的孔隙率进行分析.结果 裂纹上方陶瓷层温度变化区域的面积取决于裂纹尺寸,且最高温度始终位于裂纹中心的上方陶瓷层表面,随着裂纹宽度向两端依次递减,其对应的上方温度依次递减.在本试验条件下,随着脱粘裂纹尺寸的增加,涂层厚度方向的最高温度以线性形式增加,裂纹尺寸每增加0.5 mm,其上方陶瓷层同一位置处的温度增加约30℃,且最高温度区域随之增大.裂纹长度超过3 mm时,在脱粘裂纹热阻效应下,裂纹上方陶瓷层区域的温度升高.裂纹越长,上方陶瓷层整体温度提升越高,不仅导致陶瓷层发生相变和烧结的区域增大,还使得相变和烧结速率升高.不同梯度热循环次数下,陶瓷层表面和内部均出现了数量和长度不等的脱粘、垂直裂纹,烧结面积逐渐增大.脱粘裂纹长度为4 mm时,其最大宽度约40μm.结论 脱粘裂纹上方陶瓷层温度变化以表面最高温度处为中心向四周呈放射性递减.越靠近陶瓷层表面,层状组织信息越少,相应区域的孔隙率越小,烧结和相变程度逐渐增加,使涂层发生脱落失效的可能性进一步增加.     

Synthesis and thermophysical properties of ATa2O6 (A = Co,Ni, Mg,Ca) tantalates with robust CMAS resistance

A new family of ceramic environmental/thermal barrier coating (E/TBC) materials, that is, ATa₂O₆ (A = Co, Ni, Mg, Ca), for high-temperature applications, are investigated and reported in this study. We focus on the synthesis and features of crystal structures, and on the mechanical and high-temperature properties. ATa₂O₆ oxides have an extraordinary phase stability (up to 1300°C), and their thermal expansion coefficients (6.2–7.3 × 10⁻⁶ K⁻¹) match those of SiC fiber-enhanced SiC ceramic matrix composites (3–7 × 10⁻⁶ K⁻¹). Their low thermal conductivities (min: 1.15 W·m⁻¹·K⁻¹) root in the slow phonon spreading speed and fierce phonon-phonon scattering process, and they will provide exceptional thermal insulation. Moreover, their hardness (5.6–8.8 GPa), toughness (1.4–1.9 MPa·m^1/2), and moduli (100–210 GPa) have good comparability with current E/TBCs. We propose the 33CaO-9MgO-13AlO_1.5-45SiO₂ (CMAS) corrosion mechanisms of ATa₂O₆ ceramics, and their robust CMAS resistance relies on the phase stability of CaTa₂O₆ oxides. The excellent high-temperature properties ensure that ATa₂O₆ can be used as E/TBCs to provide thermal insulation and CMAS corrosion protection.     

Simulation of thermal barrier coating spallation induced by the initiation/growth/coalescence of internal crack and interfacial crack based on a real image model

In the furnace cycle test, the growth of oxide film leads to the propagation and coalescence of multiple cracks near the interface, which should be responsible for the spallation of thermal barrier coatings (TBCs). A TBC model with real interface morphology is created, and the near-interface large pore is retained. The purpose of this work is to clarify the mechanism of TBC spallation caused by successive initiation, propagation, and linkage of cracks near the interface during thermal cycle. The dynamic growth of thermally grown oxide (TGO) is carried out by applying a stress-free strain. The crack nucleation and arbitrary path propagation in YSZ and TGO are simulated by the extended finite element method (XFEM). The debonding along the YSZ/TGO/BC interface is evaluated using a surface-based cohesive behavior. The large-scale pore in YSZ near the interface can initiate a new crack. The ceramic crack can propagate to the YSZ/TGO interface, which will accelerate the interfacial damage and debonding. For the TGO/BC interface, the normal compressive stress and small shear stress at the valley hinder the further crack propagation. The growth of YSZ crack and the formation of through-TGO crack are the main causes of TBC delamination. The accelerated BC oxidation increases the lateral growth strain of TGO, which will promote crack propagation and coalescence. The optimization design proposed in this work can provide another option for developing TBC with high durability.