超音速火焰喷涂MCrAlY粘结层对热障涂层热震性能的影响

分别采用超音速火焰喷涂技术(HVOF)和等离子喷涂技术(APS)在高温合金GH99上制备MCrAIY粘结层(BC),对比研究了HVOF和APS喷涂BC对热障涂层(TBC)热震性能的影响.结果表明:APS喷涂BC界面不平整,起伏较大,而HVOF喷涂BC界面较为平整.经200次热循环后,APS喷涂TBC部分陶瓷层(TC)出现剥落,而HVOF喷涂TBC仅出现细小的微裂纹,生成的热生长氧化物(TGO)比较厚.APS喷涂TBC经过350次热循环后,涂层出现大面积剥离现象.而HVOF热障涂层直到热震430次后,才出现涂层剥落现象.拉曼光谱(RFS)残余应力分析表明,HVOF热障涂层残余应力随热循环次数的增加而增大,热震350次后APS热障涂层残余应力为650MPa,而HVOF热障涂层热震400次后其应力值仅为571 MPa.可知,HVOF显著地提高了TBC的热震性能.     

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.     

基于内聚力单元与XFEM的热障涂层失效分析

为了更好的理解热障涂层的失效机理,文中运用ABAQUS有限元软件来分析热障涂层的失效情况,使用内聚力单元和扩展有限元（XFEM）两种方法研究热障涂层TGO界面开裂与陶瓷涂层（TC）和氧化层（TGO）内随机裂纹的萌生与扩展,研究竖直裂纹与水平裂纹的关系.结果表明,热障涂层TGO界面的开裂首先出现在TGO/TBC波谷处.陶瓷涂层和氧化层内随机裂纹的萌生同样发生在TGO/TBC波谷处.竖直裂纹的存在可以抑制水平裂纹的萌生与扩展,且其在TGO/TBC波谷处的扩展长度比在TGO/TBC波峰处的扩展长度更长,说明TGO/TBC波谷区域是个危险区域,在此区域容易引发裂纹的萌生与扩展.     

等离子喷涂梯度热障涂层的抗热震性能

对比研究了等离子喷涂梯度热障涂层与双层热障涂层,试验中梯度热障涂层选用不同比例的NiCoCrAlY与ZrO₂-8%Y₂O₃复合粉末作为梯度过渡层材料,并对两种结构的热障涂层进行了抗热震性能试验。抗热震试验结果表明,梯度热障涂层的抗热震寿命明显高于双层热障涂层的抗热震寿命。     

不同结构等离子喷涂热障涂层的性能研究

通过等离子喷涂,制备了常规层状结构、垂直裂纹结构的氧化钇部分稳定氧化锆(YSZ)和铈酸镧(LCO)热障涂层,分析了涂层的微观形貌及性能。结果表明:对于YSZ涂层,垂直裂纹结构的结合强度是层状结构的1.8倍;LCO涂层的微观结构对喷涂工艺比较敏感,适当降低喷涂功率有助于提高扁平化粒子间的结合,缓解涂层中横向裂纹的产生,促进垂直裂纹形成;与层状结构的LCO/YSZ双层涂层相比,垂直裂纹结构的LCO/YSZ双层涂层的结合强度和抗热震性能未明显提高。     

等离子喷涂纳米热障涂层热震性能

采用等离子喷涂工艺制备常规和纳米结构ZrO2-7%Y2O3热障涂层,比较两种涂层在850℃下的热震性能,并探讨其热震失效机理。结果表明,不管是首次出现宏观裂纹(局部剥落)还是达到热震失效,纳米结构热障涂层的热震次数都明显高于相应的常规涂层。相对于常规涂层,纳米结构涂层有较好的抗热震性能。等离子喷涂常规热障涂层的热震失效形式为大面积整体剥落,而纳米结构热障涂层热震失效形式为边角局部剥落。     

有关因素对热障涂层抗热震性能的影响

等离子喷涂热障涂层，对研制新型航空发动机具有重要意义。喷涂热障除层的关键，是如何提高涂层的抗热震性能。本文介绍了涂层结构、基体温度、涂层气孔率、不同粘结底层等因素，对涂层抗热震性能的影响。并简要介绍了涂层的抗高温氧化、抗热盐腐蚀性能及涂层的隔热效果。     

激光表面重熔对ZrO_2-8wt%Y_2O_3热障涂层组织与抗热震性能的影响

采用等离子喷涂设备在H13热作模具钢表面制备氧化钇部分稳定的氧化锆(ZrO2-8 wt%Y2O3)热障涂层,并用CO2横流激光器对热障涂层进行表面重熔处理,并采用X射线衍射仪(XRD)、扫描电子显微镜(SEM)、热震试验等手段研究激光重熔前后热障涂层的微观结构及其抗热震性能的变化。结果表明,重熔前后涂层均由四方结构钇锆氧化物和立方相的氧化锆组成,重熔后涂层结晶度增加,晶粒有长大现象。激光重熔后涂层产生明显分层,表层组织孔隙和裂纹明显减少,裂纹呈网状且沿晶界分布,重熔涂层内部仍保持等离子喷涂典型结构。激光重熔后涂层孔隙率降低了67%,涂层的抗热震性能也显著提高。     

等离子喷涂ZrO2热障涂层的抗热震性能研究

采用等离子喷涂方法在304不锈钢表面喷涂NiCoCrAIY2O3+(ZrO2+7%Y2O3)陶瓷热障涂层,模拟航空发动机涡轮叶片工作环境,研究涂层在加热和空气冷却条件下的抗热震性能.结果表明:喷涂后的涂层内部产生大量微观裂纹,随着热震次数的增加,陶瓷层内部的纵向微观裂纹通过大孔隙的连通方式逐渐在涂层内部扩展.ZrO2陶瓷喷涂后涂层主要以四方相和部分立方相组成,当涂层在热震40次时,陶瓷中的部分四方相向单斜相转变,并伴随着体积的变化,易在涂层中形成新的裂纹并加快原有裂纹的扩展.     

纳米SiCw晶须/ZrO2复合热障涂层的制备与性能

运用微弧等离子喷涂制备了碳化硅晶须(SiCw)掺杂部分稳定ZrO2(YPSZ)复合热障涂层(CTBCs),对涂层进行了显微组织观察、EDS分析、XRD分析和抗热震性能试验.喷涂过程中,复合粉末里的部分SiCw在高温下分解产生的气体夹杂在熔融的颗粒内形成气孔,另一部分沉积在涂层中起到降低热应力和钉扎、桥联作用.结果表明,随着粉末中SiCw含量的增加,复合陶瓷层的孔隙率呈增大趋势;复合涂层的抗热震性能优于单纯氧化锆涂层,SiCw含量为20%的复合涂层的抗热震性能最优.     

铂铝涂层高温氧化的影响因素研究

研究比较沉积热障涂层和无热障涂层的镍基高温合金铂改性铝化物涂层在900,1000和1100℃空气中高温氧化生成的氧化铝层表面形态和断面结构。发现低铂含量涂层氧化初期热生长层(TGO)表面有放射状裂纹形成和长大,造成氧化铝的局部脱落,并在TGO与铂铝涂层界面形成空洞。涂层900℃循环氧化300h后TGO内部均形成空洞。而在1100℃氧化时,TBC陶瓷层的存在改变了两种铂铝涂层TGO的内应力变化趋势,升高温度使TGO厚度迅速增大,涂层寿命迅速下降。     

燃气轮机起动过程热障涂层的应力数值分析

考虑了热障涂层在服役过程中发生的陶瓷层烧结和氧化层增厚作用,对燃气轮机起动过程中涂层热应力进行了数值研究。通过瞬态传热模拟获得起动过程温度场,运用顺序热应力耦合求解起动过程热应力。其中起动初始的陶瓷层烧结和氧化层增厚状态,通过预先模拟高温烧结和氧化层增厚过程来获得,并通过ABAQUS子程序分别实现。结果表明,起动过程中涂层瞬态温度场的变化主要受燃气温度的变化规律所影响。起动过程未见热应力激增现象,陶瓷层烧结和氧化层增厚主要对起动初期,尤其是起动过程的初始残余应力有重要影响,对起动过程中后期的影响可忽略。烧结对陶瓷层和粘结层的热应力均有较大影响,而氧化层增厚对陶瓷层热应力的影响很小,但其对粘结层热应力的影响比烧结更大。     

预氧化处理对热障涂层热冲击性能及残余应力的影响

采用等离子喷涂工艺在镍基高温合金基体上制备了热障涂层(底层为MCrAlY,面层为ZrO2+ 8％ Y2O3),通过控制高真空烧结炉的氧分压对涂层进行预氧化处理,分析了预氧化处理对热障涂层热冲击性能和涂层应力状态的影响.结果表明,预氧化处理提高了粘接层的致密度,涂层组织变得均质化,降低了粘结层由于凸起尖角产生复杂应力的概率;有效干预热生长氧化物(TGO)的生长过程,降低了TGO的生长速度;热障涂层残余应力随热冲击次数的增加而增大,但经过预氧化处理的涂层应力增长幅度较缓慢,经过400次热冲击后的残余应力为492.5 MPa,未经过预氧化处理涂层热冲击350次后应力值为650.1 MPa.     

热障涂层高温抗氧化性能研究的现状与发展

从热障涂层(TBCs)的制备方式,长期高温氧化环境中服役的失效机制及高温抗热氧化性能的改善等方面,综述了近年来热障涂层(TBCs)中存在的热氧化生长(TGO)导致涂层失效及改善高温抗氧化性能研究的热点问题,并提出了作者的一些观点.     

Delamination resistance of thermal barrier coatings containing embedded ductile layers

Micromechanical models are developed to explore the effect of embedded metal layers upon thermal cycling delamination failure of thermal barrier coatings (TBCs) driven by thickening of a thermally grown oxide (TGO). The effects of reductions in the steady-state (i.e. maximum) energy release rate (ERR) controlling debonding from large interface flaws and decreases in the thickening kinetics of TGO are investigated. The models are used to quantify the dependence of the ERR and delamination lifetime upon the geometry and constitutive properties of metal/TBC/TGO multilayers. Combinations of multilayer properties are identified which maximize the increase in delamination lifetime. It is found that even in the absence of TGO growth rate effects, the delamination lifetime of TBC systems with weak TGO/bond coat interfaces can be more than doubled by replacing 10–20% of the ceramic TBC layer with a metal whose ambient temperature yield stress is in the ～100–200 MPa range.     

On the role of imperfections in the failure of a thermal barrier coating made by electron beam deposition

An impression test has been used to explore the remnant toughness and the delamination characteristics of thermal barrier coatings (TBCs) after extended thermal exposure. The delamination trajectory is found to change as the thermally grown oxide (TGO) thickens. At small thicknesses, delamination occurs predominantly within the TGO and TBC. With a thicker TGO, developed after 100 h exposure at 1100°C, the delamination extends predominantly along the TGO/bond coat interface, but with small oxide domains remaining embedded in the bond coat. The changes in the interface adhesion and the mechanics responsible for this transition are addressed, along with a discussion of the role of morphological imperfections in the TGO in failure nucleation. A method for determining the effective in-plane modulus of the TBC from the curvature of decohered TGO/TBC bilayers is also presented.     

Improved Thermal Cycling Durability of Thermal Barrier Coatings Manufactured by PS-PVD

The plasma spray-physical vapor deposition (PS-PVD) process is a promising method to manufacture thermal barrier coatings (TBCs). It fills the gap between traditional thermal spray processes and electron beam physical vapor deposition (EB-PVD). The durability of PS-PVD manufactured columnar TBCs is strongly influenced by the compatibility of the metallic bondcoat (BC) and the ceramic TBC. Earlier investigations have shown that a smooth BC surface is beneficial for the durability during thermal cycling. Further improvements of the bonding between BC and TBC could be achieved by optimizing the formation of the thermally grown oxide (TGO) layer. In the present study, the parameters of pre-heating and deposition of the first coating layer were investigated in order to adjust the growth of the TGO. Finally, the durability of the PS-PVD coatings was improved while the main advantage of PS-PVD, i.e., much higher deposition rate in comparison to EB-PVD, could be maintained. For such coatings, improved thermal cycling lifetimes more than two times higher than conventionally sprayed TBCs, were measured in burner rigs at ~1250 °C/1050 °C surface/substrate exposure temperatures.     

高温拉压环境下DZ125高温合金的热障涂层失效

采用电子束物理气相沉积法（EB-PVD）在定向凝固Ni基高温合金DZ125基体上制备了NiCoCrAlY粘结层和YSZ陶瓷层，研究了高温拉压环境下热障涂层的失效模式，并对其进行了有限元分析。实验结果表明，热障涂层的失效与仅受热载荷作用下的有很大不同，仅有热载荷作用下的热障涂层裂纹多萌生于热氧化层（TGO）内部，进而扩展引起热障涂层的失效。而高温拉压试验后热障涂层体系存在两种裂纹，分别萌生于TGO／粘结层界面和粘结层／扩散层界面附近。有限元模拟结果显示TGO／陶瓷层和TGO／粘结层处存在应力状态的转变和应力值的突变，径向应力的突变导致了界面分离现象的产生，而轴向应力的突变加速了垂直于界面裂纹的扩展，并导致了试样的最终断裂。     

Thermal stability and mechanical properties of thick thermal barrier coatings with vertical type cracks

The thermal stability and failure mechanism of thick thermal barrier coatings (TBCs) with and without vertical type cracks were investigated through the cyclic thermal exposure and thermal-shock tests. The TBC systems with thickness of about 2000 µm in the top coat were prepared by an air plasma spray (APS) on the bond coat of about 150 µm in thickness prepared by APS. The adhesive strength values of the as-prepared TBCs with and without vertical type cracks were determined to be 24.7 and 11.0 MPa, respectively, indicating the better interface stability in the TBC with vertical type cracks. The TBC with vertical type cracks shows a better thermal durability than that without vertical type cracks in the thermal cyclic exposure and thermal-shock tests. The hardness values of the as-prepared TBCs with and without vertical type cracks were found to be 6.6 and 5.3 GPa, respectively, which were increased to 9.5 and 5.5 GPa, respectively, after the cyclic thermal exposure tests. These results indicate that the vertical type cracks developed in the top coat are important in improving the lifetime performance of thick TBC in high temperature environment.