NiCoCrAlY粘结层喷涂工艺对8YSZ热障涂层抗氧化性能的影响

目的 提高热障涂层粘结层的抗高温氧化性能。方法 分别采用爆炸喷涂和等离子喷涂工艺制备了不同结构的NiCoCrAlY粘结层,之后通过等离子喷涂制备8YSZ陶瓷层,分析了两种粘结层结构的热障涂层的抗高温氧化性能。利用XRD、SEM和EDS对涂层物相、微观结构和成分进行分析,并对其与基体结合状态、抗高温氧化性能进行研究。结果 爆炸喷涂粘结层内部组织致密,缺陷较少,与基体结合处孔隙少;而等离子喷涂粘结层内部的层状特征明显,孔隙较多,表面粗糙度较低。爆炸喷涂粘结层氧化5 h后,表面生成了一层富Al2O3的致密氧化物膜;而等离子喷涂粘结层表面形成了富NiO、CoO、Cr2O3和Ni(Cr,Al)2O4的氧化物层,并出现了许多微裂纹和片层状氧化物。爆炸喷涂制备的热障涂层试样在前5 h氧化增重速率高于等离子喷涂试样,随后变平缓,而等离子喷涂试样氧化速率依然较高。爆炸喷涂热障涂层的热生长氧化物层（Thermally grown oxide, TGO）经50 h氧化后,仍呈连续状,厚度均匀,粘结层内氧化物缺陷较少。结论 爆炸喷涂粘结层组织均匀、致密,喷涂时涂层的氧化以及热处理的内氧化较少,使得足够的Al较快速地在粘结层表面形成致密的氧化铝,表面一定厚度的氧化铝层抑制了氧和其他金属原子的相向扩散反应,提高了涂层的抗高温氧化性能。     

电热爆炸喷涂和等离子喷涂联合法制备热障涂层的研究

采用电热爆炸喷涂和等离子喷涂联合制备热障涂层,以电热爆炸喷涂法在DZ125合金表面制备NiCoCrAlY粘结层,以等离子喷涂技术制备陶瓷顶层。利用扫描电镜(SEM)和X射线衍射(XRD)仪对所制备的粘结层进行分析,结果表明:电热爆炸喷涂的粘结层与基体结合良好,喷涂态的粘结层的相主要由Ni3Al组成。采用联合法制备的热障涂层,在喷涂态的陶瓷层、粘结层、基体3者结合良好,界面清晰。在高温热循环过程中,粘结层/陶瓷层界面间生成了连续、致密的Al2O3膜,阻碍粘结层的氧化。粘结层/TGO界面产生平行于界面的裂纹,是导致热障涂层失效的主要原因。     

爆炸喷涂制备NiCrAlY/NiAl/ZrO2-Y2O3体系热障涂层

为了提高热障涂层的高温抗氧化性，采用爆炸喷涂技术在M22合金上制备了Ni-25Cr-5Al—0．5Y／Ni-50Al/ZrO2—8Y2O3(质量分数，％)体系的热障涂层．喷涂态Ni-50Al(NiAl)扩散阻挡层由δ-Ni2Al3，3-NiAl和NiAl3组成．对该涂层进行1050，1100和1150℃下的等温氧化，研究了NiAl层对氧化膜生长机制的影响．结果表明，NiCrAlY／NiAl／YSZ体系的氧化增重明显小于双层结构热障涂层的，其氧化动力学在1050和1100℃下符合四次方规律，在1150℃下符合抛物线规律，NiAl层有阻碍粘结层元素向外扩散、促进以Al2O3为主的氧化膜形成的作用．     

爆炸喷涂空心球形氧化锆热障涂层的抗热冲击性能

在镍基高温合金基体DSM11上制备双层结构的热障涂层．粘结底层采用电弧离子镀技术制备的NiCoCrAlY涂层，陶瓷顶层采用爆炸喷涂技术制备的Y2O3部分稳定的ZrO2(YSZ)陶瓷涂层，粉末采用普通实心YSZ粉、空心球形YSZ粉对制备的热障涂层进行热导率测定和热冲击性能实验．结果表明：爆炸喷涂制备的空心YSZ陶瓷层涂层具有低的热导率和良好的抗热冲击性能。     

YAG/8YSZ双陶瓷热障涂层等温氧化性能研究

本文对比研究了YAG/8YSZ双陶瓷和8YSZ单陶瓷热障涂层体系的抗高温氧化性能。采用爆炸喷涂(D-GUN)在310S耐热不锈钢基体上制备粘结层(NiCoCrAlY),用大气等离子喷涂(APS)分别在粘结层试样上制备YAG/8YSZ双陶瓷和8YSZ单陶瓷热障涂层,利用SEM和XRD分析涂层氧化前后截面与表面特征,对比研究2种热障涂层体系在1100 ℃等温氧化不同时间后的氧化增重动力学、YAG陶瓷层微观结构与物相及TGO生长过程和生长动力学。结果表明,YAG陶瓷层在1100 ℃等温氧化200 h后无明显相结构转变,孔隙率稍有降低;YAG/8YSZ双陶瓷层体系较8YSZ单陶瓷层体系氧化增重速率降低1.7倍,TGO生长速率降低1.4倍,粘结层β-NiAl相消耗速度及岛状氧化物生长速度更低,表现出更好的抗高温氧化性能。     

等离子喷涂热障涂层高温风洞热震行为

采用等离子喷涂工艺制备ZrO2-8%Y2O3(质量分数,下同)陶瓷层,冷喷涂制备CoNiCrAlY粘结层,在高温燃气风洞条件下测试热障涂层的热震性能,并研究了高温氧化处理对试样热震性能的影响.结果表明,等离子喷涂热障涂层具有较好的抗热震性能,经过100次热震循环后,涂层与基体结合良好,涂层较为完整,未出现大面积的剥落;经过氧化处理后的试样抗热震性较差.     

TiAl合金等离子喷涂CoNiCrAlY+(ZrO2+Y2O3)涂层性能的研究

利用等离子喷涂法在TiAl合金基体表面依次喷涂结合紧密的过渡CoNiCrAlY涂层和(ZrO2 Y2O3)的陶瓷热障涂层，并进行高温氧化试验。用XRD、SEM检测了试样的显微组织、结构及形貌，结果表明，经等离子喷涂处理后TiAl合金表面形成陶瓷热障涂层且与基体结合紧密；过渡层的硬度有所增大，表面陶瓷层的硬度显著增高，耐磨性能提高；进行850℃和1000℃高温静态氧化试验，TiAl合金表面高温抗氧化能力也显著提高。     

等离子喷涂-物理气相沉积7YSZ热障涂层的高温氧化行为

以纳米团聚烧结的ZrO2-7%Y2O3(7YSZ)粉末为原料,采用等离子喷涂-物理气相沉积(PS-PVD)工艺及大气等离子喷涂工艺(APS)在镍基高温合金表面制备了柱状热障涂层(C-TBC)和层状热障涂层(L-TBC),并进行1 000℃的恒温氧化试验,采用X射线衍射仪、扫描电镜、电子探针、能谱分析等检测手段表征热障涂层的微观结构和高温氧化行为。结果表明:C-TBC涂层在氧化初始阶段快速生成TGO层,氧化50h后TGO层生长速率减慢,氧化动力学曲线符合五次方抛物线规律,而L-TBC涂层氧化动力学曲线符合常规二次方抛物线规律。C-TBC涂层氧化速度快于L-TBC涂层,但抗氧化剥落性能优于L-TBC涂层。     

钛合金表面等离子喷涂热障涂层性能的研究

用等离子喷涂法在钛合金（Ti6Al4V）表面制备NiCrAlY＋（ZrO2＋Y2O3）陶瓷热障涂层。用XRD、SEM检测了涂层的金相组织、结构及形貌。对喷涂前后的试样在600℃进行了高温氧化实验,给出了氧化动力学曲线。结果表明．钛合金经等离子喷涂处理后表面形成陶瓷热障涂层且与基体结合紧密,涂层的厚度约为210um。所形成的热障涂层显著地提高了钛合金的高温抗氧化性能．降低了氧化速率,致密的氧化膜对继续氧化有阻碍作用。     

涂层致密度对MCrAlY涂层氧化行为的影响

采用等离子弧喷涂工艺和超音速火焰喷涂工艺分别制备MCrAlY涂层,利用扫描电镜、X射线衍射仪等研究不同工艺条件下涂层的结构特征,并研究2种涂层在1050℃时的高温氧化行为。结果表明:超音速火焰喷涂工艺可以使MCrAlY涂层获得更高的致密度,在高温氧化过程中该涂层表面可以形成致密的Al2O3膜层,减少NiO,尖晶石类复杂氧化物的出现。同等离子弧喷涂工艺相比,超音速火焰喷涂工艺制备的MCrAlY涂层在高温氧化过程中表现出较小的增重速率和致密的氧化物结构,有利于热障涂层整体寿命的提升。     

Development of refractory silicate-yttria-stabilized zirconia dual-layer thermal barrier coatings

Development of advanced thermal barrier coatings (TBCs) is the most promising approach for increasing the efficiency and performance of gas turbine engines by enhancing the temperature capability of hot section metallic components. Spallation of the yttria-stabilized zirconia (YSZ) top coat, induced by the oxidation of the bond coat coupled with the thermal expansion mismatch strain, is considered to be the ultimate failure mode for current state-of-the-art TBCs. Enhanced oxidation resistance of TBCs can be achieved by reducing the oxygen conductance of TBCs below that of thermally grown oxide (TGO) alumina scale. One approach is incorporating an oxygen barrier having an oxygen conductance lower than that of alumina scale. Mullite, rare earth silicates, and glass ceramics have been selected as potential candidates for the oxygen barrier. This paper presents the results of cyclic oxidation studies of oxygen barrier/YSZ dual-layer TBCs.     

等离子喷涂热障涂层高温 TGO 的形成与生长研究

目的研究热障涂层(TBC)和纯粘结层(BC)在1100℃下的氧化动力学,探讨热障涂层中热生长氧化物(TGO)组织结构的演化规律。方法运用大气等离子喷涂技术(APS)制备涂层,对比分析热障涂层和纯粘结层涂层在1100℃下等温氧化2,5,10,20,50,100,200,350 h后TGO的厚度变化,并对粘结层表面和热障涂层截面分别进行XRD和SEM分析。结果热障涂层和纯粘结层在1100℃下的氧化动力学均遵循抛物线规律,其氧化速率常数分别为0.344,0.354μm/h0.5。等温氧化5 h后,TGO的主要成分为α-Al2O3;随氧化时间的增加,生成Cr2O3、尖晶石、Co O和Ni O的混合氧化物;等温氧化100 h后,Co O消失,Ni O的含量减少,Cr2O3和尖晶石氧化物的含量增加;等温氧化350 h后,TGO中出现了裂纹,但涂层仍未剥落,TGO最终由顶层多孔的混合氧化物层和底层具有柱状晶结构的α-Al2O3层组成。结论顶层陶瓷层(TC)对热障涂层氧化速率常数的影响很小。TGO中α-Al2O3首先形成并以柱状结晶的方式生长,混合氧化物在α-Al2O3上形成,TGO生长速度逐渐变缓。     

等离子喷涂Al2O3与ZrO2复合热障涂层的高温性能

采用等离子喷涂(PS)方法，在GH536高温合金基材上制备了传统的双层热障涂层(TBCs)和2种含有Al2O3与ZrO2陶瓷复合层的3层热障涂层。传统TBC8结构为Ni22Cr10AlY合金连接层和8％Y2O3部分稳定的ZrO2(8YPSZ)陶瓷顶层；3层TBCs中分别采用置于8YPSZ陶瓷层内层及外层的Al2O3与8YPSZ复合层。3种类型试样的100h。1050℃静态氧化试验及1050℃热震试验结果表明：3层涂层较双层涂层的氧化阻力提高，双层涂层的热震阻力最佳，氧化阻力最差。不同复合层形式试样的热振失效方式和寿命也有差别，复合层置于陶瓷层外层热震寿命略高，但100h氧化增重有明显提高，抗氧化性降低。     

Al2O3对等离子喷涂热障涂层高温氧化及热震性能的影响

采用等离子喷涂 (PS)在GH5 36高温合金基材上制备了典型的双层热障涂层 (TBCs)和两种分别加入了Al2 O3 陶瓷成分的复合热障涂层。典型的TBCs采用Ni2 2Cr10AlY连接层与 8%Y2 O3 稳定的 (8YPSZ)顶层的双层结构 ;多层涂层分别采用Al2 O3 与Ni2 2Cr10AlY复合的连接层和Al2 O3 与 8YPSZ复合的顶层。3种类型试样的10 0h ,10 0 0℃静态氧化及 10 5 0℃热震试验的结果分析表明 :8YPSZ Al2 O3 的复合氧障层具有最佳的氧化阻力 ;Ni2 2Cr10AlY 8YPSZ双层涂层的热震阻力最佳 ,氧化阻力最差 ;连接层采用Ni2 2Cr10AlY Al2 O3 复合涂层具有热震和静态氧化条件下综合优良的高温热循环性能     

Processing, repairing and cyclic oxidation behaviour of sol–gel thermal barrier coatings

Sol–gel Thermal Barriers Coatings (TBCs) are manufactured using the dip-coating technique optimised in terms of process parameters including sol formulation, rate of withdrawing and heat treatment. The specific mechanisms of sol–gel TBCs, deposited on either NiAl or NiPtAl bond-coated superalloy substrates, are described. The possibility to reinforce and stabilise the crack network formed during the heat treatment or the first oxidation cycles using supplementary dip-coatings and appropriate process parameters is investigated. It is shown that implementing this technique that can be further regarded as an attractive way for repairing TBCs, significantly improves the cyclic oxidation behaviour of the multi-materials systems.     

Thermal Shock Resistance of APS 8YSZ Thermal Barrier Coatings on Titanium Alloy

Thermal barrier coatings (TBCs) with a typical 8YSZ ceramic top coat and CoNiCrAlY bond coat were deposited on titanium alloy substrate (Ti-6Al-4V in wt.%) by air plasma spraying. Thermal insulation and thermal shock resistance of the TBCs at different temperatures as well as their failure behavior were investigated. The results showed that the test temperature had a significant effect on thermal shock life of the TBCs. Failure of the TBCs systems was caused by the formation of crack, bond coat oxidation and elemental diffusion. The vertical cracks induced by thermal shock cycles were probably responsible for the enhancement in thermal shock resistance of the TBCs. Furthermore, elemental diffusion had a great effect on the acceleration of the TBCs failure. The TBCs could provide a good thermal protection for the titanium alloy substrate.     

Behavior of plasma-sprayed thermal barrier coatings during thermal cycling and the effect of a preoxidized NiCrAlY bond coat

The failure mechanisms of thermal barrier coatings (TBCs) subjected to a thermal load are still not entirely understood. Thermal stresses and/or oxidation cause the coating to fail and hence must be minimized. During the present investigation, TBCs up to 1.0 mm were sprayed and withstood high thermal stresses during thermal testing. Owing to the substantial thickness, the temperature at the top coat/bond coat interface was relatively low, resulting in a low oxidation rate. Furthermore, bond coats were preoxidized before applying a top coat. The bond strength and the behavior during three different thermal loads of the preoxidized TBCs were compared with a standard duplex TBC. Finite-element model (FEM) calculations that took account of bond coat preoxidation and interface roughness were made to calculate the stresses occurring during thermal shock. It is concluded that the thick TBCs applied during this research exhibit excellent thermal shock resistance and that a preoxidizing treatment of the bond coat increases the lifetime during thermal loading, where oxidation is the main cause of failure. The FEM analysis gives a first impression of the stress conditions on the interface undulations during thermal loading, but further development is required.     

High temperature properties of thermal barrier coatings obtained by detonation spraying

NiCrAlY/YPSZ and NiCrAlY/NiAl/YPSZ thermal barrier coatings (TBCs) were successfully deposited by detonation spraying. The results indicated that the detonation sprayed TBCs included a uniform ceramic coat containing a few microcracks and a bond coat with a rough surface. The lamellar structure and the presence of cracks and impurities could reduce the thermal conductivity of the ceramic coat. Oxidation kinetics at 1000–1150 °C of detonation sprayed TBCs have been measured and discussed. The role of a Ni–Al intermediate layer in improving the oxidation resistance of duplex TBCs has also been studied.     

Damage growth triggered by interface irregularities in thermal barrier coatings

The efficiency and reliability of modern jet engines strongly depend on the performance of thermal barrier coatings (TBCs), which prevent melting and oxidation of the turbine blades’ structural core. The system’s lifetime is limited by cracks appearing in and in the vicinity of an oxide layer that grows in the TBC under thermal cycling. High replacement costs have led to an increased demand to identify, quantify and remedy damage in TBCs. An integrated experimental–numerical approach is presented for studying the main factors that contribute to damage, particularly interfacial irregularities. Damage at several stages of oxidation in TBCs is analyzed in samples with predefined interfacial irregularities. The model predicts the experimentally observed crack patterns, clearly quantifying the influence of imperfections and indicating that damage can be delayed by surface treatment.