稀土掺杂ZrO_2基热障涂层陶瓷材料研究进展

热障涂层用于燃气轮机的热端部件,不仅可以显著提高其使用温度,延长热端部件的使用寿命,而且提高了燃气轮机发动机的效率.介绍了稀土掺杂ZrO2基热障涂层的研究现状及发展趋势.结果表明LnO1.5-Ta2O5（或Nb2O5）-YSZ材料既可以提高传统YSZ热障涂层的使用温度,而且也降低了其热导率.LnO1.5-Ta2O5（或Nb2O5）-YSZ材料可以作为热障涂层系统中陶瓷顶层的下一代候选材料.     

热障涂层用稳定ZrO_2基陶瓷材料研究现状

综述了氧化物稳定的热障涂层用ZrO2陶瓷的研究现状.氧化物稳定ZrO2陶瓷材料主要适用于在1000℃左右工作的热障涂层,而不宜用作新型高温热障涂层表面陶瓷层材料.随着航空发动机技术的发展,稀土铈酸盐陶瓷材料有望替代氧化物稳定的ZrO2陶瓷.根据声子导热理论和晶体化学原理,选用合适的氧化物对稀土铈酸盐陶瓷材料进行掺杂,可进一步降低其热导率并改善热膨胀系数,这将为热障涂层技术应用开辟广阔的空间.     

燃气轮机热障涂层陶瓷材料发展现状及展望

Y2O3部分稳定的ZrO2(YSZ)陶瓷热障涂层在1200 K以上服役时会出现烧结、体积变化、腐蚀等问题而发生失效.为明确能替代YSZ陶瓷的新型陶瓷材料的研究方向和发展趋势,本文阐述了热障涂层常见制备方法的原理和优缺点,总结归纳了传统ZrO2基材料的掺杂改性和新型陶瓷材料的研究现状.认为对ZrO2基陶瓷材料进行掺杂改性...     

热障涂层用稳定ZrO2基陶瓷材料研究现状

综述了氧化物稳定的热障涂层用ZrO2陶瓷的研究现状．氧化物稳定ZrO2陶瓷材料主要适用于在1000℃左右工作的热障涂层,而不宜用作新型高温热障涂层表面陶瓷层材料．随着航空发动机技术的发展,稀土铈酸盐陶瓷材料有望替代氧化物稳定的ZrO2陶瓷．根据声子导热理论和晶体化学原理,选用合适的氧化物对稀土铈酸盐陶瓷材料进行掺杂,可进一步降低其热导率并改善热膨胀系数,这将为热障涂层技术应用开辟广阔的空间．     

等离子喷涂复合热障涂层的静态氧化行为

采用等离子喷涂方法，在GH536高温合金基材上制备了传统的双层热障涂层（TBCs）和两种含有Al2O3与ZzO2陶瓷复合层的三层热障涂层，传统TBCs结构为Ni22Cr10AlY合金连接层和8％Y2O3部分稳定的ZrO2陶瓷顶层；三层TBCs分别用了置于陶瓷层内侧及外侧的Al2O3复合层，三种类型试样的100h,1050℃静态氧化试验结果表明：三层涂层较双层涂层的氧化阻力提高，双层涂层的氧化阻力最差，不同复合层形式试样氧化动力学曲线不同，内置复合层的氧化增重最小，氧化阻力最佳。1050℃是氧化增重的临界点，外置复合层试样的氧化增重出现明显增加趋势。     

热障涂层对活塞温度场影响的三维分析

为提高内燃机的工作效率和使用寿命,以表面涂覆热障涂层的发动机活塞为主要研究对象,综合分析热障涂层对活塞温度场的影响.建立了热障涂层活塞的三维模型,运用有限元软件对其进行了温度场分析计算,考察了不同涂层材料和涂层厚度对活塞温度场的影响情况.研究结果表明:0.4mm厚的ZrO2陶瓷涂层可使活塞的隔热效果提升约8.8%,并且隔热效果明显优于Al2O3、Si3N4和SiC;ZrO2涂层厚度每增加0.5mm,活塞金属基体顶面的最高温度下降约3.2℃,陶瓷涂层顶面的最高温度上升约8.3℃.     

激光熔覆Al2O3陶瓷涂层组织结构

研究了45钢表面激光熔覆等离子Al2O3陶瓷喷涂层的组织结构、硬度及滑动磨损特性。结果表明，等离子喷涂Al2O3陶瓷涂层呈层片状，涂层疏松，由α－Al2O3,ZrO2和γ－Al2O3组成。激光熔覆Al2O3陶瓷涂层致密，由α－Al2O3及ZrO2组成。激光熔覆Al2O3涂层硬度较高，滑动磨损时其耐磨性也明显优于等离子喷涂Al2O3陶瓷涂层。     

等离子喷涂热障涂层抗氧化性能研究

热障涂层在航空发动机热端部件上有着越来越广泛的应用 ,由于热端部件工作温度很高 ,它的抗高温氧化性显得十分重要。通过 90 0℃恒温静态氧化试验和循环氧化试验 ,对用空气等离子喷涂方法制备的热障涂层试样进行了抗氧性能测试 ,并对其结果进行了详细的分析。结果表明 ,此热障涂层系统在 90 0℃的抗氧化性能良好 ;为保持良好的抗氧化性能 ,防止涂层剥落 ,热循环次数不能超过 90次 ;静态氧化曲线基本遵循抛物线规律。此外 ,影响热障涂层的因素有热应力、残余应力、ZrO2 相变以及热腐蚀等     

钢表面ZrO2陶瓷纳米等离子喷涂

采用等离子喷涂技术在20Cr钢表面等离子喷涂纳米ZrO2涂层,并用1Cr18Ni9作中间梯度涂层,用以制造特殊管状绝热体.利用SEM方法研究了梯度涂层的结构和显微组织,通过摩擦磨损试验对涂层的耐磨性能进行了分析,用热震法研究了涂层和基体的结合力,并用有无热障涂层的箱体进行实际模拟对比试验,测试了涂层的隔热性能.研究结果表明,ZrO2纳米陶瓷层和1Cr18Ni9梯度层可以形成良好的机械结合;喷涂后的试样表面显微硬度显著提高,耐磨性比GCr15轴承钢提高2.84倍;纳米陶瓷梯度涂层使20Cr钢的隔热性能和抗高温氧化性能显著提高.     

等离子喷涂改性YSZ涂层耐熔融玻璃腐蚀机制

采用Al2O3、TiO2掺杂改性8％Y2O3-ZrO2(质量分数,YSZ)陶瓷粉末,通过等离子喷涂制备Al2 O3-TiO2-Y2O3-ZrO2(AT+YSZ)热障涂层,1 200℃,保温2 h,对两种涂层进行熔融玻璃腐蚀试验.采用扫描电子显微镜(SEM)、X射线衍射仪(XRD)、维氏显微硬度分析仪对AT+YSZ涂层及...     

Mechanical Study of Nano-ceramic Thermal Barrier Coatings by the Equation of Phonon Radiative Transfer

基于辐射模型的微、纳米尺度陶瓷热涂层的热力学性能分析

张士元¹,郑百林²,贺鹏飞²

（1 福建工程学院 土木工程系,福建福州,350007;2 同济大学 航空航天与力学学院,上海,200092）

摘要：温度场、热应力（特别是剥离力）和J积分对于热冲击下的热涂层具有重要作用,在微、纳米尺度上,能量传输机制与宏观尺度上有显著的不同。对于热冲击条件下微、纳米尺度陶瓷热涂层结构,采用声子辐射输运方程(EPRT)（用于纳米尺度陶瓷涂层）和傅里叶热传导定理（用于基底）相结合求得温度场,继而得到热应力和J积分。将这些结果与涂层和基底都采用傅里叶热传导定理计算的结果进行比较,同时分析了热物理特性（如弛豫时间和声子速度）对这些结果的影响。结果表明,用EPRT计算的温度、热应力和J积分,低于采用傅里叶热传导定理计算的结果。此外,TBCs的热物理性质对温度场和热应力的影响在TBCs表面和内部不同。

关键词:微纳尺度陶瓷热涂层,纯声子辐射模型,热应力,J积分

     

激光制备陶瓷热障涂层的研究和发展

论述了激光制备陶瓷热障涂层的研究和发展状况 .激光制备陶瓷热障涂层包括激光重熔和激光熔覆两种方法 .激光重熔等离子喷涂热障涂层可获得等离子喷涂涂层所不具备的外延生长致密的柱状晶组织 ,提高涂层应变容限及热震性能 .激光熔覆可获得自动分层的梯度热障涂层成分及柱状晶组织 ,改善涂层的高温氧化及热震性能 .通过激光工艺参数的优化及涂层体系成分及性能的合理设计 ,可获得优于等离子喷涂 ,接近电子束物理气相沉积的热障涂层性能     

Evaluation of properties and thermal stress field for thermal barrier coatings

In order to get thermal stress field of the hot section with thermal barrier coating (TBCs), the thermal conductivity and elastic modulus of top-coat are the physical key properties. The porosity of top-coat was tested and evaluated under different high temperatures. The relationship between the microstructure (porosity of top-coat) and properties of TBCs were analyzed to predict the thermal properties of ceramic top-coat, such as thermal conductivity and elastic modulus. The temperature and stress field of the vane with TBCs were simulated using two sets of thermal conductivity data and elastic modulus, which are from literatures and this work, respectively. The results show that the temperature and stress distributions change with thermal conductivity and elastic modulus. The differences of maximum temperatures and stress are 6.5% and 8.0%, respectively.     

Microstructures and Mechanical Properties of Ceramic/Metal Gradient Thermal Barrier Coatings

1　IntroductionCeramicthermalbarriercoatings (TBCs)sprayedonmetalsubstrateshavebeenusedtoincreasethetempera turelimitsandtodecreasetheheatrejectionforgastur bineanddieselengines .However,themismatchbetweenceramicsandmetalwillcausethermalstresseswhichmayleadtocrackandspallofthecoatings .Functionalgradi entmaterials (FGMs)areanewconceptionfordesigningtheceramic metalthermalbarriercoatings ,whichhasgradientmicrostructureaswellasgradientmaterialprop ertiesandcangreatlydecreasethethermalstresses[…     

In-situ measurement of elastic modulus for ceramic top-coat at high temperature

The ceramic thermal barrier coatings (TBCs) play an increasingly important in advanced gas turbine engines because of their ability to further increase the engine operating temperature and reduce the cooling, thus help achieve future engine low emission, high efficiency and improve the reliability goals. Currently, there are two different processes such as the plasma spraying (PS) and the electron beam-physical vapor deposition (EB-PVD) techniques. The PS coating was selected to test the elastic modulus. Using the nanoindentation and resonant frequency method, the mechanical properties of ceramic top-coat were measured in-situ. According to the theory of the resonant frequency and composite beam, the testing system was set up including the hardware and software. The results show that the accurate characterization of the elastic properties of TBCs is important for stress-strain analysis and failure prediction. The TBCs systems are multi-layer material system. It is difficult to measure the elastic modulus of top-coat by tensile method. The testing data is scatter by nanoindentation method because of the microstructure of the ceramic top-coat. The elastic modulus of the top-coat between 20?1 150 ℃ is obtained. The elastic modulus is from 2 to 70 GPa at room temperature. The elastic modulus changes from 62.5 GPa to 18.6 GPa when the temperature increases from 20 ℃ to 1 150 ℃.     

High temperature cyclic oxidation behavior of Y2O3-ZrO2 thermal barrier coatings irradiated by high-intensity pulsed ion beam

The high-temperature oxidation resistance behavior of 7% (mass fraction) Y₂O₃-ZrO₂ thermal barrier coatings (TBCs) irradiated by high-intensity pulsed ion beam (HIPIB) was investigated under the cyclic oxidation condition of 1 050 °C and 1 h. The columnar grains in the TBCs disappear after the HIPIB irradiation at ion current densities of 100–200 A/cm² and the irradiated surface becomes smooth and densified after remelting and ablation due to the HIPIB irradiation. The thermally grown oxide (TGO) layer thickness of the irradiated TBCs is smaller than that of the original TBCs. After 15 cycles, the mass gains of the original TBCs and those irradiated by ion current densities of 100 and 200 A/cm² due to the oxidation are found to be 0.8–0.9, 0.6–0.7, and 0.3–0.4 mg/cm², respectively. The inward diffusion of oxygen through the irradiated TBCs is significantly impeded by the densified top layer formed due to irradiation, which is the main reason for the improved overall oxidation resistance of the irradiated TBCs. Foundation item: Projects supported by The 2nd Stage of Brain Korea and Korea Research Foundation     

Study on Z-H/BMP Toughened Compound Artificial Bone and Its Osteogenesis

1　IntroductionWiththedevelopmentofspinesurgery ,bettermateri alsaredemandedinthespinalfusion .Thespinecanbefusedfromtheposterior ,theanteriororintervertebrae ,meanwhilemoreboneisdemanded .Soitisnecessarytofindasuperiorbonematerialforspinalfusion .Scholarshavetriedagainandagain ,buttheyusedtoemployonlyonekindofmaterialsforspinalfusion[1-4] ,includinghydroxyapatite(HA) ,metalinterverteralfusioninstrument(madeoftitaniumorstainlessteel) ,polymer ,bonemor phogeneticprotein (BMP) ,myeloidtissuean…     

铝合金上等离子喷涂NiCrAlCoY/ZrO2梯度热障层连接的研究

利用等离子喷涂法在发动机铝合金活塞上制得NiCrAlCoY与用质量分数为8％的Y2O3稳定的ZrO2梯度热障层。经热震实验、金相分析、SEM分析和TEM分析，结果表明该热障层具有良好的抗热冲击性和高温热稳定性，并且NiCrAlCoY与ZrO2间形成了化学键结合。这为今后解决TBCs可靠性的问题提出了新的思路。     

The properties of solution precursor plasma spray nanostructured thermal barrier coatings

About 300 μm thickness uniform thermal barrier coatings (TBCs) were deposited on the 1Cr18Ni9Ti samples by solution precursor plasma spray (SPPS).The analysis methods,such as TEM,SEM,and XRD were used to characterize the coatings in the aspects of microstructure and phase compositions.The samples were quenched from 1121 ℃ to room temperature by forced-air to measure the thermal cycling capability.Coatings density were measured by means of water displacement.The experimental results show that grain size of the SPPS TBCs is about 30 nm with desired tetragonal phase ZrO2,and the SPPS TBCs(with 16% porosity) consist of arcuate pores,gelatin and melted particles.The hardness of the coatings is HR45Y38.5 and bond strength between coatings and substrates is 24.2 MPa.The thermal shock test show the coatings have a average life of 500 cycles which is about 2.5 times than that of conventional air plasma spray (APS) TBCs.