CVD-Silizium als Korrosionsschutz für die Beschaufelung von stationären Gasturbinen

Chemical Vapor Deposited silicon as a corrosion protection for the blades of stationary gas turbines In order to improve the corrosion resistance of heat resistant nickel alloys used as the blade materials for stationary gas turbines these materials were given a silicon coating by a chemical vapour deposition process. With the aid of microprobe and X-ray investigations the silicides formed were investigated. Coated specimens were exposed to a series of tests specifically oriented toward the intended use in stationary gas turbines. It turned out, that the silicide coatings on nickel base alloys are exceptionally stable to high temperature corrosion, so that a considerable increase of the useful life of silicided gas turbine blades may be expected.     

地面重型燃气轮机及其热障涂层的研究进展与发展趋势

国际公认的重型燃气轮机制造尖端技术之一—热障涂层技术,高温下通常面临CMAS(CaO-MgO-Al₂O₃-SiO₂)腐蚀、氧化、相变与烧结等问题,其抗CMAS腐蚀性等关键性能极大地影响涂层寿命,提高热障涂层的性能刻不容缓。对重型燃气轮机用热障涂层的研究进展与发展趋势进行全面总结与分析。首先介绍国内外重型燃气轮机的现状及发展趋势、热障涂层的系统结构、材料和几种典型的制备工艺,然后针对高温下燃气轮机热障涂层遇到的一些问题,对其隔热性、抗氧化性及抗热震性等关键性能的研究进展进行综述,最后分类详述热障涂层的CMAS腐蚀机理及其防护研究进展。综述热障涂层的几种关键性能,提出热障涂层的性能与其材料、结构及制备工艺密切相关,据此总结归纳提高热障涂层性能的方法,为热障涂层性能的提高提供参考依据,以弥补燃气轮机热障涂层领域目前缺乏这类综述文章的不足。     

High‐temperature corrosion behavior of some post‐plasma‐spraying‐gas‐nitrided metallic coatings on a Fe‐based superalloy

The objective of the present study is to propose a cost‐effective process for modifying commercially available coatings by gas nitriding using commonly available equipment and starting materials. Al–Cr and Ti–Al metallic coatings were deposited on Superfer 800H (Fe‐based superalloy) using a plasma spray process. Then the gas nitriding of the coatings was done in the lab and the parameters were optimized after conducting several trials on plasma‐sprayed‐coated specimens. Characterization and high‐temperature corrosion behavior of coatings after exposure to air and molten salt at 900°C were studied under cyclic conditions. Techniques like XRD, SEM/EDX, and X‐ray mapping analysis were used for the characterization of the coatings and analysis of the oxide scale. Both the coatings successfully protected the substrate and were effective in decreasing the corrosion rate when subjected to cyclic oxidation (Type‐I hot corrosion) at 900°C for 50 cycles in air and molten salt (a salt mixture of Na₂SO₄–60%V₂O₅ dissolved in distilled water). Based on the findings of the present study, the coatings under study are recommended for tapplications to super‐heater and reheater tubes of boilers and all those surfaces that face fireside corrosion, such as fluidized beds, industrial waste incinerators, internal combustion engines, gas turbines or steam turbines, to provide protection against degradation in these environments. The cost of the product/process is approximately Rs. 0.62 per mm² in case of Al–Cr coating and Rs. 1.86 per mm² in case of Ti–Al coating.     

Failure mechanism of MCrAlY coating at the coating‐substrate interface under type I hot corrosion

MCrAlY coatings are widely used to provide protection of hot component in modern gas turbine engines against high‐temperature oxidation and hot corrosion. Coating‐substrate interface, where the substrate is only partially covered by the ?coatings, is vulnerable to the hot corrosion attack. The accelerated degradation at the coating‐substrate interface can cause fast spallation of the coating, leading to the early failure of the gas turbine components. In this paper, MCrAlY powder was deposited on IN792 disks by high‐velocity oxygen‐fuel spraying. The hot corrosion behavior of the coated sample was investigated using (0.8Na, 0.2K)₂SO ₄ salt deposition at 900°C in lab air. Results showed a minor attack in the coating center, however, an accelerated corrosion attack at the coating‐substrate interface. The fast growth of corrosion products from substrate caused large local volume expansions at the coating‐substrate interface, resulting in an early coating spallation.     

Advances in Thermal Spray Coatings for Gas Turbines and Energy Generation: A Review

Functional coatings are widely used in energy generation equipment in industries such as renewables, oil and gas, propulsion engines, and gas turbines. Intelligent thermal spray processing is vital in many of these areas for efficient manufacturing. Advanced thermal spray coating applications include thermal management, wear, oxidation, corrosion resistance, sealing systems, vibration and sound absorbance, and component repair. This paper reviews the current status of materials, equipment, processing, and properties’ aspects for key coatings in the energy industry, especially the developments in large-scale gas turbines. In addition to the most recent industrial advances in thermal spray technologies, future technical needs are also highlighted.     

燃气轮机在海洋环境下的热腐蚀与防护技术研究进展

针对海洋环境下舰船燃气轮机的热腐蚀现状,从热腐蚀的机理研究着手,基于不同阶段提出的热腐蚀模型理论,分析了高温和低温两种热腐蚀类型的发生过程和表现特征,指出热腐蚀实质上是以Na2SO4为主导的熔盐沉积共晶物与金属基体发生反应而导致金属材料加速氧化的过程。在此基础上,详细介绍了三种涂层防护技术—扩散涂层、覆盖涂层和热障涂层,并根据这三种涂层的发展阶段和功能特性,分析了其在制备工艺、作用机理和应用领域上表现出的差异性,重点强调了热障涂层(TBCs)在当前的发展境况。结合世界各国研究者开展的代表性工作,全面综述了国内外在舰船燃机热腐蚀防护领域的研究进展,重点描述了以硫酸盐为主的腐蚀介质中,金属材料的热腐蚀表现特征,并展示了数值模拟、热力学模拟等方法在热腐蚀研究上的应用案例。最后,对舰船燃气轮机涂层防护技术的发展方向进行了展望,提出发展新一代环障涂层(EBCs)是提高燃气轮机综合防护能力的有效技术手段。     

复合多防涂装在海水中的防护性能

介绍了油漆涂层，金属喷涂层，金属喷涂层／油漆封闭等13种复合多防涂装在静海和动海海水试验中的耐海水腐蚀性能，并对其耐腐蚀性能作了简要分析，进而选出最佳的涂装体系，实践结果表明，704＋842＋546环氧沥青，702＋846＋546环氧沥青，热喷A1涂层和喷A1＋842＋546环氧沥青4种涂装具有优良的耐静海海水腐蚀性能，环氧石英砂浆和热喷铝＋843＋546环氧沥青2种涂装具有优良的耐动海海水腐蚀性能。     

热浸镀Zn-Al-Mg镀层在模拟湿热海洋大气环境中的腐蚀行为研究

目的 为详细研究热浸镀Zn-Al-Mg镀层在模拟湿热海洋大气下的腐蚀行为及作用机理,同时为热浸镀Zn-Al-Mg镀层在湿热海洋大气环境中服役提供数据参考。方法 采用腐蚀失重、XRD、SEM、电化学等测试方法对热浸镀Zn-Al-Mg镀层在模拟湿热海洋大气环境下的腐蚀行为进行研究。结果 腐蚀产物主要由Zn₅(OH)₈Cl₂·H₂O组成,腐蚀一段时间后,发现少量ZnO、Zn₅(OH)₆CO₃,腐蚀产物具有与锌腐蚀类似的层状结构,1 848 h呈“三明治”型,相比于上下两层暗色物质,中层亮色腐蚀产物富集更多的Cl元素。热浸镀Zn-Al-Mg镀层腐蚀速率大体随时间延长呈上升趋势,只在672～840 h腐蚀速率下降,对比镀锌在模拟环境和锌在湿热大气环境中的腐蚀,热浸镀Zn-Al-Mg镀层在模拟湿热海洋大气中表现出较好的耐蚀性。结论热浸镀Zn-Al-Mg镀层在模拟湿热海洋大气下腐蚀产物演变与腐蚀过程中Mg的参与有关。腐蚀672～840h阶段腐蚀速率...     

铬铝涂层及其抗高温腐蚀的行为

本文作者采用粉末包装法制备Cr-Al二元涂层,对Cr-Al二元涂层的制备以及涂层的高温腐蚀性能进行了研究。实验结果表明,在纯Ni上制备Cr含量较高的Cr-Al共渗涂层是困难的,纯Ni上Cr-Al共渗时,Al会同时沉积到纯Ni试样和Cr粉表面上,由于Cr粉表而上铝涂层的形成,大大降低丁Cr的活度,从而抑制了Ni上渗Cr的过程;然而,在纯Ni上用二步法制备Cr-Al二元涂层是可行的,先渗Cr后渗Al能产生理想的Cr-Al二元涂层,涂层具有良好的抗高温氧化和抗热腐蚀性能;而先渗Al后渗Cr则产生有孔洞的Cr-Al二元涂层,涂层的抗高温腐蚀性能很差。     

Hot Corrosion Behavior of a High Velocity Arc-Sprayed Fe-Cr-B-C Coating

A Fe-Cr-B-C coating was prepared by electric arc spraying process to prevent the boiler tubes from hot corrosion at elevated temperatures.A hot corrosion resistance test was conducted in a mixed molten salt of Na2SO4 and K2SO4(7:3)at 700 ℃for a total period of 156 h.The microstructure and phases of the coatings before and after exposed to the hot corrosion were investigated by scanning election microscopy(SEM),optical microscopy(OM)and X-ray diffraction(XRD).The hardness and porosity were analyzed.The hot corrosion behavior of the coatings was examined by the measurement of corrosion mass gain and the observation of corrosion morphology.The results show that some splats of particles are formed on flat substrate surfaces and the coatings have a dense typical layer structure of electric arc thermally spraying deposits.Some amorphous phase exist in the coating.The coatings have an excellent resistance to hot corrosion.The formation of oxides of chromium on the exposed surface may be contributing better resistance to hot corrosion.The corrosion of the coatings follows the oxidation and sulfidation mechanism.     

Inelastic constitutive equation of plasma-sprayed ceramic thermal barrier coatings

Ceramic thermal barrier coatings (TBCs) are a very important technology for protecting the hot parts of gas turbines (GTs) from a high-temperature environment. The coating stress generated in the operation of GTs brings cracking and peeling damage to the TBCs. Thus, it is necessary to evaluate precisely such coating stress in a TBC system. We have obtained a stress-strain curve for a freestanding ceramic coat specimen peeled from a TBC coated substrate by conducting the bending test. The test results have revealed that the ceramic coating deforms nonlinearly with the applied loading. In this study, an inelastic constitutive equation for the ceramic thermal barrier coatings deposited by APS is developed. The obtained results are as follows: (1) the micromechanics-based constitutive equation was formulated with micro crack density formed at splat boundary, and (2) it was shown that the numerical results for a nonlinearly deformed beam simulated by the developed constitutive equation agreed with the experimental results obtained by cantilever bending tests.     

热障涂层无损检测技术研究进展

为提高发动机的涡轮前温度和热端部件服役寿命,热障涂层（TBCs）被广泛应用于燃气涡轮发动机。热障涂层具有多相、多界面和非均质特性,且其服役工况恶劣复杂。寻找一种可以表征涂层显微组织、缺陷、热物性、应力等反映涂层质量和剩余寿命的无损检测方法,对发动机的热端部件安全性和可靠性至关重要。文中综述了超声检测技术（UT）、声发射技术（AE）、红外热成像技术（IRT）、阻抗谱技术（IS）和光激发荧光压电光谱技术（PLPS）的原理以及其在热障涂层无损检测中的研究应用,并详细介绍了太赫兹时域光谱（THz-TDS）技术及其在热障涂层中的应用。最后总结了上述无损检测方法的检测能力,并对热障涂层无损检测方法进行展望。     

Internal surface protection of gas turbine blade by Si‐aluminide coating

A laboratory‐scale slurry silicoaluminizing process has been developed to apply coating into cooling passageways of a first‐stage gas turbine blade. Analytical techniques for characterizing the coatings comprised optical microscopy, SEM, EDS, and XRD. The results of metallographic examinations demonstrated that acceptable coatings had been formed in almost all of the passageways. The amounts of Al and Si in the topcoat were found to be in the ranges of 24–26 wt% and 4.5–6 wt%, respectively. The heat treated coating consisted largely of β‐NiAl phase as the coating matrix with uniform distribution of <2 µm‐size precipitates. In addition, oxidation and hot corrosion performance of the coatings were investigated by cyclic exposure to 1100 °C and the furnace method using a mixture of sodium sulfate‐40 wt% sodium vanadate‐10 wt% sodium chloride at 780 °C, respectively. It was found that the presence of Si in the coating improves both oxidation and hot corrosion Type II properties.     

An evaluation study of aluminide and chromoaluminide coatings on IN-100

Aluminide diffusion coatings are commonly used to protect aircraft gas turbine blades and vanes from oxidation and hot-corrosion attack. These coatings are based on NiAl intermetallic compound with other alloying elements like Cr and Ti either diffused from the superalloy substrate or incorporated in a separate coating step. The present investigation is mainly concerned with the development of both aluminide and chromoaluminide coatings on IN-100, a cast Ni-base superalloy. The coating structure and composition have been characterized and the cyclic oxidation and hot corrosion properties have been evaluated for the different types of coatings. The difference in the hot-corrosion properties between the aluminide and the chromoaluminide coatings has been rationalized in terms of the coating chemistry. The mode of coating degradation under hot-corrosion conditions has also been analyzed.     

铸造镍基合金K-3的热腐蚀及防护研究

用光学显微镜、X 光衍射、扫描电镜、能谱分析和化学分析等多种手段,对经热腐蚀后的K-3合金试样及渗铝的 K-3合金涡轮叶片进行了分折研究。结果表明叶片失效的原因是硫化及熔盐引起的热腐蚀;低铬、富难熔金属的 K-3合金的热腐蚀机制是硫化、碱性熔解和酸性熔解的综合作用。用 RFL 燃气腐蚀装置对不同的保护涂层进行抗热腐蚀性能的对比试验表明:渗铝的防护效果并不理想,而富硅的扩散型和融烧型料浆铝硅涂层则具有良好的抗热腐蚀性能。     

热腐蚀和盐雾腐蚀影响氮化物涂层冲蚀行为的机制

金属氮化物涂层是目前重点关注的航空发动机压气机抗冲蚀涂层体系。为了兼顾热物理化学环境和应力环境的影响,进行涂层的腐蚀-冲蚀耦合行为研究十分重要。本研究对比了TiN/Ti涂层与TiN/ZrN涂层的原始状态、热腐蚀后和盐雾腐蚀后的冲蚀行为。结果表明,对于TiN/Ti涂层,在涂层的缺陷处盐雾腐蚀时形成点蚀坑,这是发生冲蚀的薄弱环节,盐雾腐蚀后TiN/Ti涂层的抗冲蚀能力及结合力低于原始涂层和热腐蚀后的涂层。对于TiN/ZrN涂层,热腐蚀过程中液滴表面形成疏松的腐蚀产物和氧化物,使其在冲蚀时更容易脱落,热腐蚀过程中产生的层间热应力削弱了涂层的结合力。热腐蚀涂层冲蚀后呈现严重的螺旋状剥落,热腐蚀后TiN/ZrN涂层的抗冲蚀能力及结合力低于原始涂层和盐雾腐蚀后涂层。     

Thermal spray manufacturing issues in coating IGT hot section components

The desire to improve the performance of gas turbine engines has led to higher operating temperatures in the turbine sections of the engine. Materials used for hot section turbine blades and vanes are not resistant to hot corrosion, and therefore require protective coatings. This paper reviews the current art and technology of thermally sprayed MCrAlY and TB coatings onto hot section components. The issues in applying such coatings will be discussed, along with references to manufacturing issues on the shop floor. The difficulties inherent in applying a line-of-sight coating to complex geometries will be discussed. The testing, evaluation, and performance characteristics of typical coatings are discussed. Adapted from P. Sahoo et al., “Thermal Spray Manufacturing Issues in Coating IGT Hot Section Components,” Paper No. 97-GT-487, American Society of Mechanical Engineers, 1997.     

Development of Low-Oxide MCrAlY Coatings for Gas Turbine Applications

Advanced high-energy plasma systems are being used to achieve the benefits of the high-velocity oxy-fuel (HVOF) system without losing the inherent advantages of plasma for coating of gas turbine parts. MCrAlY coatings play a very important role in the performance and reliability of gas turbine components. One of the important considerations for next generation of gas turbines, which have more demanding conditions and need to withstand ever increasing operating temperatures, is that they should possess very low oxygen content levels in the coating. Low oxygen content coatings are applied by the expensive low-pressure plasma spray (LPPS)/vacuum plasma spray (VPS) technique for critical components in aero- and land-based gas turbines. This work deals with the development of low-cost LPPS equivalent coatings (having low oxygen content) using the high-energy high-velocity plasma spray (HEHVPS) gun and inert gas shroud. A comparison has also been made with CoNiCrAlY coatings by HVOF.     

Some Aspects of the Hot Corrosion of Thermal Barrier Coatings

This paper reviews the hot corrosion of zirconia-based thermal barrier coatings for engine applications. Emphasis is placed on understanding the chemical reactions, and such other mechanisms as can be iden-tified, that cause corrosive degradation of the thermal barrier coating. The various approaches taken to improve the hot corrosion resistance of thermal barrier coatings are also briefly described and critiqued.     

Hot corrosion of TBC-coated components upon combustion of low-sulfur fuels

Gas turbine reliability is a crucial requirement for passenger safety in aviation and a secure energy supply. Hence, corrosive degradation of combustor parts, vanes, and blades in gas turbines must be prevented. One of the most severe forms of corrosion is alkali-sulfate-induced hot corrosion, which is associated with internal sulfidation of components and is usually anticipated to fade in importance in the absence of sulfur. However, the literature suggests that hot corrosion might still occur in low-sulfur combustion gases. In this study, established thermodynamic modeling methods are used to analyze the low-sulfur hot corrosion regime. Liquid sodium chromate is found to be stable in these conditions. A comparison of calculation results and engine findings suggests that high alkali levels can negatively impact thermal barrier coating life even if sulfur is absent in the fuel. Laboratory tests are carried out to validate the chromate formation on MCrAlY-coated specimens. It is shown that molten sodium chromate can alter the oxidation behavior of MCrAlY, promoting the formation of voluminous spinel. This represents a new and different form of hot corrosion compared to type I hot corrosion.