镍基铸造高温合金低周疲劳研究进展

镍基铸造高温合金具有优异的高温性能,广泛应用于航空发动机涡轮叶片等热端部件之中。航空发动机涡轮叶片是发动机中工作环境最为恶劣、结构最为复杂的零件之一,在发动机运行过程中所产生的高温交变应力的作用下,合金承受着严重的应力、应变循环损伤,裂纹往往在合金中的薄弱区域形成并扩展,使合金以低周疲劳的模式失效,严重影响了合金的服役寿命,因此对合金低周疲劳性能的研究尤为重要。本文详细阐述了影响镍基铸造高温合金低周疲劳性能的表面缺陷、内部组织及缺陷、晶体取向和低周疲劳试验条件等四方面因素,从位错运动方式和形态变化特点出发,研究了不同温度下镍基铸造合金的变形机制,最后总结了合金低周疲劳寿命预测的应力应变准则、能量准则、损伤累积准则及临界面和临界距离准则。     

镍基高温合金叶片焊接修复技术的研究进展

镍基高温合金在整个高温合金领域内占有特殊重要的地位,它广泛地用来制造航空喷气发动机、各种工业燃气轮机的最热端部件,尤其是发动机的叶片.随着国内航空业的飞速发展,镍基高温合金叶片的先进焊接修复技术有着非常广阔的应用前景.综述了镍基高温合金叶片焊接修复技术的研究状况,主要涉及激光熔覆、堆焊和钎焊等方法,指出了这些方法的特点、最新进展及适用性.     

镍基高温合金修复强化技术研究现状及发展趋势

镍基高温合金具有优良的高温强度和抗氧化性能,广泛应用于航空发动机、涡轮叶片等热端部件。其在高温、高压、高转速及交变负荷等恶劣条件下长期使用过程中,易出现烧蚀、磨损等表面损伤和掉块、断裂等体积损伤。采用特定的表面工程技术和增材修复技术可有效恢复损伤零件的尺寸和性能,为镍基高温合金综合使役性能的保持和再生提供可行途径。重点综述了表面改性、表面镀层、表面涂层、载能束增材、能束能场复合等镍基高温合金修复强化技术国内外研究现状,归纳总结了各修复方法的技术原理、工艺特点及应用范围。加强能束能场复合修复技术开发、能束能场与材料的作用机理,以及修复过程形性协同调控等方面的研究,对拓宽工艺适用范围、降低修复强化层缺陷以及增强修复机动时效性具有重要意义,是镍基高温合金修复强化技术未来发展趋势。     

激光增材修复K465高温合金裂纹控制研究

采用激光增材技术修复了损坏的K465镍基高温合金航空发动机涡轮叶片,研究了激光增材修复K465高温合金的裂纹特征,分析了开裂机理,并采取有效措施实现了裂纹控制。结果表明:激光增材修复K465合金的裂纹产生于热影响区,并沿晶界扩展到修复区中,为液化裂纹;热影响区晶界上的连续液膜来源于晶界上大尺寸γ′相的液化,且晶界液化过程中有γ-γ′共晶出现;利用Ansys软件进行应力场模拟的结果显示,基材及熔池之间存在较大热应力;通过同步预热基材,并采用优化的激光工艺参数,实现了K465高温合金单道多层结构的无裂纹激光增材修复。     

镍基高温合金K403电火花沉积工艺

高Al、Ti型镍基高温合金具有良好的热稳定性、热强度和高温组织稳定性,广泛地应用于航空发动机叶片、燃气轮机热端部件等高端精密领域。由于这些热端部件造价昂贵且极易损坏,对该种零件进行维修与再制造成为降低该类部件运行成本的重要方法。由于Al、Ti含量会增大高温合金的焊接裂纹发生率,传统的熔焊技术很难应用到该类部件的维修当中,利用微弧电火花沉积技术对高Al、Ti型镍基高温合金K403进行了沉积试验,获得无裂纹堆焊层,为高Al、Ti高温合金的再制造工程增加了新的工艺方法。     

沉淀强化镍基高温合金熔化焊液化裂纹研究进展

沉淀强化镍基高温合金由于具有优异的高温强度和耐热腐蚀性而被广泛应用于航空发动机和工业燃气轮机的热端部件。但是这类合金在焊接过程中具有较高的液化裂纹敏感性,影响部件的使用寿命和性能。系统地阐述了沉淀强化镍基高温合金熔化焊液化裂纹的形成机理,介绍了几种控制液化裂纹的方法,包括增大焊接热输入、焊前预热、焊前热处理和添加中间层,最后指出了今后的主要研究方向。     

数据驱动镍基铸造高温合金设计及复杂铸件精确成形

材料基因组工程与材料智能制备加工技术的发展为航空发动机高温合金关键热端部件的研发与制造提供了新的思路.针对航空发动机涡轮机匣类结构件高温合金材料与铸造成型的需求,开发了高通量并发式的热动力学模拟软件系统,结合镍基铸造高温合金的筛选判据,从520万余种成分组合中筛选并研制了一种新型镍基铸造高温合金,815℃、400 MP...     

重型燃汽轮机叶片用材料和失效原因概述

叶片是重型燃气轮机的关键零件,其服役环境苛刻,需采用高性能的材料制作,以确保重型燃气轮机稳定、可靠运行。目前,重型燃气轮机叶片主要采用镍基高温合金制造,如IN-738、GTD-111、MGA1400、K44及单晶高温合金等。透平叶片的成形工艺也在不断发展,早期的镍基高温合金叶片均是锻造成形的。为提高透平叶片主应力方向(长度方向)的蠕变强度等性能,定向凝固精密铸造技术于1970年前后得到了快速发展和应用。但由于透平入口处燃气温度急剧提高,采用定向凝固技术生产的镍基高温合金叶片已不能满足使用要求,1980年前后又开发了用单晶制备透平叶片的技术并得到了应用。重型燃气轮机叶片长期在高温高压的燃气中运行,不但经受燃气的高温氧化和热腐蚀,还承受离心力和高压燃气产生的弯曲力,其失效形式有腐蚀、疲劳和蠕变等。不含或含少量铼的镍基单晶高温合金具有良好的综合性能,是我国重型燃气轮机叶片用材料的发展方向。     

高Al、Ti含量镍基高温合金激光、微弧火花表面熔焊处理研究进展及解决熔焊裂纹的途径

Al、Ti是镍基高温合金主要沉淀强化元素,随着Al、Ti含量的增加,镍基高温合金γ'-Ni3(Al,Ti)相体积百分数增加,高温强度增加,但是热裂纹敏感性也随之增加,如何利用熔焊工艺实现高Al、Ti镍基高温合金材料的表面无损伤熔焊处理一直是高Al、Ti镍基高温合金叶片与热端部件制造与再制造面临的难题.文中从高温合金表面熔焊修复与强化问题出发,着重介绍了高温合金焊接冶金问题及焊接性改善途径、激光与微弧火花两种低热输入熔焊工艺在高温合金表面修复与强化领域的研究与应用进展.分析表明:高Al、Ti镍基高温合金表面熔焊处理的主要难题是其高的热裂纹敏感性,主要表现在焊接或焊后热处理过程中容易产生凝固裂纹、液化裂纹、应变时效裂纹,采用惰性气体保护、改变基体组织状态、使用低强度的合金焊料、降低热输入等措施可有效改善其焊接性;激光、微弧火花等低热输入焊接工艺在解决高Al、Ti镍基高温合金表面熔焊问题方面具有极大的潜力.     

Research Progress on the Crack Formation Mechanism and Cracking-Free Design of gamma' Phase Strengthened Nickel-Based Superalloys Fabricated by Selective Laser MeltingEI北大核心CSCD

传统牌号高强镍基高温合金具有较宽的凝固温度区间、较高比例的低熔点共晶相,在增材制造快速非平衡凝固过程中易产生裂纹等缺陷;同时,热处理过程中残余应力释放和γ’相快速析出导致应变时效裂纹的形成,严重限制了其在激光增材制造领域的应用与推广。基于此,本文综述了近年来国内外研究组及作者团队在选区激光熔化高强镍基高温合金裂纹形成机理与抗裂纹设计(成形工艺参数优化、热处理制度调控以及合金成分设计)领域相关的研究进展,并对激光增材制造γ’相强化镍基高温合金裂纹调控的研究进行了展望。     

激光增材制造高温合金复合材料研究进展

本文对增材制造技术在高温合金复合材料中的研究进行了系统全面地梳理归纳，综述了增材制造高温合金复合材料的粉末混合、冶金过程以及强化机制，并且在增材制造高温合金复合材料显微组织、缺陷及其性能方面进行详细对比分析研究。在此基础上，分析了增材制造高温合金复合材料研究现状及进展，并且对高温合金复合材料新增强相设计、增强相添加方式及其对蠕变疲劳性能的影响机制等的研究进行了展望，本文将有利于对增材制造高温合金复合材料的研究和发展提供参考。     

Manufacturing Processes for Long-Life Gas Turbines

Dual-alloy turbine wheels produced by solid-state diffusion bonding of vacuum investment cast blade rings of one superalloy to preconsolidated powder metal hubs of a second superalloy have the long cyclic lives characteristic of wrought or powder superalloys combined with the high creep strength and net-shape blades characteristic of cast superalloys. A wide variety of superalloys and turbine configurations are compatible with this technology. Improved temperature capability turbine blades and vanes of the MAR-M 247 alloy made by directional solidification casting processes are now in volume production for Garrett gas turbines. Single-crystal alloys derivative to MAR-M 247 further extend the temperature capability of turbine blades and have been successfully engine tested. These blades are produced by a relatively simple modification of the processes used to manufacture directionally solidified blades.     

Magnetic Property Changes of CoNiCrAlY Coating Under Cyclic Oxidation and Hot Corrosion

Oxidation of Metals - In this paper, a non-destructive method for evaluation of a CoNiCrAlY coating applied to gas turbine blades has been studied. The specimens from cast Ni-base superalloy...     

Additive Manufacturing of Nickel-Based Superalloy Single Crystals with IN-738 Alloy

The production of non-weldable nickel-based superalloys, especially single-crystal superalloys, is important for additive manufacturing. Single-crystal specimens of non-weldable nickel-based superalloys were produced by electron beam selective melting using an IN-738 alloy. In this study, single-crystal nickel-based superalloy specimens of different sizes were prepared by a multiple preheating process and tight control of the melting parameters without the need for a grain selector or single-crystal seed for the first time. Electron backscattered diffraction measurements were performed to confirm the presence of a single crystal. The transition boundaries between the polycrystalline and single-crystal regions at the edges and bottom of the samples were characterized to analyze the formation of single crystals.     

Isothermal Oxidation Behaviour of NiCoCrAlYTa Coatings Produced by HVOF Spraying and Tribomet™ Process

Protective NiCoCrAlYTa coatings are used on gas turbine single crystal superalloy blades to provide environmental resistance. They can be deposited by several processes. In this study, isothermal oxidation behaviour of NiCoCrAlYTa coatings produced by HVOF spraying and Tribomet? process and deposited on single crystal nickel-based superalloy CMSX-4 were compared between 950 and 1,150 °C for several exposure durations. Microstructure and chemical composition of both coatings were examined before and after oxidation testing and quite similar observations were made for both coating processes. The combination of phase and chemical analyses allowed the establishment of an occurrence diagram of phases for both coating processes, according to temperature and duration of exposure. The obtained diagrams seemed similar for both processes. Finally both processes appeared to be equivalent for the protection of CMSX-4 superalloy in isothermal oxidation conditions.     

Oxidation-induced damage of an uncoated and coated nickel-based superalloy under simulated gas environment

Turbine blades and vans operated in an aggressive gas environment usually suffer from combined oxidation and cycle loading effects. The surface oxide layer will result in premature failure and lead to a significant reduction in the service lifetime. The effects of prior oxidation-induced damage under a simulated combustion-gas environment on the fatigue lifetime of the directionally solidified(DS) nickel-based superalloy DZ125 with and without an oxidation-resistant coating were presented. The fatigue lifetime of uncoated samples is adversely affected by prior oxidation exposure. The deterioration of fatigue lifetime in uncoated samples is associated with surface microstructural degradation, which occurs during prior exposure. However,the presence of MCrAlY coating is beneficial for the sample's lifetime under high stress. Further scanning electron microscopy(SEM) analysis demonstrates that the coating does not contribute to the initiation mode of fatigue cracks.     

Numerical analysis of the weldability of superalloys

When manufacturing fusion welds, the potential exists for defects to be introduced. The possibilities include the formation of a centreline grain boundary, interdendritic microporosity, constitutional liquation and solidification cracking. In this paper, numerical analysis is carried out in order to predict the processing conditions necessary to cause the occurrence of these phenomena. Although the models developed are of general applicability, their behaviour is examined particularly with respect to the tungsten–inert gas (TIG) welding of the nickel-based superalloy IN718. Weldability maps are presented, on which the conditions for successful processing are identified.     

Numerical simulation and experimental validation on fabrication of nickel-based superalloy Kagome lattice sandwich structures

Nickel-based superalloy lattice sandwich structures present higher stiffness,higher strength and higher temperature resistance in comparison with other metals.In this study,the Kagome unit was adopted to design the lattice sandwich structure and ProCAST software was used to simulate the filling and solidification processes of the nickel-based superalloy.Grain morphology and sizes of the nickel-based superalloy lattice sandwich structures were simulated by using of cellular automaton coupled with finite element model(CAFE),and indirect additive manufacture combining with investment casting were carried out to fabricate the nickel-based superalloy lattice sandwich structures.The calculated grain morphology and sizes are in good agreement with the experimental results.The grains are mainly equiaxed with an average size of about 500µm.The simulated results also show that the superheat of melting and the mold preheated temperature have significant influence on the grain size of the Kagome lattice sandwich structures,lower superheat of melting and mold preheated temperatures are encouraged to obtain the fine grains while assuring the integrity of the Kagome lattice sandwich structures for industrial application.