单晶高温合金DD6再结晶晶界析出相特征及其形成机制

对单晶高温合金DD6进行表面吹砂处理,然后进行固溶与时效真空热处理,采用SEM,TEM,EPMA和Thermo-Calc的方法研究了单晶合金DD6再结晶晶界析出相的特征及其形成机制.结果表明,经过吹砂处理的DD6合金在固溶与时效热处理过程中发生再结晶.再结晶晶界出现析出相,分析表明析出相为M_6C碳化物,该碳化物呈粒状析出,尺寸约为0.5μm,数量极少,富含W,Re和Mo,且Cr,Nb和Co的含量与合金名义成分差别不大,而Al,Ta和Ni含量较低.由于再结晶晶界上C元素的聚集效应,C原子在晶界上达到一定浓度后即与一定数量的W,Mo等μ相形成元素发生相变反应,抑制了合金析出μ相的倾向.又因为DD6合金W含量较高,而Cr含量较低,抑制了M_(23)C_6碳化物,有利于析出M_6C碳化物.     

铸造镍基高温合金增材修复技术的研究现状

铸造镍基高温合金广泛用于燃气轮机与航空发动机叶片等高温部件,长时间运行过程中经常发生叶片局部损伤失效,其维修或更换成本极高。通过增材修复来恢复局部损伤叶片的性能,将极大地降低制造成本、缩短制造周期、节约资源,具有极大的社会效益和市场价值。本文针对燃气轮机与航空发动机用铸造镍基高温合金部件的服役工况与失效形式,结合铸造镍基高温合金的成分、组织与性能特点,系统分析了增材修复时出现裂纹的类型、特点及形成机理,阐述了各类裂纹的主要影响因素,从增材工艺和材料两方面分类综述了减少或避免裂纹的增材修复工艺与技术现状,分析了不同增材修复方法的优缺点与未来可能的研究热点。     

Precision Cast vs. Wrought Superalloys

The advancement of jet engine technology has traditionally given wrought superalloys eminence when design calls for both reasonable high temperature strength and dynamic fracture reliability. Despite the attractiveness of cast superalloys for their improved buy-to-fly ratios and higher strengthening γ volume fractions, the expansion of polycrystalline castings into the more critical of the superalloy applications has been prevented by a lack of sufficient micro structural control in casting technology. Recently, however, advances in casting technology are making possible the production of defect tolerant superalloy castings with improved fracture reliability. This new generation of superalloy castings now offers serious competition to wrought superalloys. Never before have wrought superalloys been so seriously threatened by their cast counterparts.     

镍基单晶高温合金涡轮叶片薄壁效应研究进展

镍基单晶高温合金具有优异的高温综合性能,是航空发动机涡轮叶片和导向叶片等部件的首选材料,承受高温度和高应力的严苛服役环境。目前,高冷效叶片的结构设计中采用多种复杂冷却结构以提高其承温能力,其中以层板冷却和双层壁冷却为代表的微型冷却结构是其主流发展方向。但由于这类复杂涡轮叶片中存在超薄壁结构,已成为叶片制造的关键点和难点。本文综述了镍基单晶高温合金薄壁结构的发展趋势,分析了薄壁受限空间的缺陷产生及枝晶生长规律,阐述了薄壁结构对力学性能的影响,展望了先进涡轮叶片的制备及其组织控制的发展趋势。     

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。     

R & D OF CAST SUPERALLOYS AND PROCESSING FOR GAS TURBINE BLADES IN BIAM

Research and development of cast superalloys and processing for turbine blades in BIAM during the last 35 years have been reviewed briefly in this paper.     

MAR-M247合金高温断裂机制的原位研究

利用原位高温拉伸台在扫描电镜中研究了镍基铸造高温合金MAR-M247在室温、400 ℃与760 ℃拉伸过程中的动态组织演变和断裂机制。原位测试结果表明,在室温到760 ℃范围内,MAR-M247合金的屈服强度与抗拉强度随温度的升高略有下降,拉伸塑性略有提高。室温原位拉伸过程中,并没有出现滑移带;400 ℃与760 ℃的原位拉伸,只在样品断口附近存在少量的滑移带。随拉伸温度的提高,合金的断裂机制并无明显变化,均表现为韧性穿晶断裂。合金的微裂纹主要来源于变形过程中碳化物的破裂,晶内与晶界都存在因碳化物破裂而形成的微裂纹。     

涂层/高温合金界面行为及调控研究进展EI北大核心CSCD

防护涂层技术对于提高涡轮叶片材料抗氧化腐蚀性能、保证涡轮叶片安全服役具有至关重要的作用,然而,防护涂层与高温合金间有本征的物理、化学性能不匹配性,其界面反应会导致界面组织退化,合金与涂层性能下降,成为制约涂层应用的关键因素。本文概述了典型涂层/高温合金界面组织演变与扩散行为及其影响因素,讨论了界面行为对含涂层高温合金组织稳定性和力学性能的影响,从涂层组织成分优化、界面阻扩散层设计和新型界面稳定涂层研发3个方面介绍了涂层/合金界面的调控方法。总结了涂层/高温合金界面相容性的关键特征,并提出未来应在界面对涂层/合金性能的影响规律与机制、调控界面的多手段联用、计算辅助涂层设计等方面开展系统性研究。     

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.     

新型涡轮盘用高性能粉末高温合金的研究进展

综合分析了国外第3代粉末高温合金的化学成分、显微组织和点阵常数,总结出新型涡轮盘用高性能粉末高温合金的研发趋势,重点介绍了作者课题组与钢铁研究总院合作在国内率先进行我国新型第3代高性能粉末高温合金的初期研究工作与成果,并提出了研制高性能粉末高温合金的重点研究方向。     

考虑炉壁温度变化的高温合金叶片定向凝固过程模拟

考虑炉壁温度的变化,基于Monte Carlo射线追踪法建立了高温合金叶片定向凝固过程的温度场计算改进模型.通过法向射线加密提高加热炉炉壁的辐射计算精度,并采用叶片三维有限差分网格和加热炉二维网格混合使用的方法提高计算效率.叶片和炉壁的温度曲线模拟与实验结果吻合良好,改进模型反映了抽拉过程中炉壁温度的变化及其对叶片内部温度分布的影响,提高了叶片温度的模拟精度.     

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...     

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。     

MICROSTRUCTURAL EVOLUTION AND CONTROL IN SUPERALLOY FORGINGS

ＭＩＣＲＯＳＴＲＵＣＴＵＲＡＬＥＶＯＬＵＴＩＯＮＡＮＤＣＯＮＴＲＯＬＩＮＳＵＰＥＲＡＬＬＯＹＦＯＲＧＩＮＧＳＲ．Ｎｏｅｌ,Ｄ．Ｆｕｒｒｅｒ,Ｇ．ＳｈｅｎａｎｄＪ．Ｌｅｍｓｋｙ（ＬａｄｉｓｈＣｏ．,Ｉｎｃ．,Ｐ．Ｏ．Ｂｏｘ８９０２,Ｃｕｄａｈｙ,ＷＩ５...     

Processing of Advanced Cast Alloys for A-USC Steam Turbine Applications

The high-temperature components within conventional supercritical coal-fired power plants are manufactured from ferritic/martensitic steels. To reduce greenhouse-gas emissions, the efficiency of pulverized coal steam power plants must be increased to as high a temperature and pressure as feasible. The proposed steam temperature in the DOE/NETL Advanced Ultra Supercritical power plant is high enough (760°C) that ferritic/martensitic steels will not work for the majority of high-temperature components in the turbine or for pipes and tubes in the boiler due to temperature limitations of this class of materials. Thus, Ni-based superalloys are being considered for many of these components. Off-the-shelf forged nickel alloys have shown good promise at these temperatures, but further improvements can be made through experimentation within the nominal chemistry range as well as through thermomechanical processing and subsequent heat treatment. However, cast nickel-based superalloys, which possess high strength, creep resistance, and weldability, are typically not available, particularly those with good ductility and toughness that are weldable in thick sections. To address those issues related to thick casting for turbine casings, for example, cast analogs of selected wrought nickel-based superalloys such as alloy 263, Haynes 282, and Nimonic 105 have been produced. Alloy design criteria, melt processing experiences, and heat treatment are discussed with respect to the as-processed and heat-treated microstructures and selected mechanical properties. The discussion concludes with the prospects for full-scale development of a thick section casting for a steam turbine valve chest or rotor casing.     

RECENT DEVELOPMENTS IN AEROSPACE PROPULSION MATERIALS

ＲＥＣＥＮＴＤＥＶＥＬＯＰＭＥＮＴＳＩＮＡＥＲＯＳＰＡＣＥＰＲＯＰＵＬＳＩＯＮＭＡＴＥＲＩＡＬＳＴ．Ｋｈａｎ（Ｏｎｅｒａ,Ｂ．Ｐ．７２,９２３２２ＣｈａｔｉｌｌｏｎＣｅｄｅｘ,ＦｒａｎｃｅＭａｎｕｓｃｒｉｐｔｒｅｃｅｉｖｅｄ２６Ａｕｇｕｓｔ１９９６）...     

单晶高温合金的中温Ⅰ阶蠕变--涡轮叶片伸长的重要因素

单晶镍基高温合金已广泛用于制造先进燃气涡轮叶片,但这种合金至今仍被忽视的薄弱环节是它的中温Ⅰ阶蠕变伸长量远高于高温蠕变,而且与高温蠕变相比,中温Ⅰ阶蠕变对取向偏离、合金成分和热处理组织的变化更为敏感.虽然预蠕变引进较高的位错密度能有效抑制中温蠕变,但在实用上仍有困难.在选用单晶合金作为涡轮叶片时,应考虑到先进的二代和三代单晶在中温下的抗变形能力不如一代单晶,同时中温大应力状态下的叶片根部可能过度伸长.     

NICKEL-BASED ALLOYS IN GE AIRCRAFT TURBINES:PAST,PRESENT & FUTURE

Improvements in materials have been critical to advances in the propulsion system. Over the past 50 years, many improvements have been made to nickel-based superalloys to satisfy design requirements; several key developments will be highlighted. Today, millions of pounds of superalloys are annually produced for use in turbine blades, vanes, disks, cases, and frames throughout the engine. Looking to the future, several themes emerge, although predicting the future is inherently risky.     

NICKEL-BASED ALLOYS IN GE AIRCRAFT TURBINES：PAST,PRESENT ＆ FUTURE

1. Introduction Freedom to travel anywhere in the world, both quickly and inexpensively, defines our modern era. Despite year-to-year variation, the long term demand for travel by airplane continues to grow. Three ma- jor systems comprise the modern airplane: the aircraft structure that encompasses the fuselage, wings, and landing gear; the avionics that enable flight through crowded skies in nearly all weather conditions; and the propulsion system that powers the aircraft. Improvements in mat…     

Influence of service-induced microstructural changes on the aging kinetics of rejuvenated Ni-based superalloy gas turbine blades

Rejuvenation of Ni-based superalloy gas turbine blades is widely and successfully employed in order to restore the material microstructure and properties after service at high temperature and stresses. Application of hot isostatic pressing (HIP) and re-heat treatment can restore even a severely overaged blade microstructure to practically “as-new” condition. However, certain service-induced microstructural changes might affect an alloy’s behavior after the rejuvenated blades are returned to service. It was found that advanced service-induced decomposition of primary MC carbides, and the consequent changes of the γ-matrix chemical composition during the rejuvenation, can cause a considerable acceleration of the aging process in the next service cycle. The paper will discuss the influence of the previous microstructural deterioration on the aging kinetics of rejuvenated gas turbine blades made from IN-738 and conventionally cast GTD-111 alloys.