共查询到19条相似文献,搜索用时 156 毫秒
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粉末高温合金是先进航空发动机关键热端部件的优选材料,先进的粉末制备技术是获得高品质高温合金粉末、保证合金件质量的关键技术。近年来,我国在粉末高温合金的研发和生产技术方面都取得了突破性进展,成功研发出新一代粉末高温合金,形成了成熟的粉末高温合金生产工艺。在粉末制备技术方面,通过对高纯净母合金熔炼技术、先进雾化制粉技术和电选分离技术的深入研究,进一步发展了粉末纯净化制备技术,满足了我国航空发动机领域对粉末高温合金关键零部件的需求。简要回顾了国内外粉末高温合金的发展历程,分析了粉末高温合金中的缺陷来源及其对合金性能的影响,概述了我国镍基高温合金粉末制备技术的发展情况,讨论了未来高温合金粉末及其关键制备技术的发展方向。 相似文献
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粉末高温合金研究进展 总被引:5,自引:0,他引:5
粉末高温合金是制造高性能航空发动机涡轮盘等转动部件的关键材料.针对国外粉末高温合金的研究历史和现状,结合粉末高温合金的制备工艺流程,重点介绍了美国和俄罗斯粉末高温合金的发展现状,对比分析了不同粉末制备工艺、粉末固结工艺、盘件成形工艺的特点,总结了粉末高温合金中存在缺陷的原因及控制方法.针对我国粉末高温合金的研究历史和现状,总结了国内粉末高温领域所取得的进展.对国内外粉末高温合金在航空发动机上的应用进行了总结.对超纯净度细粉制备、直接热等静压近终成形、双性能粉末涡轮盘制备工艺等高性能粉末高温合金的关键技术及发展方向进行了展望.针对国内对粉末高温合金的需求现状,指出了国内粉末高温合金研制和生产过程中存在的问题并给出了相应的解决思路. 相似文献
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粉末高温合金的低周疲劳研究进展 总被引:1,自引:0,他引:1
参考了前人对粉末高温合金低周疲劳的研究成果,回顾了基于缺陷的裂纹萌生和扩展的研究情况,介绍了针对粉末高温合金的喷丸强化机理和作用,总结了几种寿命模型,其中修正Mitchell模型最适合粉末高温合金的寿命预测;得出了需加强粉末高温合金低周疲劳寿命模型及喷丸强化研究的结论。 相似文献
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目的 研究GH4698微型涡轮盘热塑性成形工艺。方法 采用有限元软件Deform-3D对镍基高温合金微型涡轮盘模锻过程进行数值模拟分析,研究坯料不同高径比、不同模锻温度下涡轮盘成形的最大载荷值、等效应力、等效应变、速度场的变化规律。结果 微型涡轮盘模锻过程载荷最大值随模锻温度升高而降低,温度和高径比对涡轮盘的凸台、直榫等部位的等效应力、等效应变影响有明显的差异。在涡轮盘路径1上,随着温度的升高,等效应力逐渐降低,变形更加均匀;随着高径比的增加,变形不均匀程度增大,高径比为1时等效应力的极大值最小;温度和高径比对速度场的影响较小。结论 温度和高径比对GH4698微型涡轮盘锻造变形行为有显著的影响,选择合适的模锻工艺参数可以有效降低成形载荷,并获得使用性能较好的微型涡轮盘。 相似文献
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烟气轮机涡轮盘和叶片用WASPALOY合金研究 总被引:4,自引:0,他引:4
对烟气轮机涡轮盘和叶片用WASPALOY合金从合金成分特点、相析出规律、冶炼、加工和力学性能等方面进行了综述和讨论,重点介绍了该合金针对烟气轮机使用环境的合金设计特点及析出相特征,为烟气轮机用涡轮盘和叶片材料的发展给出研究方向。 相似文献
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目的 研究GH901合金涡轮盘锻件的成形工艺.方法 采用有限元软件Simufact-2D对镍基高温合金涡轮盘的锤上模锻过程进行数值模拟分析,研究不同中间坯高径比下涡轮盘的填充效果及等效应变变化规律;研究不同锤击能量下涡轮盘的温度分布规律.结果 GH901合金涡轮盘锤上模锻时,中间坯高径比过大或过小均影响填充效果,同时不同高径比下模锻的等效应变也有差异.当高径比为0.21时,锻件填充效果最好,且应变分布均匀.随着锤击能量的增加,锻件心部产生温升的程度增大,锤击时交替采用50%和80%的能量打击,可得到温度分布较合理的锻件.结论 中间坯高径比和锤击能量对GH901合金涡轮盘的锻造变形行为有显著影响,选择合适的锤上模锻工艺参数可以得到尺寸精度高、组织均匀且性能优良的涡轮盘锻件. 相似文献
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O.Kh. Fatkullin V.I. Yeriomenko O.N. Vlasova N.N. Korneyeva 《Advanced Performance Materials》1997,4(1):71-83
Despite projected inroads from competing materials Ni-based superalloys remain the material of choice in the hot sections of advanced gas turbine engines. In this paper microstructural development and improvement of mechanical properties in mill products produced by ingot metallurgy (IM) and powder metallurgy (PM) techniques are discussed. Particular attention is given to approaches to improvement in ingot ductility. Thermomechanical treatment schemes used during forging of a complex-alloyed Ni-based superalloy are recommended. It is demonstrated that the PM technique used for production of this complex-alloyed superalloy is a promising approach. On the basis of the studies carried out the salient features of the structure of material produced both by both IM and PM techniques have been defined. The mechanical properties of two versions of an advanced Ni-base superalloy produced by IM and PM techniques are discussed. The best combination of mechanical properties are exhibited by a PM material with a necklace structure; and this latter structure is superior to a fine grained structure for IM product also. 相似文献
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工业燃气轮机具有热效率高、污染低等突出优点,成为未来发电机组与大型水面舰船动力的首选设备。铸造高温合金是工业燃气轮机涡轮叶片等热端部件的关键材料,其性能和制备水平在一定程度上决定了先进燃气轮机的功率、效率、寿命等性能。本文重点综述了工业燃气轮机及其涡轮叶片用铸造高温合金材料的研究及应用现状,并对工业燃气轮机涡轮叶片用铸造高温合金及涡轮叶片制造技术的发展趋势进行了展望。未来,先进定向凝固,“材料基因工程”等技术将逐渐应用到工业燃气轮机涡轮叶片用铸造高温合金的研制中;此外,先进工业燃气轮机上定向/单晶高温合金的应用将越来越广泛。 相似文献
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B.I. Bondarev N.F. Anoshkin O. KH. Fatkullin G.S. Garibov L.S. Buslavsky I.A. Kononov V.I. Yeremenko 《Advanced Performance Materials》1997,4(1):85-93
The paper shows stages of development of Ni-base superalloy powder metallurgy in Russia, including modifying of the alloys, with the reference to this new technology, production, testing and flying service of turbine disks in various aircraft engines. Histograms plotted from the results of mechanical property testing are presented. Prospects of application of PM Ni-base superalloys in production of aircraft engines are shown. 相似文献
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There is a need to increase the temperature capability of superalloy turbine disks to allow higher operating temperatures
in advanced aircraft engines. When modifying processing and chemistry of disk alloys to achieve this capability, it is important
to preserve the ability to use rapid cooling during supersolvus heat treatments to achieve coarse grain, fineγ′ microstructures. An important step in this effort is an understanding of the key variables controlling the cracking tendencies
of nickel-base disk alloys during quenching from supersolvus heat treatments. The objective of this study was to investigate
the quench cracking tendencies of several advanced disk superalloys during simulated heat treatments. Miniature disk specimens
were rapidly quenched after solution heat treatments. The responses and failure modes were compared and related to the quench
cracking tendencies of actual disk forgings. Cracking along grain boundaries was generally observed to be operative. For the
alloys examined in this study, the solution temperature, not alloy chemistry, was found to be the primary factor controlling
quench cracking. Alloys with high solvus temperatures show greater tendency for quench cracking. 相似文献