CN110072647B - 用于制作具有薄根部件的铸造部件的一体化铸造芯壳结构 - Google Patents
用于制作具有薄根部件的铸造部件的一体化铸造芯壳结构 Download PDFInfo
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Abstract
本发明大体涉及一体化芯壳熔模铸造模具,其提供对应于涡轮叶片或轮叶的薄根部件(即,天使翼、裙部、阻尼器凸耳)的凹口结构。
Description
技术领域
本公开大体涉及熔模铸造芯壳模具部件和运用这些部件的处理。根据本发明制作的芯壳模具包括在模具的芯和壳之间的一体化陶瓷凹口,可以用来形成由这些模具制作的涡轮叶片或定子轮叶中的薄根部件,即,天使翼、阻尼器凸耳和裙部。一体化芯壳模具在铸造操作中提供有用的性质,诸如在制作用于喷气飞行器发动机或发电涡轮部件的涡轮叶片和轮叶的超合金的制造中。
背景技术
许多现代发动机和下一代涡轮发动机要求具有曲折和复杂几何形状的部件和零件,这要求新型材料和制造技术。用于制造发动机零件和部件的常规技术涉及到费力的熔模或失蜡铸造处理。熔模铸造的一个示例涉及到用在燃气涡轮发动机中的典型转子叶片的制造。涡轮叶片一般包括具有径向通道的中空翼型件,径向通道沿着具有至少一个或多个入口的叶片的跨度延伸,用于在发动机操作期间接收加压冷却空气。叶片中的各种冷却通路一般包括蛇形通道,蛇形通道安置在翼型件的在前缘和尾缘之间的中部。翼型件一般包括延伸通过叶片的入口,用于接收加压冷却空气,入口包括局部特征,诸如短的紊流肋或销,用于增加翼型件的受热侧壁和内部冷却空气之间的热传递。
一般由高强度、超合金金属材料制造这些涡轮叶片涉及到图1中示出的诸多步骤。首先,制造精密陶瓷芯以符合涡轮叶片内侧所需的曲折冷却通路。还创建精密压模或模具,其限定涡轮叶片的精确3D外部表面,涡轮叶片包括其翼型件、平台和一体化楔形榫。这种模具结构的示意图在图2中示出。陶瓷芯200组装在两个压模半部内侧,两个压模半部在其间形成限定叶片的所得金属部分的空间或空隙。将蜡注入组装的压模中以填充空隙并围绕封装其中的陶瓷芯。将两个压模半部分开并从模制蜡中去除。模制蜡具有期望叶片的精确构造,然后涂覆有陶瓷材料以形成围绕的陶瓷壳202。然后,将蜡熔化并从壳202去除,在陶瓷壳202和内部陶瓷芯200和顶腔204之间留出对应的空隙或空间201。然后将熔化的超合金金属倒入壳中以填充其中的空隙,并再次封装容纳在壳202中的陶瓷芯200和顶腔204。熔化的金属冷却并凝固,然后适当地去除外部壳202和内部芯200和顶腔204,留下其中发现有内部冷却通道的期望金属涡轮叶片。为了提供经由浸出处理去除陶瓷芯材料的路径,设置球形槽203和顶销205,在浸出时在涡轮叶片内形成球形槽和顶孔,随后必须钎焊闭合。
然后,铸造涡轮叶片可以经历附加的后铸造改造,诸如但不限于,视所需通过翼型件的侧壁钻出合适的多排膜冷却孔,用于为内部导通的冷却空气提供出口,内部导通的冷却空气然后在燃气涡轮发动机的操作期间在翼型件的外部表面上边形成保护性冷却空气膜或垫。在涡轮叶片从陶瓷模具中去除之后,陶瓷芯200的球形槽203形成通路,随后通路被钎焊闭合,以提供通过铸造涡轮叶片的内部空隙的期望空气路径。然而,这些后铸造改造受到限制,并且鉴于涡轮发动机的复杂性不断增加以及认识到涡轮叶片内侧的某些冷却回路的效率,要求更复杂和曲折的内部几何形状。虽然熔模铸造能够制造这些零件,但是,使用这些常规制造处理制造的位置精度和曲折的内部几何形状变得更复杂。由此,期望提供一种用于具有曲折内部空隙的三维部件的改进铸造方法。
名称为“叶片裙部(Blade Skirt)”的美国专利No.9,039,382描述包括叶片根部的细节的涡轮叶片。叶片300一般具有翼型件302、平台304、柄部306和具有枞树构造的多叶楔形榫308。在叶片300的前侧,具有前天使翼310。在叶片300的后侧,具有远侧后天使翼312,在其径向向内处是近侧后天使翼314,两者之间具有间隙。在近侧后天使翼314的近侧,具有融合到叶片裙部318中的圆角316。可以在叶片300的前侧和后侧之间的柄部306内设置凹部。在该凹部内,具有前阻尼器保持凸耳324和后阻尼器保持凸耳326,它们彼此一起使用以保持阻尼器(未示出)。楔形榫区段308插入转子(未示出)中,使得楔形榫叶328与转子配合以径向上将叶片固定就位。
在熔模铸造处理期间,图3中示出的整个结构以蜡的形式制备,然后在蜡上形成陶瓷壳。除非涡轮叶片的根部分中的突出特征(即,天使翼、叶片裙部、阻尼器凸耳)足够厚,否则,在处置蜡期间、在处置最终金属零件期间或者在形成陶瓷壳的同时,在从蜡模具中去除时这些特征将变形。例如,天使翼、裙部和阻尼器凸耳的最小尺寸必须大于25密耳(0.64mm),优选地,大于30密耳(0.8mm)。
依然需要备制使用更高分辨率方法生产的陶瓷芯壳模具,该方法能够在铸造处理的终端产品中提供精细的细节铸造特征。
发明内容
在一个实施例中,本发明涉及一种制造用于涡轮叶片的陶瓷模具的方法。该方法具有下述步骤:(a)使工件的固化部分与液态陶瓷光聚合物接触;(b)通过接触液态陶瓷光聚合物的窗口照射液态陶瓷光聚合物的邻近于固化部分的一部分;(c)从未固化的液态陶瓷光聚合物去除工件;以及,(d)重复步骤(a)-(c),直到形成陶瓷模具为止,陶瓷模具包含:芯部分和壳部分,在芯部分和壳部分之间具有至少一个空腔,空腔适配成在铸造和去除陶瓷模具时限定涡轮叶片或轮叶的形状;以及空腔,该空腔限定具有小于0.64mm的最小尺寸的涡轮叶片或轮叶根部件。在步骤(d)之后,该处理可以进一步包括步骤(e):将液态金属倒入铸造模具中并使液态金属凝固以形成铸造部件。在步骤(e)之后,该方法可以进一步包括步骤(f),步骤(f)包含从铸造部件中去除模具,优选地,该步骤涉及到机械力和碱性浴中的化学浸出的组合。
在另一方面,本发明涉及一种制备涡轮叶片或轮叶的方法。该方法包括下述步骤:将液态金属倒入陶瓷铸造模具中并凝固液态金属以形成涡轮叶片或轮叶,陶瓷铸造模具包含:芯部分和壳部分,在芯部分和壳部分之间具有至少一个空腔,空腔适配成在铸造和去除陶瓷模具时限定涡轮叶片或轮叶的形状;以及空腔,该空腔限定具有小于0.64mm的最小尺寸的涡轮叶片或轮叶根部件。
在另一方面,本发明涉及一种陶瓷铸造模具,其具有:芯部分和壳部分,在芯部分和壳部分之间带有至少一个空腔,空腔适配成在铸造和去除陶瓷模具时限定铸造部件的形状;以及空腔,该空腔限定具有小于0.64mm的最小尺寸的涡轮叶片或轮叶根部件。陶瓷可以是光聚合陶瓷或固化的光聚合陶瓷。
在又一方面,本发明涉及一种单晶金属涡轮叶片或轮叶,其具有内空腔和外表面,多个冷却孔提供内空腔和外表面之间的流体连通,并且涡轮叶片或轮叶根部件具有小于0.64mm的最小尺寸。优选地,单晶金属是超合金。
在一个方面,涡轮叶片或轮叶根部件具有在0.1和0.6mm的范围内的最小尺寸。在另一方面,涡轮叶片或轮叶根部件具有在0.2和0.5mm的范围内的最小尺寸。
在一个方面,涡轮叶片或轮叶根部件是天使翼、裙部或阻尼器凸耳。
附图说明
图1是示出常规熔模铸造的步骤的流程示图。
图2是示出用于通过常规处理制备的具有球形槽的芯壳模具的常规方案的示例的示意性示图。
图3示出具有连接芯部分和壳部分的连接件的现有技术的一体化芯壳模具的立体视图。
图4、图5、图6和图7示出用于执行直接光处理(DLP)的方法次序的连续阶段的设备的示意性横向截面视图。
图8示出沿着图7的线A-A的示意性截面视图。
图9示出根据本公开实施例制作的涡轮叶片根部分的立体视图。
具体实施方式
下面连同附图一起阐述的详细描述意在作为各种构造的描述,而不意在表示可以实践文中描述的概念的唯一构造。出于提供对各种概念的透彻理解的目的,该详细描述包括具体细节。然而,这些概念可以在没有这些具体细节的情况下实践对本领域技术人员而言将是明显的。例如,本发明提供一种制作铸造金属零件的优选方法,优选地,用在制造喷气飞行器发动机中的那些铸造金属零件。具体地,根据本发明,可以有利地生产单晶、镍基超合金铸造零件,诸如涡轮叶片、定子轮叶和护罩部件。然而,可以使用本发明的技术和一体化陶瓷模具备制其他铸造金属部件。
本发明人认识到,已知用于制作涡轮叶片和定子轮叶的现有处理(即,熔模铸造)缺乏,对于生产具有薄叶片根部元件的涡轮叶片和轮叶来说必要的精细分辨率性能。特别地,熔模铸造中的蜡处理步骤严重限制制造涡轮叶片的能力,其中叶片或轮叶根部元件可以视所需制作为薄的或精细的。
本发明人发现了,本发明的一体化芯壳模具可以使用直接光处理(DLP)制造。DLP与粉末床和SLA处理的不同之处在于,聚合物的光固化通过树脂箱底部的窗口发生,该窗口将光投射到随着处理进行而升高的构建平台上。利用DLP,同时生产整层固化聚合物,并且消除使用激光扫描图案的需要。进一步,聚合发生在该下方的窗口和正在构建的物体的最后固化层之间。下方的窗口提供支撑,允许生产材料的细长丝而不需要分离的支撑结构。换言之,生产桥接构建物体的两个部分的材料的细长丝是困难的,在现有技术中一般是避免的。例如,分配给劳斯莱斯公司的美国专利No.8,851,151描述使用3D打印来生产陶瓷芯壳模具的方法,使用与短柱体连接的竖向板结构,短柱体的长度大约为它们的直径。因为'151专利中公开的粉末床和SLA技术要求竖向支撑的陶瓷结构,所以需要交错的竖向空腔,并且该技术不能可靠地生产对应于铸造涡轮叶片的薄涡轮叶片根部件(即,天使翼、阻尼器凸耳、裙部)的薄凹口或凹部。此外,粉末床内的可得分辨率大约为1/8"(3.2mm),使得薄涡轮叶片根部件的生产不可行。例如,这些薄涡轮叶片根部件大体具有小于0.64mm的最小尺寸,优选地,在0.1到0.6mm的范围内,更优选地,在0.2到0.5mm的范围内。如文中使用的,术语“最小尺寸”意指“最小可能尺寸”。生产这种尺寸的涡轮叶片根部件要求在粉末床处理中根本不用的分辨率。相似地,由于缺乏与激光散射相关的支撑和分辨率问题,立体光刻在其生产这种薄凹口的能力上有限。但是,DLP曝光凹口的整个长度并在窗口和构建板之间支撑它的事实使之能够生产具有期望最小尺寸的足够薄的凹口。尽管粉末床和SLA可以被用以生产凹口,但是,如上所述,它们生产足够精细的凹口的能力有限。
一种合适的DLP处理公开在分配给义获嘉伟瓦登特公司(Ivoclar Vivadent AG)和维也纳工业大学(Technische Universitat Wien)的美国专利No.9,079,357以及WO2010/045950A1和US2013131070中,其中的每一个通过引用的方式并入此文并在下面参考图4至图8论述。该装置包括箱404,箱404具有至少一个半透明底部406,底部406覆盖曝光单元410的至少一部分。曝光单元410包含光源和调制器,可以在控制单元的控制之下利用调制器位置选择性地调节强度,以便在箱底部406上生产具有当前待形成层所需几何形状的曝光区域。替换性地,可以在曝光单元中使用激光器,激光器的光束借助于控制单元所控制的移动镜以期望强度图案连续扫描曝光区域。
与曝光单元410相对地,在箱404的上面设置生产平台412;它通过提升机构(未示出)支撑,从而它在曝光单元410上面的区域中以高度可调节的方式保持在箱底部406上边。类似地,生产平台412可以是透明的或半透明的,以便可以通过生产平台上面的又一曝光单元将光照入,使得至少当在生产平台412的下侧形成第一层时,它也可以从上面被曝光,从而首先在生产平台上固化的层以更高的可靠性粘附到其上。
箱404容纳有高粘性可光聚合性材料420的填充物。填充物的材料水平比意在限定用于位置选择性曝光的层的厚度高得多。为了限定一层可光聚合性材料,采用以下程序。生产平台412通过提升机构以受控方式降低,从而(在第一曝光步骤之前)其下侧浸没在可光聚合性材料420的填充物中,并接近箱底部406,达到所需层厚度Δ(参见图5)精确地留在生产平台412的下侧和箱底部406之间的程度。在该浸没处理中,可光聚合性材料从生产平台412的下侧和箱底部406之间的间隙偏离。在设定了层厚度Δ之后,对该层执行期望的位置选择性层曝光,以便使它固化成期望形状。特别地,当形成第一层时,也可以通过透明或半透明的生产平台412从上面进行曝光,从而特别是在生产平台412的下侧和可光聚合性材料之间的接触区域中进行可靠和完全的固化,因此确保了第一层良好地粘附到生产平台412。在形成了该层之后,借助于提升机构再次升高生产平台。
随后重复这些步骤若干次数,从最后形成的层422的下侧到箱底部406的距离分别设定为期望层厚度Δ,并且接着的下一层以期望方式位置选择性地固化。
在曝光步骤以后升高了生产平台412之后,在曝光区域中存在材料不足,如图6中指示的。这是因为,在固化设定有厚度Δ的层之后,该层的材料被固化并利用生产平台以及已经形成在其上的成形本体的该部分升高。因此,在已经形成的成形本体的该部分的下侧和箱底部406之间缺失的可光聚合性材料必须由来自围绕曝光区域的区域的可光聚合性材料420的填充物填充。然而,由于材料的高粘性,它不会自身流动回到成形本体的该部分的下侧和箱底部之间的曝光区域,从而材料下陷或可能在该处留下“孔”。
为了利用可光聚合性材料补充曝光区域,细长的混合元件432移动通过箱中可光聚合性材料420的填充物。在图4至图8中表示的示范性实施例中,混合元件432包含细长的线,该线在可移动地安装在箱404的侧壁上的两个支撑臂430之间张紧。支撑臂430可以可移动地安装在箱404的侧壁中的引导槽434中,从而通过使支撑臂430在引导槽434中移动,在支撑臂430之间张紧的线432可以相对于箱404平行于箱底部406移动。细长的混合元件432具有尺寸,其移动被相对于箱底部引导,从而细长的混合元件432的上边缘留在曝光区域外的箱中的可光聚合性材料420的填充物的材料的水平以下。如在图8的截面视图中可以看到的,混合元件432在线的整个长度上在箱中的材料水平以下,并且仅支撑臂430突出超出箱中的材料水平。将细长的混合元件布置在箱404中的材料水平以下的效果不是细长的混合元件432在其相对于箱移动通过曝光区域期间大致移动其前面的材料,而是该材料在混合元件432上流动同时执行稍微向上的移动。在图7中示出了混合元件432从图6中示出的位置在例如箭头A所指示的方向上移动到新位置。可以发现,通过对箱中的可光聚合性材料的这类动作,材料被有效地刺激以流动回到生产平台412和曝光单元410之间的消耗材料的曝光区域。
细长的混合元件432相对于箱的移动可以首先利用静定的箱404通过线性驱动器执行,线性驱动器使支撑臂430沿着引导槽434移动,以便实现细长的混合元件432通过生产平台412和曝光单元410之间的曝光区域的所需移动。如图8所示,箱底部406在两侧具有凹部406’。支撑臂430突出,使其下端进入这些凹部406’中。这使得伸长的混合元件432可以保持在箱底部406的高度,而不与支撑臂430的下端通过箱底部406的移动干涉。
DLP的其他替换性方法可以用以备制本发明的一体化芯壳模具。例如,箱可以定位在可旋转平台上。当在连续构建步骤之间从粘性聚合物撤回工件时,箱可以相对于平台和光源旋转,以提新的一层粘性聚合物,其中使构建平台下降以构建连续的层。
本发明可以用于制作具有小于0.64mm的根部特征最小尺寸的涡轮叶片和定子轮叶。如图9所示,叶片900包括翼型件902、平台904、柄部906和具有枞树构造的多叶楔形榫908。优选地,天使翼910,912和914、裙部918以及阻尼器保持凸耳924,926具有小于0.64mm的厚度。大体上,天使翼的厚度范围可以从0.1到0.6mm,更优选地,在0.2到0.5mm的范围内。涡轮叶片或轮叶根部特征的较薄尺寸允许显著减少重量并达成新颖的设计。将理解,图9中示出的叶片的具体设计仅出于图示的目的,不以任何方式限制本发明。应当注意,涡轮叶片和轮叶通常具有根部特征,可以使用本方法制备那些涡轮叶片或轮叶设计,以实现重量减少。
在打印根据本发明的芯壳模具结构之后,可以依据陶瓷芯光聚合物材料的要求来固化和/或烧制芯壳模具。可以将熔化的金属倒入模具中,以形成一定形状且具有一体化芯壳模具所提供的特征的铸造物体。在涡轮叶片或定子轮叶的情况下,优选地,熔化的金属是超合金金属,使用与常规熔模铸造模具一起使用的已知技术来形成单晶超合金涡轮叶片或定子轮叶。
在一方面,本发明涉及包含或结合以相似方式生产的其他芯壳模具的特征的本发明的芯壳模具结构。以下专利申请包括这些各种方面及其使用的公开内容:
美国专利申请No.[],名称为“一体化铸造芯壳结构(INTEGRATED CASTING CORE-SHELL STRUCTURE)”,代理案卷号037216.00036/284976,于2016年12月13日提交;
美国专利申请No.[],名称为“具有浮动顶腔的一体化铸造芯壳结构(INTEGRATEDCASTING CORE-SHELL STRUCTURE WITH FLOATING TIP PLENUM)”,代理案卷号037216.00037/284997,于2016年12月13日提交;
美国专利申请No.[],名称为“用于制作铸造部件的多件式一体化芯壳结构(MULTI-PIECE INTEGRATED CORE-SHELL STRUCTURE FOR MAKING CAST COMPONENT)”,代理案卷号037216.00033/284909,于2016年12月13日提交;
美国专利申请No.[],名称为“制作铸造部件的具有模脚和/或缓冲器的多件式一体化芯壳结构(MULTI-PIECE INTEGRATED CORE-SHELL STRUCTURE WITH STANDOFF AND/ORBUMPER FOR MAKING CAST COMPONENT)”,代理案卷号037216.00042/284909A,于2016年12月13日提交;
美国专利申请No.[],名称为“用于制作铸造部件的具有打印管的一体化铸造芯壳结构(INTEGRATED CASTING CORE SHELL STRUCTURE WITH PRINTED TUBES FOR MAKINGCAST COMPONENT)”,代理案卷号037216.00032/284917,于2016年12月13日提交;
美国专利申请No.[],名称为“用于制作铸造部件的一体化铸造芯壳结构和过滤器(INTEGRATED CASTING CORE-SHELL STRUCTURE AND FILTER FOR MAKING CASTCOMPONENT)”,代理案卷号037216.00039/285021,于2016年12月13日提交;
美国专利申请No.[],名称为“用于制作具有非线性孔的铸造部件的一体化铸造芯壳结构(INTEGRATED CASTING CORE SHELL STRUCTURE FOR MAKING CAST COMPONENT WITHNON-LINEAR HOLES)”,代理案卷号037216.00041/285064,于2016年12月13日提交;
美国专利申请No.[],名称为“用于制作具有位于不可接近位置的冷却孔的铸造部件的一体化铸造芯壳结构(INTEGRATED CASTING CORE SHELL STRUCTURE FOR MAKINGCAST COMPONENT WITH COOLING HOLES IN INACCESSIBLE LOCATIONS)”,代理案卷号037216.00055/285064A,于2016年12月13日提交。
这些申请中的每一个的公开内容以其全部内容并入文中,达到它们公开芯壳模具及制作方法的其他方面的程度,这些可以连同文中公开的芯壳模具一起使用。
该书面描述使用示例来公开本发明,包括优选实施例,还使本领域技术人员能够实践本发明,包括制作和使用任何设备或系统,并施行任何并入的方法。本发明的专利权范围由权利要求书来限定,可以包括本领域技术人员容易想到的其他示例。这种其他示例意在包括于权利要求书的范围内,如果该示例具有与权利要求书的文字语言并无不同的结构元件的话,或者,如果该示例包括与权利要求书的文字语言无实质不同的等效结构元件的话。来自所描述的各种实施例的各方面以及针对每个这种方面的其他已知等效物可以由本领域普通技术人员混合和匹配,以构筑根据本申请原理的其他实施例和技术。
Claims (15)
1.一种制造用于涡轮叶片或轮叶的陶瓷模具的方法,其特征在于,包含:
(a)使工件的固化部分与液态陶瓷光聚合物接触;
(b)通过接触所述液态陶瓷光聚合物的窗口照射所述液态陶瓷光聚合物的邻近于所述固化部分的一部分;
(c)从未固化的所述液态陶瓷光聚合物中去除所述工件;以及
(d)重复步骤(a)-(c),直到形成陶瓷模具为止,所述陶瓷模具包含:
(1)芯部分和壳部分,在所述芯部分和所述壳部分之间具有至少一个空腔,所述空腔适配成在铸造和去除所述陶瓷模具时限定所述涡轮叶片或轮叶的形状,以及
(2)所述空腔,所述空腔限定具有小于0.64mm的最小尺寸的涡轮叶片或轮叶根部件。
2.如权利要求1所述的方法,其特征在于,其中,在步骤(d)之后,所述方法包含步骤(e),所述步骤(e)包含将液态金属倒入所述陶瓷模具中并使所述液态金属凝固以形成铸造部件。
3.如权利要求2所述的方法,其特征在于,其中,在步骤(e)之后,所述方法包含步骤(f),所述步骤(f)包含从所述铸造部件中去除所述陶瓷模具。
4.如权利要求3所述的方法,其特征在于,其中,从所述铸造部件中去除所述陶瓷模具包含机械力和化学浸出的组合。
5.如权利要求1所述的方法,其特征在于,其中,所述涡轮叶片或轮叶根部件具有在0.1和0.6mm的范围内的最小尺寸。
6.如权利要求1所述的方法,其特征在于,其中,所述涡轮叶片或轮叶根部件具有在0.2和0.5mm的范围内的最小尺寸。
7.如权利要求1所述的方法,其特征在于,其中,所述涡轮叶片或轮叶根部件是天使翼、裙部或阻尼器凸耳。
8.一种制备涡轮叶片或轮叶的方法,其特征在于,包含:
(a)将液态金属倒入陶瓷铸造模具中并凝固所述液态金属以形成所述涡轮叶片或轮叶,所述陶瓷铸造模具是根据权利要求1-7中任一项所述的方法制造的陶瓷模具并且包含:
(1)芯部分和壳部分,在所述芯部分和所述壳部分之间具有至少一个空腔,所述空腔适配成在铸造和去除所述陶瓷模具时限定所述涡轮叶片或轮叶的形状,以及
(2)所述空腔,所述空腔限定具有小于0.64mm的最小尺寸的涡轮叶片或轮叶根部件,
(b)通过所述涡轮叶片或轮叶中的孔浸出所述芯部分的至少一部分,从所述涡轮叶片或轮叶中去除所述陶瓷铸造模具。
9.如权利要求8所述的方法,其特征在于,其中,从所述涡轮叶片或轮叶中去除所述陶瓷铸造模具包含机械力和化学浸出的组合。
10.如权利要求8所述的方法,其特征在于,其中,所述涡轮叶片或轮叶根部件具有在0.1和0.6mm的范围内的最小尺寸。
11.如权利要求8所述的方法,其特征在于,其中,所述涡轮叶片或轮叶根部件是天使翼、裙部或阻尼器凸耳。
12.一种陶瓷铸造模具,其特征在于,所述陶瓷铸造模具是根据权利要求1-7中任一项所述的方法制造的陶瓷模具并且包含:
芯部分和壳部分,在所述芯部分和所述壳部分之间具有至少一个空腔,所述空腔适配成在铸造和去除所述陶瓷模具时限定铸造部件的形状,以及
所述空腔,所述空腔限定具有小于0.64mm的最小尺寸的涡轮叶片或轮叶根部件。
13.如权利要求12所述的陶瓷铸造模具,其特征在于,其中,所述涡轮叶片或轮叶根部件具有在0.1和0.6mm的范围内的最小尺寸。
14.如权利要求12所述的陶瓷铸造模具,其特征在于,其中,所述涡轮叶片或轮叶根部件具有在0.2和0.5mm的范围内的最小尺寸。
15.如权利要求12所述的陶瓷铸造模具,其特征在于,其中,所述涡轮叶片或轮叶根部件是天使翼、裙部或阻尼器凸耳。
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US15/377,766 | 2016-12-13 | ||
US15/377,766 US20180161857A1 (en) | 2016-12-13 | 2016-12-13 | Integrated casting core-shell structure for making cast components having thin root components |
PCT/US2017/057874 WO2018111405A1 (en) | 2016-12-13 | 2017-10-23 | Integrated casting core-shell structure for making cast components having thin root components |
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CN110072647B true CN110072647B (zh) | 2022-03-01 |
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US20180161866A1 (en) | 2016-12-13 | 2018-06-14 | General Electric Company | Multi-piece integrated core-shell structure for making cast component |
US10807154B2 (en) * | 2016-12-13 | 2020-10-20 | General Electric Company | Integrated casting core-shell structure for making cast component with cooling holes in inaccessible locations |
US11813669B2 (en) | 2016-12-13 | 2023-11-14 | General Electric Company | Method for making an integrated core-shell structure |
US10610933B2 (en) | 2017-02-22 | 2020-04-07 | General Electric Company | Method of manufacturing turbine airfoil with open tip casting and tip component thereof |
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US10625342B2 (en) | 2017-02-22 | 2020-04-21 | General Electric Company | Method of repairing turbine component |
US10717130B2 (en) | 2017-02-22 | 2020-07-21 | General Electric Company | Method of manufacturing turbine airfoil and tip component thereof |
US10702958B2 (en) | 2017-02-22 | 2020-07-07 | General Electric Company | Method of manufacturing turbine airfoil and tip component thereof using ceramic core with witness feature |
US10391670B2 (en) | 2017-06-28 | 2019-08-27 | General Electric Company | Additively manufactured integrated casting core structure with ceramic shell |
US10974312B2 (en) | 2017-06-28 | 2021-04-13 | General Electric Company | Additively manufactured casting core-shell mold with integrated filter and ceramic shell |
US11192172B2 (en) | 2017-06-28 | 2021-12-07 | General Electric Company | Additively manufactured interlocking casting core structure with ceramic shell |
US10391549B2 (en) | 2017-06-28 | 2019-08-27 | General Electric Company | Additively manufactured casting core-shell hybrid mold and ceramic shell |
US11173542B2 (en) | 2017-06-28 | 2021-11-16 | General Electric Company | Additively manufactured casting core-shell mold and ceramic shell with variable thermal properties |
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CN110072647A (zh) | 2019-07-30 |
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