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公开(公告)号：US07704339B2
公开(公告)日：2010-04-27
申请号：US11654596
申请日：2007-01-18
申请人： Wayne E Voice , Dawei Hu , Xinhua Wu , Michael Loretto
发明人： Wayne E Voice , Dawei Hu , Xinhua Wu , Michael Loretto
摘要： A gamma titanium aluminide alloy consisting of 46 at % aluminium, 8 at % tantalum and the balance titanium plus incidental impurities has an alpha transus temperature Tα between 1310° C. and 1320° C. The gamma titanium aluminide alloy was heated to a temperature T1=1330° C. and was held at T1=1330° C. for 1 hour or longer. The gamma titanium aluminide alloy was air cooled to ambient temperature to allow the massive transformation to go to completion. The gamma titanium aluminide alloy was heated to a temperature T2=1250° C. to 1290° C. and was held at T2 for 4 hours. The gamma titanium aluminide alloy was air cooled to ambient temperature. The gamma titanium aluminide alloy has a fine duplex microstructure comprising differently orientated alpha plates in a massively transformed gamma matrix. The heat treatment reduces quenching stresses and allows larger castings to be grain refined.
摘要翻译： 由46原子％铝，8原子％钽和余量钛加附加杂质组成的γ钛铝化物合金具有在1310℃和1320℃之间的α转变温度Tα。将γ钛铝化合物加热至温度T1 = 1330℃，并在T1 = 1330℃保持1小时以上。 将γ钛化铝合金空气冷却至环境温度以使大规模转化完成。 将γ钛化铝合金加热至T2 = 1250℃至1290℃的温度，并在T2保持4小时。 将γ钛铝化合物空气冷却至环境温度。 γ钛铝化合物具有包含在大量转化的γ基质中的不同取向的α板的精细双相微结构。 热处理降低了淬火应力，并允许更大的铸件被精细化。
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公开(公告)号：US20070175551A1
公开(公告)日：2007-08-02
申请号：US11654596
申请日：2007-01-18
申请人： Wayne E Voice , Dawei Hu , Xinhua Wu , Michael Loretto
发明人： Wayne E Voice , Dawei Hu , Xinhua Wu , Michael Loretto
IPC分类号： C22F1/18
摘要： A gamma titanium aluminide alloy consisting of 46 at % aluminium, 8 at % tantalum and the balance titanium plus incidental impurities has an alpha transus temperature Tα between 1310° C. and 1320° C. The gamma titanium aluminide alloy was heated to a temperature T1=1330° C. and was held at T1=1330° C. for 1 hour or longer. The gamma titanium aluminide alloy was air cooled to ambient temperature to allow the massive transformation to go to completion. The gamma titanium aluminide alloy was heated to a temperature T2=1250° C. to 1290° C. and was held at T2 for 4 hours. The gamma titanium aluminide alloy was air cooled to ambient temperature. The gamma titanium aluminide alloy has a fine duplex microstructure comprising differently orientated alpha plates in a massively transformed gamma matrix. The heat treatment reduces quenching stresses and allows larger castings to be grain refined.
摘要翻译： 由46at％的铝，8at％的钽和余量的钛加附加的杂质组成的γ钛铝化物合金在1310℃和1320℃之间具有α转变温度Tαα3。 铝化物合金被加热到T 1 N 1330℃的温度，并保持在T 1 = 1330℃下1小时或更长时间。 将γ钛化铝合金空气冷却至环境温度以使大规模转化完成。 将γ钛化铝合金加热至温度T T2 = 1250℃至1290℃，并保持在T 2℃4小时。 将γ钛铝化合物空气冷却至环境温度。 γ钛铝化合物具有包含在大量转化的γ基质中的不同取向的α板的精细双相微结构。 热处理降低了淬火应力，并允许更大的铸件被精细化。
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公开(公告)号：US07641847B2
公开(公告)日：2010-01-05
申请号：US11540596
申请日：2006-10-02
申请人： Wayne E Voice , Xinhua Wu , Michael Loretto
发明人： Wayne E Voice , Xinhua Wu , Michael Loretto
CPC分类号： B22D29/003 , B22C9/105 , B22D23/06 , B22F3/15
摘要： A component can be formed by a hot isostatic pressing (HIP) process but it is necessary to reinforce intricate internal structures against collapse and deformation by the hot isostatic pressing process. The present method utilizes a low melting point salt or alloy reinforcement within the structure which can be released when molten through a drain from the internal structure. The reinforcement may be molten as a result of the hot isostatic process or through achieving a temperature with the component which causes the reinforcement to become molten but without damaging the component itself. The remaining parts of the reinforcement may be removed by use of a solvent or simple washing with a corrosive agent to remove any reinforcement debris.
摘要翻译： 组分可以通过热等静压（HIP）工艺形成，但需要通过热等静压技术来加强复杂的内部结构，防止塌陷和变形。 本方法利用在结构内的低熔点盐或合金增强材料，其通过内部结构的排水管熔融时可释放。 作为热等静压过程的结果，或者通过使部件的温度达到一定程度而使加固变得熔融而不会损坏部件本身，加固件可能会熔化。 增强件的其余部分可以通过使用溶剂或使用腐蚀剂的简单洗涤来除去任何增强碎屑。
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公开(公告)号：US09061363B2
公开(公告)日：2015-06-23
申请号：US11478772
申请日：2006-07-03
申请人： Wayne E Voice , Richard C Dewes , Martin R Bache , Stephen J Tuppen , Hong G Lee , David K Aspinwall
发明人： Wayne E Voice , Richard C Dewes , Martin R Bache , Stephen J Tuppen , Hong G Lee , David K Aspinwall
CPC分类号： B23K3/0607 , B23H9/00 , B23K1/0056 , B23K1/008 , B23K1/20
摘要： The present method creates a relatively thin in situ brazing alloy layer upon first and second component edges which are brought together in order to create a component joint. This in situ brazing alloy layer is created by deposition of brazing elements, such as copper or nickel, from an electrical discharge cutting process electrode depletion utilized in order to cut the component edges, and then a subsequent brazing technique creates through interstitial migration between that brazing alloy layer and the underlying material substrate of the components a robust component joint wherein the in situ brazing alloy layer penetrates the respective component cut edge surface to only a limited depth such that the geometric effect is similarly limited, and the properties of the underlying component material structure are maintained.
摘要翻译： 本方法在第一和第二部件边缘上形成相对薄的原位钎焊合金层，这些合金层被聚集在一起以形成部件接头。 这种原位钎焊合金层是通过从用于切割部件边缘的放电切割工艺电极耗尽中的钎焊元件（例如铜或镍）沉积产生的，然后通过该钎焊之间的间隙迁移产生后续的钎焊技术 合金层和组件的下层材料基底是坚固的部件接头，其中原位钎焊合金层仅穿过相应的部件切割边缘表面，仅限于有限的深度，使得几何效应被类似地限制，并且下面的部件材料的性质 维护结构。
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公开(公告)号：US07407622B2
公开(公告)日：2008-08-05
申请号：US11273027
申请日：2005-11-15
申请人： Wayne E Voice , Junfa Mei
发明人： Wayne E Voice , Junfa Mei
CPC分类号： B22F5/04 , B22F5/10 , B22F2998/10 , B22F3/1208 , B22F3/14 , B22F3/15
摘要： A method of manufacturing a fan blade (26) for a gas turbine engine by powder metallurgy comprises the steps of forming a container (52) and placing at least one metal insert (52) at a predetermined position within the container (52) and filling the container (52) with metal powder (60). The at least one metal insert (62) has a predetermined pattern of stop off material (68,70) on at least one surface of the metal insert (64,66). The container (52) is evacuated and then sealed. The container (52) is hot pressed to consolidate the metal powder (60) into a consolidated metal powder preform (72). The container (52) is removed from the consolidated metal powder preform (72). The consolidated metal powder preform (72) is heated and a fluid is supplied to the predetermined pattern of stop off material (68,70) to hot form at least a portion of the consolidated metal powder preform (72) to form the hollow metal fan blade (26).
摘要翻译： 通过粉末冶金制造用于燃气涡轮发动机的风扇叶片（26）的方法包括以下步骤：形成容器（52）并将至少一个金属插入件（52）放置在容器（52）内的预定位置并填充 所述容器（52）具有金属粉末（60）。 所述至少一个金属插入件（62）在所述金属插入件（64,66）的至少一个表面上具有预定图案的止挡材料（68,70）。 将容器（52）抽真空，然后密封。 将容器（52）热压以将金属粉末（60）固结成固结的金属粉末预制件（72）。 从固结的金属粉末预制件（72）中取出容器（52）。 将固结的金属粉末预制件（72）加热并将流体供应到预定图案的停止材料（68,70），以热形成至少一部分固结的金属粉末预制件（72）以形成中空金属风扇 刀片（26）。
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公开(公告)号：US08568197B2
公开(公告)日：2013-10-29
申请号：US12385657
申请日：2009-04-15
申请人： Wayne E Voice , Dragos A Axinte , Ming Chu Kong
发明人： Wayne E Voice , Dragos A Axinte , Ming Chu Kong
IPC分类号： B24B49/00
CPC分类号： B26F3/004 , B24C1/00 , B24C1/045 , Y10T83/0304
摘要： A pocket (6) is machined into the surface of a component (9) by pressurising a fluid (1) and directing a jet (11) of the pressurized fluid (1) at the surface to be machined. Continuous relative movement is provided between the component (9) and the pressurized jet (11) of fluid (1) during machining. Material is removed from the component (9) in a series of layers, whereby the path of the fluid jet (11) in one of the layers is perpendicular to the path of the fluid jet (11) in the subsequent layer. The fluid jet (11) operates continuously until the required amount of material has been removed from the component (9).
摘要翻译： 通过加压流体（1）并将加压流体（1）的射流（11）引导到待加工的表面上，将口袋（6）加工成部件（9）的表面。 在加工过程中，组件（9）和流体（1）的加压喷嘴（11）之间提供连续相对运动。 材料以一系列层从组件（9）中移除，其中一层中的流体射流（11）的路径垂直于随后层中的流体射流（11）的路径。 流体射流（11）连续运行，直到从组件（9）中去除了所需量的材料。
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