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公开(公告)号：US20140010663A1
公开(公告)日：2014-01-09
申请号：US13536156
申请日：2012-06-28
IPC分类号： F01D5/14
CPC分类号： F01D5/147 , C25D9/04 , C25D11/022 , C25D11/026 , C25D11/04 , F01D5/286 , F04D29/324 , F05D2220/36 , F05D2230/312 , F05D2240/303 , F05D2240/307 , F05D2300/173 , F05D2300/174 , Y10T29/49336
摘要： A method of manufacturing a fan blade includes providing a metallic fan blade body, and applying at least a 200 volt potential to the fan blade body in a solution to produce a crystalline oxidation layer. A fan blade for a gas turbine engine includes a metallic fan blade body having a tip with a crystalline oxidation layer. A fan blade for a gas turbine engine includes a metallic fan blade body having a tip with a titanium dioxide layer.
摘要翻译： 制造风扇叶片的方法包括提供金属风扇叶片体，并在溶液中向风扇叶片体施加至少200伏的电位以产生结晶氧化层。 用于燃气涡轮发动机的风扇叶片包括具有具有结晶氧化层的尖端的金属风扇叶片体。 用于燃气涡轮发动机的风扇叶片包括具有具有二氧化钛层的尖端的金属风扇叶片体。
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公开(公告)号：US09157327B2
公开(公告)日：2015-10-13
申请号：US12713867
申请日：2010-02-26
CPC分类号： F01D5/147 , C25D1/00 , F04D29/023 , F04D29/324 , F05D2230/23 , F05D2240/303 , F05D2300/173 , F05D2300/174 , Y02T50/672 , Y02T50/673 , Y10T29/49337
摘要： A fan blade is disclosed comprising a lightweight metallic airfoil portion and a high-strength sheath portion. The airfoil portion has a forward airfoil edge, a first airfoil surface, and a second airfoil surface. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface.
摘要翻译： 公开了一种风扇叶片，其包括轻质金属翼型部分和高强度护套部分。 机翼部分具有前翼面边缘，第一翼面和第二翼面。 护套部分具有鞘头部分，第一护套侧面和第二护套侧面，两个侧面从前鞘部分向翼伸出。 护套部分结合到翼型部分，使得鞘头部分覆盖前翼型边缘，限定叶片前缘。 第一护套侧面覆盖靠近翼型件前缘的第一翼型件表面的一部分，共同限定叶片抽吸表面。 第二护套侧面覆盖靠近翼型件前缘的第二翼型件表面的一部分，共同限定叶片压力表面。
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公开(公告)号：US20130004324A1
公开(公告)日：2013-01-03
申请号：US13173816
申请日：2011-06-30
申请人： James O. Hansen , Joseph Parkos
发明人： James O. Hansen , Joseph Parkos
CPC分类号： C25D1/006 , C25D1/02 , C25D1/20 , F04D29/324 , F05D2240/303
摘要： A method of forming a sheath for a fan airfoil having a leading edge, a trailing edge, a tip, a root, a suction side and a pressure side includes electroplating a nano-structured material to form a sheath with a solid portion to wrap around the leading edge and first and second flanks to secure the solid portion to the pressure side and the suction side of the airfoil.
摘要翻译： 形成具有前缘，后缘，尖端，根部，吸力侧和压力侧的风扇翼型的护套的方法包括电镀纳米结构材料以形成具有固体部分的护套以包裹 前缘和第一和第二侧翼将固体部分固定到翼型的压力侧和吸力侧。
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公开(公告)号：US08168117B2
公开(公告)日：2012-05-01
申请号：US11595141
申请日：2006-11-09
申请人： James O. Hansen
发明人： James O. Hansen
CPC分类号： B22F3/14 , B22F2003/145 , B22F2998/10 , B22F3/02 , B22F3/17 , B22F3/20 , B22F3/18
摘要： A powder metallurgy method includes the steps of forming a member, such as a work piece or an aerospace component, from a titanium alloy powder. The average size of a carbide phase in the titanium alloy powder is controlled in order to control an average size of a carbide phase in the member. In one example, an amount of carbon within the titanium alloy and size of the carbide phase are selected to provide a desirable balance of good hot workability, resisting formation of an alpha-titanium phase within the member and a desired level of fatigue performance.
摘要翻译： 粉末冶金方法包括从钛合金粉末形成诸如工件或航空航天部件的部件的步骤。 控制钛合金粉末中的碳化物相的平均尺寸，以便控制构件中碳化物相的平均尺寸。 在一个实例中，选择钛合金中的碳量和碳化物相的大小，以提供良好的热加工性，抵抗构件内α-钛相的形成和期望的疲劳性能的期望平衡。
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公开(公告)号：US20120051922A1
公开(公告)日：2012-03-01
申请号：US12871087
申请日：2010-08-30
CPC分类号： F01D5/3092 , F01D11/006 , F01D11/12
摘要： A disk made of a first material has a groove in which a blade made of a second material is retained. A strip is placed between the blade and the disk to minimize rubbing damage to the blade and the disk and an insulating material is place between the rub strip and the blade for minimizing damaging responses of the blade to galvanic forces created by rubbing of the first material and the second material.
摘要翻译： 由第一材料制成的盘具有凹槽，在该凹槽中保持由第二材料制成的刀片。 将条带放置在刀片和盘之间以最小化对刀片和盘的摩擦损伤，并且绝缘材料位于摩擦带和刀片之间，以最小化刀片对通过摩擦第一材料而产生的电流的破坏性响应 和第二种材料。
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公开(公告)号：US20080112836A1
公开(公告)日：2008-05-15
申请号：US11595141
申请日：2006-11-09
申请人： James O. Hansen
发明人： James O. Hansen
CPC分类号： B22F3/14 , B22F2003/145 , B22F2998/10 , B22F3/02 , B22F3/17 , B22F3/20 , B22F3/18
摘要： A powder metallurgy method includes the steps of forming a member, such as a work piece or an aerospace component, from a titanium alloy powder. The average size of a carbide phase in the titanium alloy powder is controlled in order to control an average size of a carbide phase in the member. In one example, an amount of carbon within the titanium alloy and size of the carbide phase are selected to provide a desirable balance of good hot workability, resisting formation of an alpha-titanium phase within the member and a desired level of fatigue performance.
摘要翻译： 粉末冶金方法包括从钛合金粉末形成诸如工件或航空航天部件的部件的步骤。 控制钛合金粉末中的碳化物相的平均尺寸，以便控制构件中碳化物相的平均尺寸。 在一个实例中，选择钛合金中的碳量和碳化物相的大小，以提供良好的热加工性，抵抗构件内α-钛相的形成和期望的疲劳性能的期望平衡。
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公开(公告)号：US10260351B2
公开(公告)日：2019-04-16
申请号：US13422541
申请日：2012-03-16
摘要： An airfoil for a gas turbine engine includes a substrate and a sheath providing an edge. A cured adhesive secures the sheath to the substrate. The cured adhesive has a fillet that extends beyond the edge that includes a mechanically worked finished surface. A method of manufacturing the airfoil includes the steps of securing a sheath to a substrate with adhesive, curing the adhesive, and mechanically removing a portion of the adhesive extending beyond the sheath.
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公开(公告)号：US09752441B2
公开(公告)日：2017-09-05
申请号：US13362968
申请日：2012-01-31
申请人： Gregory C. Hildebrand , James O. Hansen , Joseph Parkos, Jr. , Michael A. Weisse , Christopher J. Hertel , Jesse Meyer
发明人： Gregory C. Hildebrand , James O. Hansen , Joseph Parkos, Jr. , Michael A. Weisse , Christopher J. Hertel , Jesse Meyer
CPC分类号： F01D5/20 , F01D11/122 , F05D2220/36 , F05D2240/307
摘要： A rotary blade is provided that includes a root, an airfoil, and a tip insert. The airfoil is attached to the root, and has a suction side surface, a pressure side surface, a leading edge, a trailing edge, a tip, and a slot disposed within the tip. The slot extends in a chordwise direction between the leading edge and trailing edge. The tip insert has a base end and a rub end. The base end of the tip insert is disposed within the slot. The rub end of the tip insert extends radially outward from the airfoil tip.
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公开(公告)号：US20130199934A1
公开(公告)日：2013-08-08
申请号：US13366923
申请日：2012-02-06
申请人： Joseph Parkos, JR. , James O. Hansen , Christopher A. Hertel , Andrew J. Murphy , Ashley P. Phillips , Jay T. Abraham
发明人： Joseph Parkos, JR. , James O. Hansen , Christopher A. Hertel , Andrew J. Murphy , Ashley P. Phillips , Jay T. Abraham
CPC分类号： C25D1/00 , C25D1/02 , F01D5/147 , F04D29/324 , F05D2230/30 , F05D2230/90 , F05D2240/303 , F05D2300/603
摘要： An electroformed sheath for protecting an airfoil includes a sheath body and a mandrel insert is provided. The sheath body includes a leading edge. The sheath body includes a pressure side wall and an opposed suction side wall, which side walls meet at the leading edge and extend away from the leading edge to define a cavity between the side walls. The sheath body includes a head section between the leading edge and the cavity. The mandrel insert is positioned between the pressure side and suction side walls, and includes a generally wedge-shaped geometry. A method for protecting an airfoil includes: 1) securing a mandrel insert to a mandrel; 2) electroplating a sheath body onto the mandrel and the mandrel insert; 3) removing the mandrel from the sheath body so that a sheath cavity is defined within the sheath body; and 4) securing the airfoil within the sheath cavity.
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公开(公告)号：US08449784B2
公开(公告)日：2013-05-28
申请号：US12974427
申请日：2010-12-21
CPC分类号： F01D5/005 , C23F1/44 , F01D5/286 , F04D29/324 , F05D2230/80 , F05D2240/303 , F05D2300/121 , F05D2300/174 , Y02T50/672 , Y10T156/10
摘要： A method for bonding a sheath made of a first metallic material to an airfoil made of a second metallic material includes treating the bonding surface of the airfoil; treating the bonding surface of the sheath; placing an adhesive between the bonding surfaces of the airfoil and the sheath; and pressing the airfoil and sheath together so that the adhesive bonds the sheath to the airfoil.
摘要翻译： 将由第一金属材料制成的护套接合到由第二金属材料制成的翼面的方法包括处理翼型的接合表面; 处理护套的粘合表面; 在所述翼型件和所述护套的接合表面之间放置粘合剂; 并将翼型和护套压在一起，使得粘合剂将护套粘合到翼型件上。
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