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公开(公告)号：US20100098581A1
公开(公告)日：2010-04-22
申请号：US12252754
申请日：2008-10-16
申请人： Dale A. Schenk , John J. Schirra
发明人： Dale A. Schenk , John J. Schirra
IPC分类号： C22C1/02
CPC分类号： C22C1/02 , C22C19/057
摘要： A revert alloy is used in the manufacture of a target alloy having a different composition. The weight percent of the elemental constituents of this first alloy and a second or target alloy are obtained, and the ratio of the percentage by weight of each elemental constituent in the first alloy to the second alloy is determined. The lowest ratio is used to determine the amount of the first alloy that is melted and the necessary elemental constituents that are added to the melt to produce the desired composition of the target alloy. The melt is solidified to produce the target alloy.
摘要翻译： 还原合金用于制造具有不同组成的目标合金。 获得该第一合金和第二合金或目标合金的元素成分的重量百分比，并确定第一合金中的各元素成分与第二合金的重量百分比。 最低比率用于确定熔融的第一合金的量和加入到熔体中以产生目标合金的所需组成的必要元素成分。 将熔体固化以产生目标合金。
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2.发明授权Superalloy optimized for high-temperature performance in high-pressure turbine disks 失效超高温优化用于高压涡轮盘的高温性能公开(公告)号：US06521175B1
公开(公告)日：2003-02-18
申请号：US09021040
申请日：1998-02-09
申请人： David P. Mourer , Eric S. Huron , Kenneth R. Bain , Enrique E. Montero , Paul L. Reynolds , John J. Schirra
发明人： David P. Mourer , Eric S. Huron , Kenneth R. Bain , Enrique E. Montero , Paul L. Reynolds , John J. Schirra
IPC分类号： C22C1905
CPC分类号： C22C19/057 , B22F2998/10 , C22C1/0441 , C22C19/056 , B22F3/17 , B22F9/082 , B22F3/02 , B22F3/20
摘要： A superalloy has a composition of, in weight percent, from about 16.0 percent to about 22.4 percent cobalt, from about 6.6 percent to about 14.3 percent chromium, from about 1.4 percent to about 3.5 percent tantalum, from about 1.9 percent to about 4.0 percent tungsten, from about 1.9 percent to about 3.9 percent molybdenum, from about 0.03 percent to about 0.10 percent zirconium, from about 0.9 percent to about 3.0 percent niobium, from about 2.4 percent to about 4.6 percent titanium, from about 2.6 percent to about 4.8 percent aluminum, from 0 to about 2.5 percent rhenium, from about 0.02 percent to about 0.10 percent carbon, from about 0.02 percent to about 0.10 percent boron, balance nickel and minor amounts of impurities. The superalloy is advantageously utilized in aircraft gas turbine disks.
摘要翻译： 超级合金的重量百分比为约16.0％至约22.4％的钴，约6.6％至约14.3％的铬，约1.4％至约3.5％的钽，约1.9％至约4.0％的钨 ，约1.9％至约3.9％的钼，约0.03％至约0.10％的锆，约0.9％至约3.0％的铌，约2.4％至约4.6％的钛，约2.6％至约4.8％的铝 ，0至约2.5％的铼，约0.02％至约0.10％的碳，约0.02％至约0.10％的硼，余量为镍和少量杂质。 超级合金有利地用于飞机燃气轮机盘。
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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：US08352064B2
公开(公告)日：2013-01-08
申请号：US13079857
申请日：2011-04-05
申请人： Dale A. Schenk , John J. Schirra
发明人： Dale A. Schenk , John J. Schirra
CPC分类号： C22C1/02 , C22C19/057
摘要： A revert alloy is used in the manufacture of a target alloy having a different composition. The weight percent of the elemental constituents of this first alloy and a second or target alloy are obtained, and the ratio of the percentage by weight of each elemental constituent in the first alloy to the second alloy is determined. The lowest ratio is used to determine the amount of the first alloy that is melted and the necessary elemental constituents that are added to the melt to produce the desired composition of the target alloy. The melt is solidified to produce the target alloy.
摘要翻译： 还原合金用于制造具有不同组成的目标合金。 获得该第一合金和第二合金或目标合金的元素成分的重量百分比，并确定第一合金中的各元素成分与第二合金的重量百分比。 最低比率用于确定熔融的第一合金的量和加入到熔体中以产生目标合金的所需组成的必要元素成分。 将熔体固化以产生目标合金。
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公开(公告)号：US20120095590A1
公开(公告)日：2012-04-19
申请号：US13079857
申请日：2011-04-05
申请人： Dale A. Schenk , John J. Schirra
发明人： Dale A. Schenk , John J. Schirra
IPC分类号： G06F19/00
CPC分类号： C22C1/02 , C22C19/057
摘要： A revert alloy is used in the manufacture of a target alloy having a different composition. The weight percent of the elemental constituents of this first alloy and a second or target alloy are obtained, and the ratio of the percentage by weight of each elemental constituent in the first alloy to the second alloy is determined. The lowest ratio is used to determine the amount of the first alloy that is melted and the necessary elemental constituents that are added to the melt to produce the desired composition of the target alloy. The melt is solidified to produce the target alloy.
摘要翻译： 还原合金用于制造具有不同组成的目标合金。 获得该第一合金和第二合金或目标合金的元素成分的重量百分比，并确定第一合金中的各元素成分与第二合金的重量百分比。 最低比率用于确定熔融的第一合金的量和加入到熔体中以产生目标合金的所需组成的必要元素成分。 将熔体固化以产生目标合金。
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公开(公告)号：US5527403A
公开(公告)日：1996-06-18
申请号：US507875
申请日：1995-07-27
CPC分类号： C22F1/10 , C22C19/058
摘要： A method of heat treating articles cast of a superalloy, comprising a nickel-base alloy capable of forming a chromium carbide precipitate, such as INCONEL 939.TM.. The method includes selective heating of the article to cause chromium and carbon nuclei in the lattice of the crystals in the superalloy to go into solution, and selective cooling of the article to cause the formation of discrete chromium carbide nuclei along the grain boundary of the crystals. Additional heating steps may be performed to enhance the size of the chromium carbide nuclei. Articles so treated have improved mechanical properties.
摘要翻译： 一种热处理由超合金制成的制品的方法，该方法包括能够形成碳化铬沉淀物的镍基合金，例如INCONEL 939 TM。 该方法包括选择性加热制品以使超高合金晶体的晶格中的铬和碳原子进入溶液中，并选择性地冷却制品以沿晶体的晶界形成离散的碳化铬核 。 可以进行另外的加热步骤以增加碳化铬核的尺寸。 如此处理的物品具有改善的机械性能。
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公开(公告)号：US09650897B2
公开(公告)日：2017-05-16
申请号：US13529979
申请日：2012-06-21
申请人： James L. Deal , John J. Schirra , Lee Drozdenko , William R. Graves , James O. Hansen , Michael A. Weisse , Thomas J. Watson
发明人： James L. Deal , John J. Schirra , Lee Drozdenko , William R. Graves , James O. Hansen , Michael A. Weisse , Thomas J. Watson
CPC分类号： F01D5/147 , F02K3/06 , F04D29/324 , F05D2220/36 , F05D2240/303 , Y02T50/672
摘要： A fan blade comprises an airfoil portion and a sheath portion. 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. The first metallic material is an aluminum alloy containing between about 0.5 wt % and about 3.0 wt % of lithium.
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公开(公告)号：US08708659B2
公开(公告)日：2014-04-29
申请号：US12890096
申请日：2010-09-24
CPC分类号： F01D5/022 , F01D5/02 , F01D5/28 , F01D5/288 , F01D5/3007 , F01D5/3092 , F01D25/005 , F01D25/007 , F05C2201/90
摘要： A turbine engine apparatus includes a structural component made of a superalloy material. A protective coating is disposed on the structural component and has a composition that consists essentially of up to 30 wt % cobalt, 5-40 wt % chromium, 7.5-35 wt % aluminum, up to 6 wt % tantalum, up to 1.7 wt % molybdenum, up to 3 wt % rhenium, up to 5 wt % tungsten, up to 2 wt % yttrium, 0.05-2 wt % hafnium, 0.05-7 wt % silicon, 0.01-0.1 wt % zirconium, and a balance of nickel.
摘要翻译： 涡轮发动机装置包括由超合金材料制成的结构部件。 保护性涂层设置在结构部件上，并且具有基本上由至多30重量％的钴，5-40重量％的铬，7.5-35重量％的铝，至多6重量％的钽，至多1.7重量％ 钼，至多3重量％的铼，至多5重量％的钨，至多2重量％的钇，0.05-2重量％的铪，0.05-7重量％的硅，0.01-0.1重量％的锆和余量的镍。
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公开(公告)号：US20120076662A1
公开(公告)日：2012-03-29
申请号：US12890096
申请日：2010-09-24
IPC分类号： F01D5/14
CPC分类号： F01D5/022 , F01D5/02 , F01D5/28 , F01D5/288 , F01D5/3007 , F01D5/3092 , F01D25/005 , F01D25/007 , F05C2201/90
摘要： A turbine engine apparatus includes a structural component made of a superalloy material. A protective coating is disposed on the structural component and has a composition that consists essentially of up to 30 wt % cobalt, 5-40 wt % chromium, 7.5-35 wt % aluminum, up to 6 wt % tantalum, up to 1.7 wt % molybdenum, up to 3 wt % rhenium, up to 5 wt % tungsten, up to 2 wt % yttrium, 0.05-2 wt % hafnium, 0.05-7 wt % silicon, 0.01-0.1 wt % zirconium, and a balance of nickel.
摘要翻译： 涡轮发动机装置包括由超合金材料制成的结构部件。 保护性涂层设置在结构部件上，并且具有基本上由至多30重量％的钴，5-40重量％的铬，7.5-35重量％的铝，至多6重量％的钽，至多1.7重量％ 钼，至多3重量％的铼，至多5重量％的钨，至多2重量％的钇，0.05-2重量％的铪，0.05-7重量％的硅，0.01-0.1重量％的锆和余量的镍。
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公开(公告)号：US20110211967A1
公开(公告)日：2011-09-01
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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