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1. 发明授权

US4879095A Rapidly solidified aluminum based silicon containing, alloys for elevated temperature applications 失效
标题翻译：快速固化的铝基硅，适用于高温应用的合金
公开(公告)号：US4879095A
公开(公告)日：1989-11-07
申请号：US39246
申请日：1987-04-17
申请人： Colin M. Adam , Richard L. Bye , Santosh K. Das , David J. Skinner
发明人： Colin M. Adam , Richard L. Bye , Santosh K. Das , David J. Skinner
IPC分类号： B22F9/00 , C22C1/04 , C22C45/08
CPC分类号： C22C1/0416 , B22F9/008 , C22C45/08
摘要： A rapidly solidified aluminum-base alloy consists essentially of the formula Al.sub.bal Fe.sub.a Si.sub.b V.sub.c, wherein "a" ranges from 3.0 to 7.1 atom percent, "b" ranges from 1.0 to 3.0 atom percent, "c" ranges from 0.25 to 1.25 atom percent and the balance is aluminum plus incidental impurities, with the provisos that (i) the ratio (Fe+V): Si ranges from about 2.33:1 to 3:33:1 and (ii) the ratio Fe:V ranges from 11.5:1 to 5:1. The alloy exhibits high strength, ductility and fracture toughness and is especially suited for use in high temperature structural applications such as gas turbine engines, missiles, airframes and landing wheels.
摘要翻译：快速凝固的铝基合金基本上由式AlbalFeaSibVc组成，其中“a”范围为3.0至7.1原子％，“b”为1.0至3.0原子％，“c”为0.25至1.25原子％，余量为是铝加附带杂质，条件是（i）比率（Fe + V）：Si的范围为约2.33:1至3:33:1，（ii）Fe:V的比例为11.5:1至5:1 ：1。该合金具有高强度，延展性和断裂韧性，特别适用于高温结构应用，如燃气轮机，导弹，机身和落地轮。

2. 发明授权

US4878967A Rapidly solidified aluminum based, silicon containing alloys for elevated temperature applications 失效
标题翻译：用于高温应用的快速固化的铝基，含硅合金
公开(公告)号：US4878967A
公开(公告)日：1989-11-07
申请号：US96293
申请日：1987-09-08
申请人： Colin M. Adam , Richard L. Bye , Santosh K. Das , David J. Skinner
发明人： Colin M. Adam , Richard L. Bye , Santosh K. Das , David J. Skinner
IPC分类号： B22F9/00 , C22C1/04 , C22C45/08
CPC分类号： C22C45/08 , B22F9/008 , C22C1/0416
摘要： A rapidly solidified aluminum-base alloy consists essentially of the formula Al.sub.bal Fe.sub.a Si.sub.b X.sub.c wherein X is at least one element selected from the group consisting of Mn,V,Cr,Mo,W,Nb,Ta, "a" ranges from 2.0 to 7.5 atom percent, "b" ranges from 0.5 to 3.0 atom percent, "c" ranges from 0.05 to 3.5 atom percent and the balance is aluminum plus incidental impurities, with the proviso that the ratio {Fe+X}:Si ranges from about 2.0:1 to 5.0:1. The alloy exhibits high strength, ductility and fracture toughness and is especially suited for use in high temperature structural applications such as gas turbine engines, missiles, airframes and landing wheels.
摘要翻译：快速凝固的铝基合金主要由式AlbalFeaSibXc + L组成，其中X是选自Mn，V，Cr，Mo，W，Nb，Ta中的至少一种元素，“a”的范围为2.0至 7.5原子百分比，“b”为0.5-3.0原子百分比，“c”为0.05-3.5原子百分数，余量为铝和附带杂质，条件是{Fe + X}：Si的比例约为 2.0：1至5.0：1。该合金具有高强度，延展性和断裂韧性，特别适用于高温结构应用，如燃气轮机，导弹，机身和落地轮。

3. 发明授权

US4828632A Rapidly solidified aluminum based, silicon containing alloys for elevated temperature applications 失效
标题翻译：用于高温应用的快速固化的铝基，含硅合金
公开(公告)号：US4828632A
公开(公告)日：1989-05-09
申请号：US58494
申请日：1987-06-05
申请人： Colin M. Adam , Richard L. Bye , Santosh K. Das , David J. Skinner
发明人： Colin M. Adam , Richard L. Bye , Santosh K. Das , David J. Skinner
IPC分类号： B22F9/00 , C22C1/04 , C22C45/08
CPC分类号： B22F9/008 , C22C1/0416 , C22C45/08
摘要： A rapidly solidified aluminum-base alloy consists essentially of the formula Al.sub.bal Fe.sub.a Si.sub.b V.sub.c, wherein "a" ranges from 3.0 to 7.1 atom percent, "b" ranges from 1.0 to 3.0 atom percent, "c" ranges from 0.25 to 1.25 atom percent and the balance is aluminum plus incidental impurities, with the provisos that (i) the ratio [Fe+V]:Si ranges from about 2.33:1 to 3:33:1 and (ii) the ratio Fe:V ranges from 11.5:1 to 5:1. The alloy exhibits high strength ductility and fracture toughness and is especially suited for use in high temperature structural applications such as gas turbine engine components, automotive engine components, missiles and airframes.
摘要翻译：快速凝固的铝基合金基本上由式AlbalFeaSibVc组成，其中“a”范围为3.0至7.1原子％，“b”为1.0至3.0原子％，“c”为0.25至1.25原子％，余量为是铝加附带杂质，条件是（i）[Fe + V]：Si的比例为约2.33:1至3:33:1，（ii）Fe:V的比例为11.5:1至5:1 ：1。该合金具有高强度延展性和断裂韧性，特别适用于高温结构应用，如燃气轮机发动机部件，汽车发动机部件，导弹和机身。

4. 发明授权

US5226983A High strength, ductile, low density aluminum alloys and process for making same 失效
标题翻译：高强度，延性，低密度铝合金及其制造方法
公开(公告)号：US5226983A
公开(公告)日：1993-07-13
申请号：US786683
申请日：1991-11-01
申请人： David J. Skinner , Santosh K. Das , Richard L. Bye
发明人： David J. Skinner , Santosh K. Das , Richard L. Bye
IPC分类号： C22C21/00
CPC分类号： C22C21/00
摘要： The present invention provides a process for making high strength, high ductility, low density rapidly solidified aluminum-base alloys, consisting essentially of the formula Al.sub.bal Zr.sub.a Li.sub.b X.sub.c, wherein X is at least one element selected from the group consisting of Cu, Mg, Si, Sc, Ti, U, Hf, Be, Cr, V, Mn, Fe, Co and Ni, "a" ranges from about 0.2-0.6 wt %, "b" ranges from about 2.5-5 wt %, "c" ranges from about 0-5 wt % and the balance is aluminum. The alloy is given multiple aging treatments after being solutionized. The microstructure of the alloy is characterized by the precipitation of a composite phase in the aluminum matrix thereof.
摘要翻译：本发明提供一种制备高强度，高延展性，低密度快速凝固的铝基合金的方法，其基本上由式AlbalZraLibXc组成，其中X是选自Cu，Mg，Si，Sc中的至少一种元素，Ti，U，Hf，Be，Cr，V，Mn，Fe，Co和Ni，“a”为约0.2-0.6重量％，“b”为约2.5-5重量％，“c” 约0-5重量％，余量为铝。溶液后，合金经过多次老化处理。合金的显微组织的特征在于复合相在其铝基体中的沉淀。

5. 发明授权

US6103396A Thick amorphous metal strip having improved ductility and magnetic properties 失效
标题翻译：具有改善的延展性和磁特性的厚的无定形金属条
公开(公告)号：US6103396A
公开(公告)日：2000-08-15
申请号：US920717
申请日：1997-08-29
申请人： Santosh K. Das , Richard L. Bye , Jeng S. Lin
发明人： Santosh K. Das , Richard L. Bye , Jeng S. Lin
IPC分类号： B22D11/06 , C21D8/12 , H01F1/153 , H01F41/02
CPC分类号： H01F41/0226 , B22D11/0611 , C21D8/1211 , H01F1/15341 , C21D2201/03 , Y10T428/12431 , Y10T428/12465 , Y10T428/12493
摘要： An amorphous metal strip having a sheet thickness ranging from about 50 to 75 .mu.m and a sheet width of at least 20 mm is produced by a casting process utilizing a single nozzle orifice and a high thermal conductivity, large diameter wheel as a casting substrate. The strip has a fracture strain of 0.01 or more, a lamination factor of 0.8 or more, and a core loss of less than 0.2 W/kg at 60 Hz and 1.4 T.
摘要翻译：通过使用单个喷嘴孔和高导热率的大直径轮作为流延基底的铸造工艺来生产具有约50至75μm的片材厚度和至少20mm的片材宽度的非晶态金属条。钢带的断裂应变为0.01以上，层压系数为0.8以上，铁心损耗小于0.2W / kg，60Hz，1.4T。

6. 发明授权

US5427173A Induction skull melt spinning of reactive metal alloys 失效
标题翻译：感应颅骨熔融纺丝反应性金属合金
公开(公告)号：US5427173A
公开(公告)日：1995-06-27
申请号：US179837
申请日：1994-01-07
申请人： Santosh K. Das , Richard L. Bye , Alexander Loboysky
发明人： Santosh K. Das , Richard L. Bye , Alexander Loboysky
IPC分类号： B22D11/06 , B22D11/10 , B22D11/18
CPC分类号： B22D11/064
摘要： An apparatus for melting and rapid solidification casting of metal alloys has a crucible for molding a metal charge. The crucible has side walls, a top and a bottom having an orifice therein. Collectively, the side walls, top and bottom define an interior of the crucible. A portion of the dimensions of the side walls of the side walls and bottom is divided by longitudinal slits into at least two segments. A nozzle is disposed partially within the crucible and extends through the orifice. The nozzle has a first end in communication with the interior of tune crucible. A second end of the nozzle has a nozzle orifice therein for defining a stream of molten metal alloy. A cooling mechanism cools the top, side walls and bottom of the crucible. The apparatus has mechanisms for inducing alternating electrical currents within the metal charge and within the nozzle, and for establishing and maintaining pressure within the interior of the crucible. A positioning mechanism positions the crucible and nozzle means relative to a quenching mechanisms that includes a rapidly moving chill substrate. The crucible, nozzle and quenching mechanism are housed within an enclosure that provides there within a controlled atmosphere having positive or negative pressure.
摘要翻译：金属合金的熔融和快速凝固铸造的装置具有用于模制金属电荷的坩埚。坩埚具有侧壁，顶部和底部具有孔口。集体地，侧壁，顶部和底部限定了坩埚的内部。侧壁和底部的侧壁的尺寸的一部分被纵向狭缝分成至少两个部分。喷嘴部分地设置在坩埚内并延伸穿过孔口。喷嘴具有与调节坩埚内部连通的第一端。喷嘴的第二端在其中具有用于限定熔融金属合金流的喷嘴孔。冷却机构冷却坩埚的顶部，侧壁和底部。该装置具有用于在金属电荷和喷嘴内引起交流电流的机构，并且用于在坩埚内部建立并保持压力。定位机构相对于包括快速移动的冷却基板的淬火机构来定位坩埚和喷嘴装置。坩埚，喷嘴和淬火机构容纳在一个外壳内，在一个受控气氛中提供正或负压力。

7. 发明授权

US07291231B2 Copper-nickel-silicon two phase quench substrate 有权
标题翻译：铜镍硅两相淬火基板
公开(公告)号：US07291231B2
公开(公告)日：2007-11-06
申请号：US10644220
申请日：2003-08-21
申请人： Shinya Myojin , Richard L. Bye , Nicholes J. DeCristofaro , David W. Millure , Gary A. Schuster
发明人： Shinya Myojin , Richard L. Bye , Nicholes J. DeCristofaro , David W. Millure , Gary A. Schuster
IPC分类号： C22C9/06
CPC分类号： C22F1/00 , B22D11/0611 , B22D11/0651 , C22C9/06 , C22F1/08 , Y10T428/12882
摘要： A copper-nickel-silicon quench substrate rapidly solidifies molten alloy into microcrystalline or amorphous strip. The substrate is composed of a thermally conducting alloy. It has a two-phase microstructure with copper rich regions surrounded by a discontinuous network of nickel silicide phases. The microstructure is substantially homogeneous. Casting of strip is accomplished with minimal surface degradation as a function of casting time. The quantity of material cast during each run is improved without the toxicity encountered with copper-beryllium substrates.
摘要翻译：铜镍硅淬火基板将熔融合金快速固化成微晶或非晶带。基板由导热合金构成。它具有两相微结构，其铜富集区由镍硅化物相的不连续网络围绕。微结构基本上是均匀的。带材的铸造是以最小的表面退化作为铸造时间的函数来实现的。在每次运行期间铸造的材料的数量得到改善，而没有铜 - 铍底物遇到的毒性。

8. 发明申请

US20110293963A1 COATINGS, TURBINE ENGINE COMPONENTS, AND METHODS FOR COATING TURBINE ENGINE COMPONENTS 审中-公开
标题翻译：涂层，涡轮发动机部件和涂装涡轮发动机部件的方法
公开(公告)号：US20110293963A1
公开(公告)日：2011-12-01
申请号：US12787215
申请日：2010-05-25
申请人： Yiping Hu , Richard L. Bye , Paul Mravcak
发明人： Yiping Hu , Richard L. Bye , Paul Mravcak
IPC分类号： B32B15/01 , B23K31/02 , C23C14/14 , C22C19/03 , C23C14/34
CPC分类号： C23C14/025 , B23K26/32 , B23K26/34 , B23K26/342 , B23K35/0244 , B23K35/3033 , B23K35/365 , B23K2101/001 , B23K2103/26 , B32B15/01 , C22C19/03 , C23C14/16 , C23C14/5806 , F01D5/288 , F05D2230/313 , Y02T50/67 , Y02T50/673 , Y02T50/6765 , Y10T428/12944
摘要： A coating is disclosed that consists essentially of, by weight, about 27.5% to about 31.5% aluminum, about 0.20% to about 0.60% hafnium, about 0.08% to about 0.30% zirconium, about 0.005% to about 0.100% of two or more reactive elements selected from a group consisting of yttrium, lanthanum, and cerium, and a balance of nickel. Turbine engine components including the coating and methods of applying the coating on such components are also disclosed.
摘要翻译：公开了一种涂层，其基本上由以重量计约27.5％至约31.5％的铝，约0.20％至约0.60％的铪，约0.08％至约0.30％的锆，约0.005％至约0.100％的两种或更多种选自钇，镧和铈的反应性元素，余量为镍。还公开了包括涂层的涡轮发动机部件以及在这些部件上施加涂层的方法。

9. 发明申请

US20120048912A1 METHODS FOR THE FORMATION OF MCrAlY COATINGS ON GAS TURBINE ENGINE COMPONENTS 审中-公开
标题翻译：在气体涡轮发动机组件上形成MCrAlY涂层的方法
公开(公告)号：US20120048912A1
公开(公告)日：2012-03-01
申请号：US12869464
申请日：2010-08-26
申请人： Yiping Hu , Richard L. Bye
发明人： Yiping Hu , Richard L. Bye
IPC分类号： B23K31/02
CPC分类号： F01D5/288 , F01D5/005 , F05D2230/31 , F05D2230/80 , F05D2230/90
摘要： Embodiments of a method for forming an MCrAlY coating on a gas turbine engine component are provided, as are embodiments of a method for repairing a structurally-damaged region of a gas turbine engine component utilizing an MCrAlY material. In one embodiment, the method includes the step of preparing an MCrAlY slurry containing an MCrAlY powder, a low melting point powder, a binder, and a dilutant. After application over the gas turbine engine component, the MCrAlY slurry is heated to a predetermined temperature that exceeds the melting point of the low melting point powder to form an MCrAlY coating on the gas turbine engine component. The MCrAlY powder may have any one of a number of different compositions.
摘要翻译：提供了一种用于在燃气涡轮发动机部件上形成MCrAlY涂层的方法的实施例，其中使用MCrAlY材料修复燃气涡轮发动机部件的结构受损区域的方法的实施例。在一个实施方案中，该方法包括制备含有MCrAlY粉末，低熔点粉末，粘合剂和稀释剂的MCrAlY浆料的步骤。在施加在燃气涡轮发动机部件上之后，将MCrAlY浆料加热到超过低熔点粉末的熔点的预定温度，以在燃气涡轮发动机部件上形成MCrAlY涂层。 MCrAlY粉末可以具有多种不同组合物中的任何一种。

10. 发明申请

US20100001130A1 Hybrid aircraft wheel having metal and composite portions 有权
标题翻译：混合飞轮具有金属和复合部分
公开(公告)号：US20100001130A1
公开(公告)日：2010-01-07
申请号：US12216542
申请日：2008-07-07
申请人： Douglas J. Steinke , Allen H. Simpson , James F. Stevenson , Manuel G. Koucouthakis , Richard L. Bye
发明人： Douglas J. Steinke , Allen H. Simpson , James F. Stevenson , Manuel G. Koucouthakis , Richard L. Bye
IPC分类号： B64C25/34 , B21D53/26
CPC分类号： B64C25/36 , B29C70/86 , B29L2031/32 , B60B5/02 , Y10T29/49481
摘要： An aircraft wheel (14) comprises a metal support structure (30) having a first annular ring (31) and a second annular ring (32) connected via at least one connecting element (37); and a fiber-enforced, molded-composite body. The metal support structure (30) is at least partially embedded in the composite body to form a first aircraft wheel section (20, 22) having a rim flange (16a, 16b) for forming a seal with a tire.
摘要翻译：飞机轮（14）包括具有通过至少一个连接元件（37）连接的第一环形圈（31）和第二环形环（32）的金属支撑结构（30）。和纤维强化的成型复合体。金属支撑结构（30）至少部分地嵌入在复合体中以形成具有用于与轮胎形成密封的边缘凸缘（16a，16b）的第一飞行器轮部分（20,22）。

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