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1. 发明授权

US08471168B2 Methods of treating metal articles and articles made therefrom 有权
标题翻译：处理由其制成的金属制品和制品的方法
公开(公告)号：US08471168B2
公开(公告)日：2013-06-25
申请号：US12142242
申请日：2008-06-19
申请人： Swami Ganesh
发明人： Swami Ganesh
IPC分类号： B23K26/34
CPC分类号： B23K9/04 , B23K10/027 , B23K26/32 , B23K26/34 , B23K26/356 , B23K35/001 , B23K35/004 , B23K35/3046 , B23K2101/001 , B23K2103/50 , B23P6/005 , B23P9/02 , C21D7/06 , C21D7/08 , C21D9/0068 , C21D9/50 , C21D10/005 , C21D2251/04
摘要： A method for treating a metal article can comprise: fusion welding a cladding onto an article comprising a surface and a compressive case depth processing the cladding. An average compression case depth, as measured from the cladding outer surface, can be greater than the cladding thickness. Also included herein are articles made from this method.
摘要翻译：用于处理金属制品的方法可以包括：将包层熔融焊接到包括表面的制品上，并且加工包层的压缩壳体深度。从包层外表面测量的平均压缩箱深度可以大于包层厚度。本文还包括由此方法制成的文章。

2. 发明申请

US20110192205A1 PEENING PROCESS FOR ENHANCING SURFACE FINISH OF A COMPONENT 有权
标题翻译：用于增强部件表面处理的珩磨工艺
公开(公告)号：US20110192205A1
公开(公告)日：2011-08-11
申请号：US12702534
申请日：2010-02-09
申请人： Swami Ganesh
发明人： Swami Ganesh
IPC分类号： C21D7/06
CPC分类号： B24C1/10 , B24C7/0007 , C21D7/06 , Y10T29/479
摘要： A process for treating a surface of a component to improve its surface finish and induce residual compresses stresses in a near-surface region of the component. The process entails performing a first peening operation to form residual compressive stress layers in the near-surface region of the component, and then performing at least a second peening operation to cause surface smoothing of the surface of the component while retaining residual compressive stresses in the near-surface region of the component. The first peening operation comprises wet glass bead peening at a first intensity with a first glass bead media, and the second peening operation comprises wet glass bead peening at a second intensity with a second glass bead media, wherein the second intensity is lower than the first intensity and the second glass bead media is smaller than the first glass bead media.
摘要翻译：用于处理部件的表面以改善其表面光洁度并在部件的近表面区域中引起残余压缩应力的方法。该过程需要执行第一喷丸操作以在部件的近表面区域中形成残余的压应力层，然后进行至少一次第二喷丸操作以引起部件表面的表面平滑化，同时保留部件中的残余压应力组件的近表面区域。第一个喷丸操作包括以第一强度的湿玻璃珠喷丸处理与第一玻璃珠粒介质，并且第二喷丸操作包括用第二玻璃珠介质以第二强度的湿玻璃珠喷丸处理，其中第二强度低于第一强度强度和第二玻璃珠介质小于第一玻璃珠介质。

3. 发明授权

US5161950A Dual alloy turbine disk 失效
标题翻译：双合金涡旋盘
公开(公告)号：US5161950A
公开(公告)日：1992-11-10
申请号：US417096
申请日：1989-10-04
申请人： Daniel D. Krueger , Bruce P. Bardes , Richard G. Menzies , Swami Ganesh , Jeffrey F. Wessels , Sulekh C. Jain , Michael E. Sauby , Keh-Minn Chang
发明人： Daniel D. Krueger , Bruce P. Bardes , Richard G. Menzies , Swami Ganesh , Jeffrey F. Wessels , Sulekh C. Jain , Michael E. Sauby , Keh-Minn Chang
IPC分类号： F01D5/02 , B23K20/22 , C22C19/03 , C22C19/05 , C22F1/00 , C22F1/10 , F01D5/28
CPC分类号： B23K20/22 , F01D5/28 , F05D2300/603 , Y02T50/672 , Y10T29/49316
摘要： A dual alloy disk made from a rim alloy having high stress rupture and creep resistance as well as good hold time fatigue crack resistance and a hub alloy having high tensile strength and good low cycle fatigue crack resistance is described. The dual alloy disk is designed for use as a disk in gas turbine engines operating as high as 1500.degree. F. The hub and rim are joined together at a substantially defect-free joint to form a turbine disk having improved properties in both the hub and rim regions.
摘要翻译：描述了由具有高应力断裂和抗蠕变性以及良好的保持时间疲劳抗开裂性的边缘合金制成的双合金圆盘，以及具有高拉伸强度和良好的低循环疲劳抗开裂性的轮毂合金。双合金盘被设计用作高达1500°F的燃气涡轮发动机中的盘。轮毂和轮辋在基本上无缺陷的接头处连接在一起以形成具有改进的轮毂和轮毂性能的涡轮盘边缘区域。

4. 发明申请

US20100061863A1 AIRFOIL AND METHODS OF LASER SHOCK PEENING OF AIRFOIL 审中-公开
标题翻译：空气动力学和空气动力学碰撞的方法
公开(公告)号：US20100061863A1
公开(公告)日：2010-03-11
申请号：US12208369
申请日：2008-09-11
申请人： John McConnell Delvaux , Swami Ganesh
发明人： John McConnell Delvaux , Swami Ganesh
IPC分类号： F01D5/28 , C21D10/00 , F01D5/14
CPC分类号： F01D5/286 , B23K26/0006 , B23K26/356 , B23K2103/02 , B23K2103/08 , B23K2103/14 , B23K2103/26 , C21D10/005
摘要： A blade for rotating equipment. The blade includes a root and an airfoil with a leading edge attached to the root. The blade may include a laser shot peened root patch extending along the leading edge and the root.
摘要翻译：用于旋转设备的刀片。叶片包括根部和具有连接到根部的前缘的翼型件。刀片可以包括沿前缘和根部延伸的激光喷丸硬化的根部补片。

5. 发明申请

US20090060735A1 TURBINE ROTOR APPARATUS AND SYSTEM 审中-公开
标题翻译：涡轮转子装置和系统
公开(公告)号：US20090060735A1
公开(公告)日：2009-03-05
申请号：US11848645
申请日：2007-08-31
申请人： Swami Ganesh , Robin Carl Schwant , Lyle B. Spiegel
发明人： Swami Ganesh , Robin Carl Schwant , Lyle B. Spiegel
IPC分类号： F01D1/00 , F01D5/02 , F04D3/00
CPC分类号： F01D5/063 , F05D2230/233 , F05D2230/235 , Y02T50/671
摘要： A segmented turbine rotor is disclosed. The segmented turbine rotor has a plurality of rows of a plurality of turbine blades. At least one rotor segment of a plurality of rotor segments of the segmented turbine rotor includes a ring disposed circumferentially about and having an axis substantially parallel to a central axis of the rotor, the ring defining a cavity disposed at a center thereof and having an outer surface supporting at least one row of the plurality of rows of turbine blades.
摘要翻译：公开了一种分段涡轮转子。分段涡轮转子具有多排多个涡轮叶片。分段式涡轮机转子的多个转子段中的至少一个转子段包括围绕并且具有基本上平行于转子的中心轴线的轴线设置的环，该环限定了设置在其中心处的空腔，表面支撑多排涡轮叶片的至少一排。

6. 发明授权

US5571345A Thermomechanical processing method for achieving coarse grains in a superalloy article 失效
标题翻译：在超级合金制品中实现粗晶的热机械加工方法
公开(公告)号：US5571345A
公开(公告)日：1996-11-05
申请号：US268696
申请日：1994-06-30
申请人： Swami Ganesh , Eric S. Huron
发明人： Swami Ganesh , Eric S. Huron
IPC分类号： B22F3/24 , C22F1/10
CPC分类号： B22F3/24 , C22F1/10 , Y10S148/902
摘要： A method is provided for obtaining a uniform grain size on the order of about ASTM 5 or coarser in at least a portion of an article formed from a .gamma.' precipitation strengthened nickel-base superalloy. The method comprises forming an article by: providing a billet, preheating the billet above 2000.degree. F. for at least 0.5 hours, working at least a portion to near-net shape at working conditions including a first strain rate of less than about 0.01 per second and at a subsolvus temperature at or near the recrystallization temperature, supersolvus heating to form a grain size in the portion of at least 5 ASTM, and cooling to reprecipitate .gamma.' within the article. The method can be utilized to form a .gamma.' precipitation strengthened nickel-base superalloy article whose grain size varies uniformly between portions thereof, so as to yield a desirable microstructure and property gradient in the article in accordance with the in-service temperature and stress-state gradient experienced by the article. The method is particularly useful for the making of relatively large components such as turbine disks used in gas turbine engines, which are subjected to stress and temperature conditions that vary radially from the center of the disk to its outer rim.
摘要翻译：提供了一种方法，用于在由γ'沉淀强化的镍基超级合金形成的制品的至少一部分中获得大约为ASTM 5或更粗的大小的均匀晶粒尺寸。该方法包括通过以下步骤来形成物品：提供坯料，将坯料预热到2000°F以上至少0.5小时，在包括第一应变速率小于约0.01的工作条件下工作至少一部分至接近净形状第二和在重结晶温度或接近重结晶温度的亚沉积温度下，加热至少5 ASTM部分中的晶粒尺寸，并冷却以在制品内再沉淀γ'。该方法可用于形成晶粒尺寸在其各部分之间均匀变化的γ'沉淀强化镍基超合金制品，从而根据使用中的温度和应力 - 压力产生所需的微结构和性能梯度，文章经历的状态渐变。该方法特别适用于制造相对较大的部件，例如在燃气涡轮发动机中使用的涡轮盘，其经受从盘的中心到其外缘径向变化的应力和温度条件。

7. 发明授权

US09291062B2 Methods of forming blades and method for rendering a blade resistant to erosion 有权
标题翻译：形成刀片的方法和使刀片耐腐蚀的方法
公开(公告)号：US09291062B2
公开(公告)日：2016-03-22
申请号：US13607046
申请日：2012-09-07
申请人： Michael Lewis Jones , Swami Ganesh
发明人： Michael Lewis Jones , Swami Ganesh
IPC分类号： B05D3/12 , B23K31/02 , B05D1/36 , F01D5/28
CPC分类号： F01D5/288 , B23K26/342 , B23K26/702 , B23K2101/001 , F01D5/286 , F05D2220/31
摘要： Methods of forming a blade and rendering a blade resistant to erosion includes positioning a backing plate(s) or elongated backing plate(s) adjacent at least one side of a forward face of a leading edge surface of the blade. The methods include depositing an erosion resistant material in a plurality of layers by fusion bonding the erosion resistant material to the forward face of the leading edge surface of the blade. The backing plates providing a template or guide for depositing the plurality of layers of erosion resistant material. The plurality of layers of erosion resistant material form an erosion shield and a leading edge of the blade. Methods include removing the backing plate.
摘要翻译：形成叶片并且使得抗侵蚀的刀片的方法包括在叶片的前缘表面的前面的至少一侧附近定位背板或细长背板。所述方法包括通过将抗侵蚀材料熔融粘合到叶片的前缘表面的前表面而将抗侵蚀材料沉积在多个层中。背板提供用于沉积多层抗侵蚀材料的模板或引导件。多层抗侵蚀材料形成侵蚀屏蔽和叶片的前缘。方法包括移除背板。

8. 发明授权

US08414267B2 Multiple alloy turbine rotor section, welded turbine rotor incorporating the same and methods of their manufacture 有权
标题翻译：多合金涡轮转子部分，包含其的焊接涡轮转子及其制造方法
公开(公告)号：US08414267B2
公开(公告)日：2013-04-09
申请号：US12570566
申请日：2009-09-30
申请人： Swami Ganesh , Robin Carl Schwant
发明人： Swami Ganesh , Robin Carl Schwant
IPC分类号： F01D5/02
CPC分类号： F01D5/063 , B21J5/002 , B21K1/28 , B22F5/009 , B22F7/062 , B23K35/0261 , B23K2101/001 , B23P15/006 , C22C19/00 , F01D5/28 , F05D2230/23 , F05D2230/25 , Y02E10/721 , Y10T29/49316 , Y10T29/4932
摘要： A method of making a multiple alloy, multi-section welded turbine rotor includes providing a forged multiple alloy rotor section having an integral microstructure, the rotor section comprising a first alloy having a first alloy composition and second alloy having a second alloy composition, a first weld face comprising the first alloy on a first end and an a second weld face comprising the second alloy on an opposed second end. The method also includes providing a first rotor section comprising the first alloy composition and a second rotor section comprising the second alloy composition. The method also includes welding the first rotor section to the first weld face and welding the second rotor section to the second weld face.
摘要翻译：制造多合金，多段焊接涡轮转子的方法包括提供具有整体微结构的锻造多合金转子部分，所述转子部分包括具有第一合金组成的第一合金和具有第二合金组成的第二合金，第一合金在第一端上包括第一合金的焊接面和在相对的第二端上包括第二合金的第二焊接面。该方法还包括提供包括第一合金组合物的第一转子部分和包括第二合金组合物的第二转子部分。该方法还包括将第一转子部分焊接到第一焊接面并将第二转子部分焊接到第二焊接面。

9. 发明申请

US20130004317A1 TURBINE DISK PREFORM, WELDED TURBINE ROTOR MADE THEREWITH AND METHODS OF MAKING THE SAME 有权
标题翻译：涡轮盘预制件，焊接式涡轮转子及其制造方法
公开(公告)号：US20130004317A1
公开(公告)日：2013-01-03
申请号：US13172943
申请日：2011-06-30
申请人： Swami Ganesh , Steven Louis Breitenbach , Robin Carl Schwant
发明人： Swami Ganesh , Steven Louis Breitenbach , Robin Carl Schwant
IPC分类号： F01D5/02 , C21D7/08 , B23P15/04 , C21D7/06
CPC分类号： F01D5/063 , B23K2101/001 , Y10T29/479 , Y10T29/49321 , Y10T29/49325
摘要： A method of making a turbine rotor is disclosed. The method includes forming a last stage disk preform having a disk axis, the preform having a rotor face and an opposed shaft face, the rotor face having a circumferential, axially-extending rotor rib protruding therefrom, the shaft face having a circumferential, axially-extending shaft rib protruding therefrom, the disk preform comprising a disk preform material. The method also includes joining the rotor rib to a rotor preform to form a rotor joint, the rotor preform comprising a rotor preform material. The method further includes joining the shaft rib to a shaft to form a shaft joint, the shaft comprising a shaft material, wherein the disk preform material is different than the rotor preform material and the shaft material.
摘要翻译：公开了一种制造涡轮转子的方法。该方法包括形成具有盘轴的最后级盘预制件，预型件具有转子面和相对的轴面，转子面具有从其突出的圆周方向轴向延伸的转子肋，该轴面具有周向的，延伸的轴肋从其突出，盘预制件包括盘预制件材料。该方法还包括将转子肋连接到转子预制件以形成转子接头，转子预制件包括转子预制件材料。该方法还包括将轴肋连接到轴以形成轴接头，该轴包括轴材料，其中盘预制件材料与转子预制件材料和轴材料不同。

10. 发明申请

US20090314758A1 Methods of Treating Metal Articles and Articles Made Therefrom 有权
标题翻译：处理金属制品和制品的方法
公开(公告)号：US20090314758A1
公开(公告)日：2009-12-24
申请号：US12142242
申请日：2008-06-19
申请人： Swami Ganesh
发明人： Swami Ganesh
IPC分类号： B23K9/00
CPC分类号： B23K9/04 , B23K10/027 , B23K26/32 , B23K26/34 , B23K26/356 , B23K35/001 , B23K35/004 , B23K35/3046 , B23K2101/001 , B23K2103/50 , B23P6/005 , B23P9/02 , C21D7/06 , C21D7/08 , C21D9/0068 , C21D9/50 , C21D10/005 , C21D2251/04
摘要： A method for treating a metal article can comprise: fusion welding a cladding onto an article comprising a surface and a compressive case depth processing the cladding. An average compression case depth, as measured from the cladding outer surface, can be greater than the cladding thickness. Also included herein are articles made from this method.
摘要翻译：用于处理金属制品的方法可以包括：将包层熔融焊接到包括表面的制品上，并且加工包层的压缩壳体深度。从包层外表面测量的平均压缩箱深度可以大于包层厚度。本文还包括由此方法制成的文章。

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