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1. 发明授权

US5732468A Method for bonding a turbine engine vane segment 失效
标题翻译：涡轮发动机叶片段接合方法
公开(公告)号：US5732468A
公开(公告)日：1998-03-31
申请号：US759545
申请日：1996-12-05
申请人： Ronald L. Galley , Stephen J. Ferrigno , L. Timothy Rasch
发明人： Ronald L. Galley , Stephen J. Ferrigno , L. Timothy Rasch
IPC分类号： B23K1/00 , F01D9/04 , B23P15/00
CPC分类号： B23K1/0018 , F01D9/044 , Y10T29/49318 , Y10T29/49323
摘要： An airfoil and a band or platform member of a vane segment, such as of a turbine engine, are bonded at a non-linear clearance slot formed between a shelf in the band and an end and edge of the airfoil. A reservoir bead of a bonding alloy slurry is deposited at one slot opening, a metallic powder is packed into the slot, and another reservoir bead is applied at a slot second opening substantially to close the slot and entrap the powder therein. Then the reservoir beads and powder are heated to flow material of the beads into the clearance slot. This bonds the airfoil and band securely at a deep pocket or blind slot.
摘要翻译：诸如涡轮发动机的叶片段的翼型和带或平台构件在形成在带中的搁架和翼型的端部和边缘之间的非线性间隙处接合。在一个开口处沉积粘结合金浆料的储存珠，将金属粉末填充到槽中，并且另一个储存珠沿施加在槽第二开口处，基本上封闭狭槽并将粉末截留在其中。然后加热储存器珠和粉末以将珠的材料流入间隙槽。这样就可以将翼型和带牢固地绑在深口袋或盲槽上。

2. 发明授权

US5675892A Laser shock peening for gas turbine engine vane repair 失效
标题翻译：用于燃气轮机发动机叶片修复的激光冲击喷丸
公开(公告)号：US5675892A
公开(公告)日：1997-10-14
申请号：US668642
申请日：1996-06-20
申请人： Seetharamaiah Mannava , Stephen J. Ferrigno
发明人： Seetharamaiah Mannava , Stephen J. Ferrigno
IPC分类号： B23P6/00 , C21D7/06 , C21D10/00 , F01D5/00 , B23P15/00
CPC分类号： B23P6/007 , C21D10/005 , F01D5/005 , C21D10/00 , C21D7/06 , Y10S148/903 , Y10T29/49318 , Y10T29/49336
摘要： A wide gap braze repair, particularly for a gas turbine engine vane or a component in the hot section of the engine. The repair is characterized by a braze filled void in a damaged area of the component, a laser shock peened surface over the repaired area of the braze filled void, and a region of deep compressive residual stresses imparted by laser shock peening (LSP) extending from the laser shock peened surface into the repair.
摘要翻译：特别是用于燃气涡轮发动机叶片或发动机热段中的部件的宽间隙钎焊修复。该修复的特征在于部件的损坏区域中的钎焊填充空隙，在钎焊填充空隙的修复区域上的激光冲击硬化表面以及由激光冲击喷丸（LSP）延伸的深度压缩残余应力的区域激光冲击喷丸表面进行修补。

3. 发明授权

US4830934A Alloy powder mixture for treating alloys 失效
标题翻译：用于处理合金的合金粉末混合物
公开(公告)号：US4830934A
公开(公告)日：1989-05-16
申请号：US56175
申请日：1987-06-01
申请人： Stephen J. Ferrigno , Mark Somerville , William R. Young
发明人： Stephen J. Ferrigno , Mark Somerville , William R. Young
IPC分类号： B23K1/00 , B22F1/00 , B22F7/08 , B23K35/30 , C22C19/05
CPC分类号： B23K35/304 , B23K35/30 , Y10T29/49746 , Y10T428/12861 , Y10T428/12931 , Y10T428/12944
摘要： An improved mixture of alloy powders is provied for use in treating a preselected article alloy, for example, to repair or join multiple components of the article. The mixture has at least three distinct groups of alloy powders which together define a mixture composition range, with each alloy powder of the groups characterized by a composition and melting range different from the others and from the article alloy. In a preferred form, the mixture composition range comprises, by weight, 15-30% Cr, 1.5-6% W, 0.4-4% Al, 1-11% Ti, 1-6% Ta, up to 1.5% B, up to 0.5% Si, up to 0.2% Zr, up to 3% Mo, up to 0.3% Hf, up to 6% Cb, up to 2% Re, with the balance selected from Co and Ni along with incidental impurities.

4. 发明授权

US5584663A Environmentally-resistant turbine blade tip 失效
标题翻译：耐环境涡轮叶片尖端
公开(公告)号：US5584663A
公开(公告)日：1996-12-17
申请号：US551689
申请日：1995-11-01
申请人： Jerry D. Schell , Howard J. Farr , Thomas J. Kelley , Paul J. E. Monson , Stephen J. Ferrigno
发明人： Jerry D. Schell , Howard J. Farr , Thomas J. Kelley , Paul J. E. Monson , Stephen J. Ferrigno
IPC分类号： C22C1/04 , C22C19/05 , C23C24/10 , F01D5/20 , F01D5/28
CPC分类号： B23K26/0853 , C22C1/0433 , C22C19/058 , C23C24/103 , F01D5/20 , Y10T428/12944
摘要： A family of environmentally-resistant alloys is provided which are suitable for forming a blade tip for a turbine blade of a gas turbine engine. The blade tip alloys preferably have a chemical composition of, in weight percent, about 14 to about 18 percent chromium, about 6.45 to about 6.95 percent aluminum, about 9.75 to about 11.45 percent cobalt, about 5.95 to about 6.55 percent tantalum, about 1.85 to about 2.35 percent rhenium, about 0.05 to about 1.75 percent hafnium, about 0.006 to about 0.03 percent zirconium, about 0.02 to about 0.11 percent carbon, up to about 1.1 percent silicon, up to about percent 0.01 percent boron, with the balance being nickel and typical impurities.
摘要翻译：提供了一系列耐环境合金，其适用于形成用于燃气涡轮发动机的涡轮叶片的叶片尖端。叶片尖端合金优选地具有重量百分比为约14至约18％的铬，约6.45至约6.95％的铝，约9.75至约11.45％的钴，约5.95至约6.55％的钽，约1.85至约2.35％的铼，约0.05至约1.75％的铪，约0.006至约0.03％的锆，约0.02至约0.11％的碳，至多约1.1％的硅，至多约0.01％的硼，余量为镍和典型杂质。

5. 发明授权

US5584662A Laser shock peening for gas turbine engine vane repair 失效
标题翻译：用于燃气轮机发动机叶片修复的激光冲击喷丸
公开(公告)号：US5584662A
公开(公告)日：1996-12-17
申请号：US399321
申请日：1995-03-06
申请人： Seetharamaiah Mannava , Stephen J. Ferrigno
发明人： Seetharamaiah Mannava , Stephen J. Ferrigno
IPC分类号： B23P6/00 , C21D7/06 , C21D10/00 , F01D5/00 , F01D5/14 , F01D9/02
CPC分类号： B23P6/007 , C21D10/005 , F01D5/005 , C21D10/00 , C21D7/06 , Y10S148/903 , Y10T29/49318 , Y10T29/49336
摘要： A wide gap braze repair, particularly for a gas turbine engine vane or a component in the hot section of the engine. The repair is characterized by a braze filled void in a damaged area of the component, a laser shock peened surface over the repaired area of the braze filled void, and a region of deep compressive residual stresses imparted by laser shock peening (LSP) extending from the laser shock peened surface into the repair.
摘要翻译：特别是用于燃气涡轮发动机叶片或发动机热段中的部件的宽间隙钎焊修复。该修复的特征在于部件的损坏区域中的钎焊填充空隙，在钎焊填充空隙的修复区域上的激光冲击硬化表面以及由激光冲击喷丸（LSP）延伸的深度压缩残余应力的区域激光冲击喷丸表面进行修补。

6. 发明授权

US5071054A Fabrication of cast articles from high melting temperature superalloy compositions 失效
标题翻译：从高熔点高温合金组合物制造铸件
公开(公告)号：US5071054A
公开(公告)日：1991-12-10
申请号：US629856
申请日：1990-12-18
申请人： Robert Dzugan , Stephen J. Ferrigno , William R. Young , Marc J. Froning
发明人： Robert Dzugan , Stephen J. Ferrigno , William R. Young , Marc J. Froning
IPC分类号： B22D21/06 , B22D29/00 , B23K9/04 , B23K20/02 , B23P6/04 , B30B5/02 , C21D10/00 , C23C24/08
CPC分类号： B23P6/007 , B23K20/021 , C21D10/00 , Y10T29/49318
摘要： A superalloy article is fabricated by casting a high melting temperature superalloy composition and then refurbishing the primary defects that are found in the surface of the cast piece. The article is refurbished by excising the primary defects and a surrounding portion of metal by grinding, filling the excised volume with metal of the same composition as the cast article by welding or a similar technique, smoothing the surface around any resulting filler metal defects, and applying a cladding powder to the surface from which the filler metal defects are removed. The cladding powder is applied by painting a binder onto the surface and then dusting cladding powder onto the binder before it has dried. The cladding powder is a mixture of particles of a high melting temperature superalloy and particles of a lower melting temperature metal. The article is heated to a preselected temperature, depending on the alloy, to melt and subsequently solidify the cladding powder. Finally, the article is hot isostatically pressed to achieve final closure of surface defects.

7. 发明授权

US5735044A Laser shock peening for gas turbine engine weld repair 失效
标题翻译：用于燃气轮机发动机焊接维修的激光冲击喷丸
公开(公告)号：US5735044A
公开(公告)日：1998-04-07
申请号：US571048
申请日：1995-12-12
申请人： Stephen J. Ferrigno , William D. Cowie , Seetharamaiah Mannava
发明人： Stephen J. Ferrigno , William D. Cowie , Seetharamaiah Mannava
IPC分类号： B23P6/00 , C21D9/50 , C21D10/00 , F01D5/00 , B23P15/00
CPC分类号： B23P6/007 , B23P6/045 , C21D10/005 , F01D5/005 , C21D9/50 , Y10T29/49318 , Y10T29/49339
摘要： A crack weld repair and method, particularly, for a gas turbine engine blade or other metallic component in the engine, providing a metallic substrate, a metallic filler bonded onto a substrate bond surface on the metallic substrate, and a region having deep compressive residual stresses imparted by laser shock peening extending into the substrate beneath the substrate bond surface. One embodiment provides a laser shock peened surface below the weld material filled void in a damaged area of the component forming a region of deep compressive residual stresses imparted by laser shock peening (LSP) extending from the laser shock peened surface into the component. Optionally, the surface over the repaired area of the weld filled void may also be laser shock peened forming a second region of deep compressive residual stresses imparted by laser shock peening (LSP) extending from the laser shock peened surface into the weld repair. Another embodiment provides a weld buildup tip overlay on a substrate bond surface of an airfoil tip having a laser shock peened region beneath the substrate bond surface.
摘要翻译：裂缝焊接修复和方法，特别是用于发动机中的燃气涡轮发动机叶片或其它金属部件，提供金属基底，结合到金属基底上的基底接合表面上的金属填料和具有较深的压缩残余应力的区域通过激光冲击喷丸延伸到衬底粘合表面下方的衬底中。一个实施例在激光冲击喷丸表面延伸到组件中的激光冲击喷丸（LSP）所施加的深度压缩残余应力区域中，提供了在该部件的损坏区域内的焊接材料填充空隙下面的激光冲击喷丸表面。任选地，焊接填充空隙的修复区域上的表面也可以是激光冲击喷丸，形成由激光冲击喷丸表面延伸到焊接修复中的激光冲击喷丸（LSP）所施加的深度压缩残余应力的第二区域。另一个实施例提供了在基片接合表面下方具有激光冲击硬化区域的翼型件末端的基底接合表面上的焊接积聚尖端覆盖层。

8. 发明授权

US5569546A Repaired article and material and method for making 失效
标题翻译：修理文章和材料和制作方法
公开(公告)号：US5569546A
公开(公告)日：1996-10-29
申请号：US402418
申请日：1995-03-10
申请人： Stephen J. Ferrigno , David C. Fairbourn
发明人： Stephen J. Ferrigno , David C. Fairbourn
IPC分类号： B23K35/02 , B23K35/30 , B23K35/40 , B23P6/04 , C22C19/05
CPC分类号： B23K35/40 , B23K35/0244 , B23K35/3046 , Y10T428/12861
摘要： A composite weld wire, for use in repairing an article of a Co base alloy, comprises the sintered product of a mixture, by weight, of about 50-90% of the Co base alloy and about 10-50% of a Ni base alloy consisting essentially of, by weight, about: 1.5-2.5% B, 2-5% Al, 2-4% Ta, 14-17% Cr, 8-12% Co, with the balance Ni and incidental impurities. Conveniently, the alloys initially are in powder form. A repaired Co base alloy article including a surface discontinuity, such as a crack or void, comprises a welded repair at the discontinuity using the weld wire. In another form, the article includes a first diffusion bonded repair alloy at the discontinuity and a second repair alloy welded over the first repair alloy using the composite weld wire. One form of a method for repairing the article includes first removing oxides from the discontinuity, diffusion bonding the first repair alloy at the discontinuity, and then welding the second repair alloy over the first repair alloy using the composite weld wire. In another form of the method, the repair alloy is welded directly over the discontinuity, particularly in the vicinity of a hole through a surface of the article. The total mount of B in the weld wire, or weld repair alloy, is in the range of about 0.2-1.2 weight % to provide desired weld flow without resulting in reduction in ductility and mechanical properties.
摘要翻译：用于修复Co基合金制品的复合焊丝包括重量比约50-90％的Co基合金和约10-50％的Ni基合金的烧结产品基本上由以重量计约为：1.5-2.5％B，2-5％Al，2-4％Ta，14-17％Cr，8-12％Co，余量为Ni和附带杂质。方便地，合金最初是粉末状的。包括诸如裂纹或空隙的表面不连续性的修复的Co基合金制品包括使用焊丝在不连续处的焊接修补。在另一种形式中，所述制品包括不连续处的第一扩散接合修复合金和使用所述复合焊丝焊接在所述第一修复合金上的第二修复合金。用于修复制品的方法的一种形式包括首先从不连续处去除氧化物，在不连续处扩散接合第一修复合金，然后使用复合焊丝将第二修复合金焊接在第一修复合金上。在该方法的另一种形式中，修补合金直接焊接在不连续部分上，特别是在通过制品表面的孔附近。在焊丝或焊接修复合金中的B的总安装量在约0.2-1.2重量％的范围内以提供所需的焊接流动，而不会导致延展性和机械性能的降低。

9. 发明授权

US5525429A Laser shock peening surface enhancement for gas turbine engine high strength rotor alloy repair 失效
标题翻译：激光冲击喷丸表面增强燃气轮机高强度转子合金修复
公开(公告)号：US5525429A
公开(公告)日：1996-06-11
申请号：US399320
申请日：1995-03-06
申请人： Seetharamaiah Mannava , William D. Cowie , Stephen J. Ferrigno
发明人： Seetharamaiah Mannava , William D. Cowie , Stephen J. Ferrigno
IPC分类号： B23K26/00 , B23P6/00 , B23P9/00 , C21D10/00 , C22F1/10 , C22F1/18 , C23C4/02 , F01D5/00 , C21D7/00 , B23P15/02
CPC分类号： B23P6/002 , B23K26/0069 , B23P9/00 , C21D10/005 , C22F1/10 , C22F1/183 , C23C4/02 , F01D5/005 , Y10S428/937 , Y10T29/49318 , Y10T428/12458 , Y10T428/12806 , Y10T428/12861 , Y10T428/12944
摘要： A metallic article and method for producing such an article, having a metallic substrate, at least one metallic layer sprayed onto a laser shock peened surface area of the substrate, and a region having deep compressive residual stresses imparted by laser shock peening extending into the substrate from the laser shock peened surface. The metallic substrate and or layer may be made from an alloy such as a Cobalt or a Nickel based superalloy. The substrate may be made from Nickel Base forgings or Titanium base forgings. An exemplary embodiment of the present invention is a gas turbine engine rotor component such a disk and, more particularly, a turbine disk suitable for use in a hot section of a gas turbine engine. The invention may be used for new or refurbished parts to restore dimensions of the component and, in particular, radial dimensions.
摘要翻译：一种用于制造这种制品的金属制品和方法，具有金属基底，喷涂到基底的激光冲击硬化表面区域上的至少一个金属层，以及由激光冲击喷丸延伸到基底中的深度压缩残余应力的区域从激光冲击硬化表面。金属基底和/或层可由合金如钴或镍基超级合金制成。衬底可以由镍基锻件或钛基锻件制成。本发明的示例性实施例是一种燃气涡轮发动机转子部件，例如盘，更具体地，适合用于燃气涡轮发动机的热部分的涡轮盘。本发明可以用于新的或翻新的部件以恢复部件的尺寸，特别是径向尺寸。

10. 发明授权

US5240491A Alloy powder mixture for brazing of superalloy articles 失效
标题翻译：合金粉末混合物用于钎焊超合金制品
公开(公告)号：US5240491A
公开(公告)日：1993-08-31
申请号：US726495
申请日：1991-07-08
申请人： David E. Budinger , Stephen J. Ferrigno , Wendy H. Murphy
发明人： David E. Budinger , Stephen J. Ferrigno , Wendy H. Murphy
IPC分类号： B23K35/30
CPC分类号： B23K35/3033 , B23K35/304 , B23K35/3046 , Y10T428/12861 , Y10T428/12931 , Y10T428/12944
摘要： A series of braze materials for brazing superalloy substrates at effective brazing temperatures above about 2300.degree. F. is described. The braze materials are formulated as mixtures of cobalt- and nickel-base alloy powders. Each such braze material contains at least two components, one of which is predominantly liquid at the effective brazing temperature, and one of which remains substantially solid at that temperature. The brazing materials solidify by an isothermal solidification process. Unless otherwise limited by the temperature capability of the superalloy substrate being joined, these brazing alloys provide joints that have useful strength at temperatures significantly higher than joints made with prior art brazing alloys.
摘要翻译：描述了一种用于在高于约2300°F的有效钎焊温度下钎焊超级合金基底的钎焊材料。钎焊材料被配制成钴和镍基合金粉末的混合物。每个这样的钎焊材料含有至少两种组分，其中一种组分在有效钎焊温度下主要是液体，其中一种在该温度下基本上保持固体。钎焊材料通过等温凝固过程固化。除非被接合的超级合金基底的温度能力限制，否则这些钎焊合金提供的接头在显着高于现有技术钎焊合金的接头温度下具有有用的强度。

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