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1. 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。

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

US06200689B1 Laser shock peened gas turbine engine seal teeth 失效
标题翻译：激光冲击硬化燃气轮机发动机密封齿
公开(公告)号：US06200689B1
公开(公告)日：2001-03-13
申请号：US09170969
申请日：1998-10-14
申请人： Stephen J. Ferrigno , Kevin G. McAllister , Seetharamaiah Mannava
发明人： Stephen J. Ferrigno , Kevin G. McAllister , Seetharamaiah Mannava
IPC分类号： F01D1102
CPC分类号： C21D10/005 , B23K26/21 , B23K26/356 , Y10S148/90 , Y10T428/12389 , Y10T428/12458
摘要： The present invention includes a method of repairing an annular metallic article and the repaired article itself which has an axially extending annular support and a projection generally radially extending therefrom. The projection has an associated operating radial height as measured from a radially facing annular first surface of the support and an associated shape. An upper portion of the projection is removed forming a stub extending away from the first surface and having a bonding surface at a stub end spaced apart from the first surface. A metallic material is metallurgically bonded to the bonding surface forming an annular heat affected zone in the stub bounded by the bonding surface. A first portion of the metallic material is removed to restore the projection to the operating height and shape. At least one annular outer surface of the tooth extending over at least a portion of the heat affected zone is laser shock peened, preferably after the first portion of the metallic material is removed. A tip of the stub formed by the removing of the first portion of the metallic material may also be laser shock peened as may a non-heat affected zone portion of the stub extending at least a partial length of a distance from the heat affected zone to the first surface. Opposite forward and aft facing annular surfaces of the projection may be laser shock peened, preferably simultaneously. The laser beam may be fired normal to or at an oblique angle to the forward and aft facing annular surfaces.
摘要翻译：本发明包括修复环形金属制品和修理制品本身的方法，其具有轴向延伸的环形支撑件和从其大致径向延伸的突出部。突起具有从支撑件的径向面对的环形第一表面和相关联的形状测量的相关联的操作径向高度。去除突起的上部，形成从第一表面延伸的短截线，并且在与第一表面间隔开的短截线端具有接合表面。将金属材料冶金地结合到接合表面，在由接合表面限定的短截线中形成环形的热影响区域。去除金属材料的第一部分以将投影恢复到操作高度和形状。在热影响区域的至少一部分上延伸的齿的至少一个环形外表面是激光冲击喷丸，优选地在去除金属材料的第一部分之后。通过去除金属材料的第一部分形成的短截线的尖端也可以是激光冲击硬化，如短截线的非热影响区域部分延伸至少部分距离热影响区域的距离的部分长度第一个表面。突起的相对的前方和后方的环形表面可以是激光冲击硬化，优选同时地。激光束可以与向前和向后的环形表面正交或倾斜地发射。

4. 发明授权

US5846057A Laser shock peening for gas turbine engine weld repair 失效
公开(公告)号：US5846057A
公开(公告)日：1998-12-08
申请号：US823414
申请日：1997-03-25
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 , F01D5/14
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.

5. 发明授权

US5620307A Laser shock peened gas turbine engine blade tip 失效
标题翻译：激光冲击硬化燃气轮机发动机叶片尖端
公开(公告)号：US5620307A
公开(公告)日：1997-04-15
申请号：US399325
申请日：1995-03-06
申请人： Seetharamaiah Mannava , Albert E. McDaniel , William D. Cowie , Herbert Halila , James E. Rhoda , Stephen J. Ferrigno
发明人： Seetharamaiah Mannava , Albert E. McDaniel , William D. Cowie , Herbert Halila , James E. Rhoda , Stephen J. Ferrigno
IPC分类号： C21D10/00 , F01D5/28 , F01D5/18
CPC分类号： B23P6/002 , C21D10/005 , F01D5/286 , F05D2230/90 , Y02T50/671 , Y02T50/673 , Y10S148/903
摘要： Gas turbine engine blade with a metallic airfoil having a radially outer tip extending chordwise between a leading edge and a trailing edge and at least one laser shock peened surface extending radially along at least a portion of the tip and a region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into the airfoil from the laser shock peened surface.
摘要翻译：具有金属翼型件的燃气涡轮发动机叶片具有在前缘和后缘之间弦向延伸的径向外端，以及至少一个激光冲击喷丸表面，其沿着尖端的至少一部分径向延伸，并具有赋予深度压缩残余应力的区域通过激光冲击硬化（LSP）从激光冲击喷丸表面延伸到翼型中。

6. 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。

7. 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。

8. 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.

9. 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。

10. 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.

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