专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US06500269B2 Method of cleaning turbine component using laser shock peening 失效
公开(公告)号：US06500269B2
公开(公告)日：2002-12-31
申请号：US09771850
申请日：2001-01-29
申请人： James D. Risbeck , Thomas E. Anderson , Stephen J. Ferrigno , Tris Colaizzi
发明人： James D. Risbeck , Thomas E. Anderson , Stephen J. Ferrigno , Tris Colaizzi
IPC分类号： B08B312
CPC分类号： B08B7/0042 , C21D10/005 , F01D25/002 , Y02P10/212
摘要： A method of cleaning airfoils and related turbine engine components that have a crust-like debris deposited on the surface thereof. This method involves subjecting at least the portion of the component having the deposit of the crust-like debris to sufficient laser shock peening to cause the debris on the surface thereof to be loosened therefrom so that the loosened debris can be removed from the component. This loosened debris can then be removed from the component, such as by passing a cleaning fluid through the portion of the component that is subjected to the laser shock peening.

2. 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。

3. 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.

4. 发明授权

US5666643A High temperature braze material 失效
标题翻译：高温钎焊材料
公开(公告)号：US5666643A
公开(公告)日：1997-09-09
申请号：US655276
申请日：1996-05-15
申请人： Richard P. Chesnes , Stephen J. Ferrigno , David E. Budinger , Melvin R. Jackson
发明人： Richard P. Chesnes , Stephen J. Ferrigno , David E. Budinger , Melvin R. Jackson
IPC分类号： B23K35/02 , B23K35/30 , B22F7/00
CPC分类号： B23P6/002 , B23K1/0018 , B23K35/0222 , B23K35/0244 , B23P6/045 , F01D5/005 , B23K2201/001 , B23K35/025 , B23K35/3033 , B23K35/3046 , Y10T428/12035 , Y10T428/12056 , Y10T428/12097 , Y10T428/1216
摘要： A braze material is provided for repairing an article, and particularly components formed from cobalt and nickel-base superalloys, such as gas turbine engine components. The braze material is composed of high melt particles distributed within a braze alloy. The braze alloy can be any suitable bonding material of the type used to repair components that must operate at high temperatures. The particles are single crystal, directionally solidified or equiaxed particles formed from a superalloy or ceramic material, or mixtures thereof. Importantly, the particles have an aspect ratio (length to width) of at least 4:1. The braze material can be provided and used in the form of a slurry, a presintered preform, a plasticized tape, or in a powdered form.
摘要翻译：提供钎焊材料用于修复制品，特别是由钴和镍基超级合金（例如燃气轮机发动机部件）形成的部件。钎焊材料由分布在钎焊合金中的高熔体颗粒组成。钎焊合金可以是用于修复必须在高温下操作的部件的类型的任何合适的粘合材料。颗粒是由超级合金或陶瓷材料形成的单晶，定向凝固或等轴的颗粒，或其混合物。重要的是，颗粒的纵横比（长宽比）至少为4:1。钎焊材料可以以浆料，预烧结预制件，增塑胶带或粉末形式的形式提供和使用。

5. 发明授权

US5622638A Method for forming an environmentally resistant blade tip 失效
标题翻译：用于形成耐环境的叶片尖端的方法
公开(公告)号：US5622638A
公开(公告)日：1997-04-22
申请号：US647523
申请日：1996-05-15
申请人： Jerry D. Schell , Howard J. Farr , Thomas J. Kelly , Paul J. E. Monson , Stephen J. Ferrigno
发明人： Jerry D. Schell , Howard J. Farr , Thomas J. Kelly , Paul J. E. Monson , Stephen J. Ferrigno
IPC分类号： C22C1/04 , C22C19/05 , C23C24/10 , F01D5/20 , B23K26/00 , C23C4/00 , F01D11/08
CPC分类号： B23K26/0853 , C22C1/0433 , C22C19/058 , C23C24/103 , F01D5/20 , Y10T428/12944
摘要： A method for forming a blade tip on a turbine blade of a gas turbine engine includes providing a powder alloy from a family of environmentally-resistant powder alloys and forming the blade tip by melting and fusing the powder alloy to the turbine blade. 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：在燃气轮机发动机的涡轮叶片上形成叶片尖端的方法包括从一系列耐环境的粉末合金中提供粉末合金，并通过将粉末合金熔化并熔合到涡轮叶片上形成叶片尖端。叶片尖端合金优选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。

6. 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。

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

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。

9. 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。

10. 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。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式