专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

11. 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。

12. 发明授权

US5492447A Laser shock peened rotor components for turbomachinery 失效
标题翻译：用于涡轮机械的激光冲击喷丸转子部件
公开(公告)号：US5492447A
公开(公告)日：1996-02-20
申请号：US319346
申请日：1994-10-06
申请人： Seetharamaiah Mannava , Albert E. McDaniel , William D. Cowie
发明人： Seetharamaiah Mannava , Albert E. McDaniel , William D. Cowie
IPC分类号： C21D7/06 , C21D10/00 , F01D5/02 , F01D5/28 , F01D5/30 , F01D1/24
CPC分类号： B23K26/0069 , C21D10/005 , F01D5/02 , F01D5/286 , F01D5/3092 , C21D7/06 , F05D2230/90 , Y02T50/671
摘要： Turbomachinery rotor components having a metallic body with at least a portion of the body subject to a tensile stress field due to centrifugal and thermal growth induced forces generated by the rotor when the rotor is rotating, at least one stress riser in the stress field portion that causes stress concentration when the rotor is rotating, and at least one region of the component around the stress riser having deep compressive residual stresses imparted by laser shock peening (LSP).
摘要翻译：具有金属体的涡轮机械转子部件，其具有至少一部分体，由于转子旋转时由转子产生的离心和热生长引起的力产生拉伸应力场，应力场部分中的至少一个应力提升器当转子旋转时，引起应力集中，并且应力提升管周围的部件的至少一个区域具有由激光冲击喷丸（LSP）赋予的较深的压缩残余应力。

13. 发明授权

US6155789A Gas turbine engine airfoil damper and method for production 失效
标题翻译：燃气涡轮发动机翼型阻尼器及其生产方法
公开(公告)号：US6155789A
公开(公告)日：2000-12-05
申请号：US286803
申请日：1999-04-06
申请人： Seetharamaiah Mannava , William D. Cowie , Robert L. Yeaton
发明人： Seetharamaiah Mannava , William D. Cowie , Robert L. Yeaton
IPC分类号： C21D10/00 , F01D5/16 , F01D5/26 , B63H1/26
CPC分类号： C21D10/005 , F01D5/16 , F01D5/26 , Y02T50/673 , Y10S416/50 , Y10T29/49318 , Y10T29/49336
摘要： A gas turbine engine airfoil assembly for damping airfoil vibrations includes a metallic airfoil having an outer surface and a chordwise extending cavity beneath the outer surface of the airfoil. A damper is trapped within the cavity and a region in the airfoil surrounding the cavity has compressive residual stresses imparted by laser shock peening. The damper is preferably a chordwise extending linear wire having a distal end tacked down within the cavity. The invention includes a method for constructing the assembly for damping airfoil vibrations.
摘要翻译：用于阻尼翼型振动的燃气涡轮发动机翼型组件包括在翼型件的外表面下方具有外表面和弦向延伸腔的金属翼型件。阻尼器被捕获在空腔内，并且围绕空腔的翼型中的区域具有由激光冲击喷丸施加的压缩残余应力。阻尼器优选地是弦向延伸的线性线，其具有在腔内向下的远端。本发明包括一种用于构造用于阻尼翼型振动的组件的方法。

14. 发明授权

US5742028A Preloaded laser shock peening 失效
标题翻译：预装激光冲击硬化
公开(公告)号：US5742028A
公开(公告)日：1998-04-21
申请号：US685647
申请日：1996-07-24
申请人： Seetharamaiah Mannava , William D. Cowie
发明人： Seetharamaiah Mannava , William D. Cowie
IPC分类号： B23K26/00 , B23K26/14 , B23K26/36 , C21D7/06 , C21D10/00 , F01D5/28
CPC分类号： F01D5/286 , B23K26/0069 , B23K26/146 , B23K26/364 , C21D10/005 , C21D7/06 , Y02T50/673
摘要： A method of laser shock peening a gas turbine engine article by loading the article such that a portion of the article to be laser shock peened is placed in a loaded condition while the portion is laser shock peened using a laser to fire a laser beam with sufficient power to vaporize material on a laser shock peening surface of the portion of the article to form a region in the portion having deep compressive residual stresses imparted by the laser shock peening process extending into the article from the laser shock peened surface. The loaded condition may be either in compression or preferably tension. The loaded article is continuously moved while continuously firing a stationary laser beam, which repeatably pulses between relatively constant periods, on a portion of the article with sufficient power to vaporize material on the surface of the portion of the article with the pulses around laser beam spots formed by the laser beam on the surface and form a region having deep compressive residual stresses extending into the article from the laser shock peened surface. Flowing a curtain of water over the surface upon which the laser beam is firing while moving the article until the laser shock peened surface is completely covered by laser beam spots at least once. The surface may coated with paint or tape which is the material used to produce the plasma or the surface may be unpainted and the metal of the article is used to produce the plasma.
摘要翻译：一种通过加载物品来激光冲击硬化燃气涡轮发动机制品的方法，使得将待激光冲击喷丸的制品的一部分置于加载状态，同时使用激光对激光进行激光冲击，以足够的激光激发激光束用于在制品的激光冲击硬化表面上蒸发材料的功能，以在由激光冲击硬化表面延伸到制品中的激光冲击硬化过程赋予的具有深的压缩残余应力的部分中形成区域。装载状态可以是压缩的或优选地是张力。负载物品连续地移动，同时连续地点燃一个固定的激光束，该固定的激光束在相对恒定的周期之间重复地脉冲，在制品的一部分上具有足够的动力，以在激光束点周围的脉冲上蒸发制品部分表面上的材料由激光束在表面上形成，并形成从激光冲击硬化表面延伸到制品中的具有深的压缩残余应力的区域。在移动物品的同时在激光束射出的表面上流动水幕直到激光冲击喷丸表面完全被激光束斑点覆盖至少一次。表面可以涂覆有用于产生等离子体或表面的材料的油漆或胶带，其可以是未涂漆的，并且制品的金属用于产生等离子体。

15. 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。

16. 发明授权

US5569018A Technique to prevent or divert cracks 失效
标题翻译：防止或转移裂缝的技术
公开(公告)号：US5569018A
公开(公告)日：1996-10-29
申请号：US399319
申请日：1995-03-06
申请人： Seetharamaiah Mannava , William D. Cowie
发明人： Seetharamaiah Mannava , William D. Cowie
IPC分类号： F01D9/00 , B23P6/04 , C21D1/09 , C21D7/04 , C21D7/06 , C21D9/00 , C21D10/00 , F01D5/28 , F01D9/02 , F02C7/00 , F04D29/44
CPC分类号： B23P6/002 , C21D10/005 , F01D5/286 , C21D2221/00 , C21D7/06 , Y02T50/671
摘要： Gas turbine engine static component with a metallic panel section, either linear or curved, that is susceptible to cracks initiated by features on the component has an elongated laser shock peened region having deep compressive residual stresses imparted by laser shock peening (LSP) disposed between the feature and a portion of the panel section, which is to be protected from failure, such that the laser shock peened region diverts cracks that propagate from the feature away from the portion of the panel section. The laser shock peened region preferably extends through the component and is may be formed by simultaneously laser shock peening first and second laser shock peened surface areas to form the laser shock peened region.
摘要翻译：具有线性或弯曲的金属板部分的燃气涡轮发动机静态部件易于由部件上的特征引起的裂纹，具有细长的激光冲击喷丸区域，其具有由激光冲击喷丸（LSP）设置的深度压缩残余应力特征和面板部分的一部分，其将被防止破坏，使得激光冲击硬化区域将从特征部分传播的裂纹从面板部分的部分转移出去。激光冲击硬化区域优选地延伸穿过部件，并且可以通过同时激光冲击硬化第一和第二激光冲击喷丸表面区域形成激光冲击喷丸区域。

17. 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