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1. 发明授权

US06341936B1 FOD inspection of laser shock peened gas turbine engine airfoils 失效
标题翻译：激光冲击喷丸机燃气涡轮发动机翼型FOD检测
公开(公告)号：US06341936B1
公开(公告)日：2002-01-29
申请号：US09556713
申请日：2000-04-21
申请人： William D. Cowie , Seetharamaiah Mannava , Jeffrey H. Nussbaum
发明人： William D. Cowie , Seetharamaiah Mannava , Jeffrey H. Nussbaum
IPC分类号： F01D514
CPC分类号： F01D21/14 , B23K26/356 , B23K2101/001 , B23P6/002 , C21D10/005 , F01D5/005 , F01D5/14 , F01D21/003 , F05D2260/80 , Y10T29/49318 , Y10T29/49336
摘要： The present invention is a method for operating a gas turbine engine airfoil having leading and trailing edges subject to FOD (foreign object damage) damage. The method includes inspecting the airfoil along at least a first one of the edges having at least a first laser shock peened patch along the first one of the edges, ascertaining FOD lengths of foreign object damage (FOD) extending from the first one of the edges into the airfoil within the patch, and allowing the airfoil to remain in service without repair if the FOD lengths are up to a maximum length of about one-half of a width of the laser shock peened patch, as measured from the edge.
摘要翻译：本发明是用于操作具有受FOD（异物损坏）损坏的前缘和后缘的燃气涡轮发动机翼型的方法。该方法包括沿至少第一边缘检查翼型件，其中至少第一边缘具有沿着第一边缘的至少第一激光冲击喷丸块，确定从第一边缘延伸的异物损坏（FOD）的FOD长度如果从边缘测量的FOD长度达到激光冲击喷丸补片的宽度的大约二分之一的最大长度，则允许翼型件保持在维修中。

2. 发明授权

US06541733B1 Laser shock peening integrally bladed rotor blade edges 失效
标题翻译：激光冲击喷丸一体叶片转子叶片边缘
公开(公告)号：US06541733B1
公开(公告)日：2003-04-01
申请号：US09771856
申请日：2001-01-29
申请人： Seetharamaiah Mannava , Jeffrey H. Nussbaum , Abraham S. Assa , Andrea G. M. Cox , James R. Zisson , Albert E. McDaniel , William D. Cowie
发明人： Seetharamaiah Mannava , Jeffrey H. Nussbaum , Abraham S. Assa , Andrea G. M. Cox , James R. Zisson , Albert E. McDaniel , William D. Cowie
IPC分类号： B23K2600
CPC分类号： F01D5/286 , C21D10/005 , Y02T50/673
摘要： A method for laser shock peening rotor blade leading and trailing edges of gas turbine engine integrally bladed rotors and disks that are not blocked by other rows of blades. The method includes continuously firing a stationary laser beam, which repeatable pulses between relatively constant periods, along at least a portion of leading or trailing edges of the blade, with the laser beam aimed at an oblique angle with respect to a surface of the edge such that laser pulses form overlapping elliptical shaped laser spots. In the exemplary embodiment of the invention, the elliptical shaped laser spots have an overlap of about 50% and are on the order of 11.7 mm by 4 mm in diameter. Another method is for laser shock peening rotor blade leading and trailing edges of gas turbine engine integrally bladed rotors and disks that are blocked by other rows of blades. The method includes continuously firing the stationary laser beam, which repeatable pulses between relatively constant periods, along at least a portion of leading or trailing edges of the blade, with the laser beam compoundly angled such that it is aimed at a first oblique angle with respect to a surface of the edge and at a second oblique angle with respect to an axis about which the rotor is circumscribed. Laser pulses form the elliptical shaped laser spots that are angled from the leading edge radially inwardly towards the axis. In the exemplary embodiment, the elliptical shaped laser spots have an overlap of about 50%.
摘要翻译：一种用于激光冲击喷丸的转子叶片的前缘和后缘的燃气涡轮发动机整体叶片的转子和盘，不被其他行的叶片阻挡。该方法包括沿着刀片的前缘或后缘的至少一部分连续射出固定的激光束，该固定激光束是相对恒定周期之间的可重复脉冲，其中激光束相对于边缘表面倾斜倾斜角，该激光脉冲形成重叠的椭圆形激光点。在本发明的示例性实施例中，椭圆形激光光斑具有约50％的重叠，并且在直径上为11.7mm×4mm。另一种方法是用于激光冲击硬化转子叶片的前缘和后缘的燃气涡轮发动机整体叶片转子和盘，被其他行的叶片阻挡。该方法包括沿着刀片的前缘或后缘的至少一部分连续点燃相对恒定周期之间的可重复脉冲的固定激光束，其中激光束复合成角度，使得其相对于第一倾斜角度瞄准到边缘的表面并且相对于绕转子限定的轴线以第二倾斜角度。激光脉冲形成从前缘径向向内朝向轴线成角度的椭圆形激光点。在示例性实施例中，椭圆形激光点具有约50％的重叠。

3. 发明授权

US5584586A Laser shock peened bearings 失效
标题翻译：激光冲击喷丸轴承
公开(公告)号：US5584586A
公开(公告)日：1996-12-17
申请号：US610298
申请日：1996-03-04
申请人： Dominick A. Casarcia , William D. Cowie , Seetharamaiah Mannava
发明人： Dominick A. Casarcia , William D. Cowie , Seetharamaiah Mannava
IPC分类号： C21D10/00 , F16C33/30 , F16C33/62 , F16C33/64
CPC分类号： C21D10/005 , F16C33/30 , F16C33/62 , F16C33/64 , F16C2360/23
摘要： A bearing element having a metallic body with a bearing contact curved surface portion, at least one laser shock peened surface encompassing at least a portion of the contact surface portion, and a region having deep compressive residual stresses imparted by laser shock peening (LSP) extending into the body from the laser shock peened surface. The present invention may be used for rolling elements such as ball bearing elements or elongated roller elements and for static elements such as races which may be singular or split and may have circumferentially spaced oil feed passages radially disposed therethrough.
摘要翻译：一种具有金属体的轴承元件，具有轴承接触弯曲表面部分，至少一个包围接触表面部分的至少一部分的激光冲击硬化表面以及具有由激光冲击喷丸（LSP）延伸的深度压缩残余应力的区域从激光冲击硬化表面进入身体。本发明可以用于诸如滚珠轴承元件或细长滚子元件之类的滚动元件，并且可用于诸如可以是单独的或分开的的种类的静态元件，并且可以具有径向设置在其中的周向隔开的供油通道。

4. 发明授权

US06183882B2 In plane deflection coupon for monitoring and controlling of laser shock peening 失效
标题翻译：用于监测和控制激光冲击喷丸的平面偏转试样
公开(公告)号：US06183882B2
公开(公告)日：2001-02-06
申请号：US09106320
申请日：1998-06-29
申请人： Seetharamaiah Mannava , William D. Cowie , P. Kennard Wright, III , Robert D. McClain
发明人： Seetharamaiah Mannava , William D. Cowie , P. Kennard Wright, III , Robert D. McClain
IPC分类号： B23K2600
CPC分类号： C21D10/005 , Y10S148/903 , Y10T428/12486
摘要： A test coupon is formed from a metallic strip having opposite first and second sides that generally define a plane of the strip and the strip includes a laser shock peened patch of the strip that has first and second laser shock peened surfaces on the first and second sides, respectively, first and second laser shocked regions having deep compressive residual stresses imparted by the laser shock peening extending into the strip from the first and second laser shock peened surfaces, respectively, and a deflection of a portion of the strip from a position of the portion before the laser shock peening. The deflection is formed by the laser shock peening such that at least a part and preferably substantially all of the deflection lies in the plane and the test coupon preferably includes an indicating means to indicate the deflection.
摘要翻译：测试试样由具有相反的第一和第二侧的金属带形成，其通常限定条带的平面，并且条带包括条带的激光冲击喷丸贴片，其在第一和第二侧上具有第一和第二激光冲击喷丸表面分别具有由激光冲击喷丸赋予的深压缩残余应力的第一激光冲击区域和第二激光冲击区域分别从第一和第二激光冲击喷丸表面延伸到条带中，并且一部分条带从激光冲击硬化之前的部分。通过激光冲击喷丸形成偏转，使得至少一部分，优选基本上全部的偏转位于平面中，并且测试试样优选地包括指示装置以指示偏转。

5. 发明授权

US5951790A Method of monitoring and controlling laser shock peening using an in plane deflection test coupon 失效
标题翻译：使用平面偏转测试试样监测和控制激光冲击喷丸的方法
公开(公告)号：US5951790A
公开(公告)日：1999-09-14
申请号：US107196
申请日：1998-06-26
申请人： Seetharamaiah Mannava , William D. Cowie , P. Kennard Wright, III , Robert D. McClain
发明人： Seetharamaiah Mannava , William D. Cowie , P. Kennard Wright, III , Robert D. McClain
IPC分类号： C21D10/00 , C21D1/54
CPC分类号： C21D10/005 , Y10S148/90 , Y10S148/903
摘要： A method for quality assurance of a laser process and more particularly a laser shock peening process that uses a test coupon having a deflection formed by a laser firing. The test coupon is from a metallic strip having opposite first and second sides that generally define a plane of the strip and the strip includes a laser shock peened patch of the strip that has first and second laser shock peened surfaces on the first and second sides, respectively, first and second laser shocked regions having deep compressive residual stresses imparted by the laser shock peening extending into the strip from the first and second laser shock peened surfaces, respectively, and a deflection of a portion of the strip from a position of the portion before the laser shock peening. The deflection is formed by the laser shock peening such that at least a part and preferably substantially all of the deflection lies in the plane of the strip and the test coupon preferably includes an indicating means to indicate the deflection. The quality assurance process of the present invention may further include correlating high cycle fatigue to the deflection.
摘要翻译：一种用于激光工艺的质量保证的方法，更具体地说是使用具有通过激光烧制形成的偏转的试样的激光冲击硬化工艺。试样来自具有相反的第一和第二侧的金属条，其通常限定条带的平面，并且条带包括条的激光冲击喷丸补片，其在第一和第二侧上具有第一和第二激光冲击硬化表面，分别具有由激光冲击喷丸赋予的深压缩残余应力的第一和第二激光冲击区域分别从第一和第二激光冲击喷丸表面延伸到条带中，并且一部分条带从该部分的位置偏转之前激光冲击硬化。通过激光冲击喷丸形成偏转，使得至少一部分并且优选地基本上全部的偏转位于条的平面中，并且试样优选地包括指示装置以指示偏转。本发明的质量保证过程还可以包括将高循环疲劳与偏转相关联。

6. 发明授权

US5591009A Laser shock peened gas turbine engine fan blade edges 失效
标题翻译：激光冲击硬化燃气轮机发动机风扇叶片边缘
公开(公告)号：US5591009A
公开(公告)日：1997-01-07
申请号：US373133
申请日：1995-01-17
申请人： Seetharamaiah Mannava , Albert E. McDaniel , William D. Cowie , Herbert Halila , James E. Rhoda , James E. Gutknecht
发明人： Seetharamaiah Mannava , Albert E. McDaniel , William D. Cowie , Herbert Halila , James E. Rhoda , James E. Gutknecht
IPC分类号： C21D10/00 , F01D5/28 , F01D5/14
CPC分类号： F01D5/286 , C21D10/005 , Y02T50/671 , Y02T50/673 , Y10S148/903
摘要： Gas turbine engine fan blade with a metallic airfoil having a leading edge, a trailing edge, and a radially outer tip, and at least one laser shock peened surface located along the leading edge with 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：具有前缘，后缘和径向外端的金属翼型的燃气涡轮发动机风扇叶片以及沿着前缘设置的至少一个激光冲击硬化表面，其具有由激光冲击喷丸赋予的较深的压缩残余应力（LSP）从激光冲击硬化表面延伸到翼型中。

7. 发明授权

US5522706A Laser shock peened disks with loading and locking slots for turbomachinery 失效
标题翻译：激光冲击喷丸盘，带有用于涡轮机械的加载和锁定槽
公开(公告)号：US5522706A
公开(公告)日：1996-06-04
申请号：US319389
申请日：1994-10-06
申请人： Seetharamaiah Mannava , William D. Cowie
发明人： Seetharamaiah Mannava , William D. Cowie
IPC分类号： C21D10/00 , F01D5/28 , F01D5/30 , F01D5/02
CPC分类号： F01D5/3007 , C21D10/005 , F01D5/286 , F01D5/3038 , F05D2230/41 , Y02T50/671
摘要： Turbomachinery rotor component, which may be a disk or drum rotor, having an annular rim disposed about a centerline for securing the blades to the rotor and that is subject to a tensile stress field due to centrifugal and thermal growth induced forces generated by the rotor when the rotor is rotating. An annular channel slot is cut around the rim, has outer annular overhanging rails, and has at least one stress riser in the form of a three sided slot cut in the radial direction through one of the rails. A region around rounded corners of the stress riser has deep compressive residual stresses imparted by laser shock peening and extends inward from a laser shocked surface of the component encompassed by the region. A more particular embodiment, the annular channel slot is a dovetail blade root slot and the outer annular overhanging rails each has pairs of stress risers in the form of opposing three sided slots cut in the radial direction through each of the rails wherein one pair is a pair of blade loading slots and another pair is a pair of blade locking slots.
摘要翻译：涡轮机械转子部件，其可以是圆盘或滚筒转子，具有围绕中心线设置的环形边缘，用于将叶片固定到转子上，并且由于转子产生的离心和热生长引起的力而受到拉伸应力场，转子旋转。围绕边缘切割环形槽槽，具有外环形突出轨道，并且具有通过其中一个轨道沿径向方向切割的三边槽形式的至少一个应力提升管。应力提升管的圆角周围的区域具有由激光冲击喷丸赋予的深的压缩残余应力，并且从该区域所包括的部件的激光冲击表面向内延伸。一个更具体的实施例，环形通道狭槽是燕尾叶片根槽，并且外环形突出轨道每个具有成对的应力提升器，其形式为通过每个轨道在径向方向上切割的相对的三边槽，其中一对为一对刀片加载槽和另一对是一对刀片锁定槽。

8. 发明授权

US06551064B1 Laser shock peened gas turbine engine intermetallic parts 失效
标题翻译：激光冲击喷丸机燃气涡轮发动机金属间零件
公开(公告)号：US06551064B1
公开(公告)日：2003-04-22
申请号：US08686630
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： B63H126
CPC分类号： F01D5/286 , C21D10/005 , Y02T50/671 , Y02T50/673 , Y10T29/49336
摘要： An intermetallic article such as a gas turbine engine component and method of manufacture thereof includes a region having compressive residual stresses imparted by laser shock peening (LSP) extending into the article from a laser shock peened surface. One embodiment includes a turbine or compressor blade with an intermetallic airfoil having a leading edge and at least one laser shock peened surface extending radially along at least a portion of the leading edge with a region having compressive residual stresses imparted by laser shock peening (LSP) extending into the intermetallic airfoil from the laser shock peened surface.
摘要翻译：诸如燃气涡轮发动机部件的金属间物品及其制造方法包括具有从激光冲击喷丸表面延伸到制品中的激光冲击喷丸（LSP）施加的压缩残余应力的区域。一个实施例包括具有前缘的金属间翼型的涡轮机或压缩机叶片以及沿着前缘的至少一部分径向延伸的至少一个激光冲击喷丸表面，具有由激光冲击喷丸（LSP）施加的压缩残余应力的区域，从激光冲击喷丸表面延伸到金属间翼型。

9. 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.

10. 发明授权

US5846054A Laser shock peened dovetails for disks and blades 失效
标题翻译：用于磁盘和刀片的激光冲击硬化燕尾形
公开(公告)号：US5846054A
公开(公告)日：1998-12-08
申请号：US319345
申请日：1994-10-06
申请人： Seetharamaiah Mannava , Albert E. McDaniel , William D. Cowie , Herbert Halila
发明人： Seetharamaiah Mannava , Albert E. McDaniel , William D. Cowie , Herbert Halila
IPC分类号： C21D10/00 , F01D5/28 , F01D5/30
CPC分类号： F01D5/3007 , F01D5/286 , F01D5/3092 , C21D10/005 , Y02T50/671
摘要： A dovetail assembly for mounting blades with dovetail roots axially into disk dovetail slots around a disk periphery which is subject to a tensile stress field due to centrifugal and thermal growth induced forces generated by the rotor when the rotor is rotating. The dovetail assembly has stress risers each in the form of a transition fillet between a neck or an area of minimum width and a pressure face which is designed to be a contact surface between complementary blade dovetail roots and disk dovetail slots formed between adjacent disk posts. The region around the stress riser has deep compressive residual stresses imparted by laser shock peening and is radially adjacent the stress riser and extends inward from a laser shocked surface of the component along the transition fillet.
摘要翻译：一种燕尾组件，其用于将叶片的叶片轴向安装在围绕盘周边的盘形燕尾槽中，盘形周边由转子旋转时由转子产生的离心和热生长引起的力引起拉应力场。燕尾组合件具有在颈部或最小宽度区域之间的过渡角形的压力提升器，压力面被设计成互补的叶片燕尾根和相邻的盘柱之间形成的盘形燕尾槽之间的接触表面。应力提升管周围的区域具有由激光冲击喷丸赋予的较深的压缩残余应力，并且径向地邻近应力提升器并且沿着过渡圆角从部件的激光冲击表面向内延伸。

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