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1. 发明授权

US07942641B2 Varying fluence as a function of thickness during laser shock peening 有权
标题翻译：在激光冲击硬化过程中作为厚度的函数改变注量
公开(公告)号：US07942641B2
公开(公告)日：2011-05-17
申请号：US12782305
申请日：2010-05-18
申请人： Mark Samuel Bailey , Michael Paul Hausfeld , Donald Eugene Williams, Jr. , Todd Jay Rockstroh
发明人： Mark Samuel Bailey , Michael Paul Hausfeld , Donald Eugene Williams, Jr. , Todd Jay Rockstroh
IPC分类号： F03B3/12 , C21D1/00
CPC分类号： C21D10/005 , C21D1/09 , C21D7/06 , F01D5/286 , F04D29/324 , F05D2240/303 , Y10T428/12389
摘要： A method for simultaneously laser shock peening opposite laser shock peening surfaces on opposite sides of an article, such as a gas turbine engine airfoil, with varying thickness using oppositely aimed laser beams and varying surface fluence of the laser beams over the laser shock peening surfaces as a function of the thickness of the article beneath each one of a plurality of laser shock peened spots formed by the beams on the surfaces. The fluence may be equal to the thickness multiplied by a volumetric fluence factor, the volumetric fluence factor being held constant over the laser shock peening surface. The volumetric fluence factor may be in a range of about 1200 J/cm3 to 1800 J/cm3 and more particularly about 1500 J/cm3. Laser beam energy may be varied with a computer program controlling firing of the laser beam.
摘要翻译：一种用于在激光冲击喷丸表面上相对激光冲击喷丸处理的方法，该激光冲击喷丸表面在物品的相对侧上，例如燃气涡轮发动机翼型，具有不同厚度，使用相对目标的激光束，以及激光束在激光冲击喷丸表面上的变化的表面注量在由表面上的光束形成的多个激光冲击喷丸点的每一个下面的物品的厚度的函数。流量可以等于厚度乘以体积注量因子，体积注量因子在激光冲击喷丸表面上保持不变。体积注量系数可以在约1200J / cm 3至1800J / cm 3的范围内，更特别地约在1500J / cm 3的范围内。激光束能量可以随着控制激光束射击的计算机程序而变化。

2. 发明授权

US07736450B2 Varying fluence as a function of thickness during laser shock peening 有权
标题翻译：在激光冲击硬化过程中作为厚度的函数改变注量
公开(公告)号：US07736450B2
公开(公告)日：2010-06-15
申请号：US11540186
申请日：2006-09-29
申请人： Mark Samuel Bailey , Michael Paul Hausfeld , Donald Eugene Williams, Jr. , Todd Jay Rockstroh
发明人： Mark Samuel Bailey , Michael Paul Hausfeld , Donald Eugene Williams, Jr. , Todd Jay Rockstroh
IPC分类号： C21D1/00 , B23K26/00 , C22C14/00 , C22C19/03
CPC分类号： C21D10/005 , C21D1/09 , C21D7/06 , F01D5/286 , F04D29/324 , F05D2240/303 , Y10T428/12389
摘要： A method for laser shock peening an article, such as a gas turbine engine airfoil, with varying thickness by varying a surface fluence of a laser beam over a laser shock peening surface as a function of the thickness beneath a laser shock peened spot formed by the beam on the surface. The fluence may be equal to the thickness multiplied by a volumetric fluence factor, the volumetric fluence factor being held constant over the laser shock peening surface. The volumetric fluence factor may be in a range of about 1200 J/cm3 to 1800 J/cm3 and more particularly about 1500 J/cm3. The method may include varying energy in the laser beam using a computer program controlling firing of the laser beam. A device such as an optical attenuator external to a laser performing firing may be used to vary the energy.
摘要翻译：一种通过在激光冲击硬化表面上改变激光束的表面能量密度来改变厚度变化的诸如燃气涡轮发动机翼型的物品的激光冲击冲击的方法，其作为由激光冲击硬化点形成的激光脉冲硬化点下方的厚度的函数光束在表面。流量可以等于厚度乘以体积注量因子，体积注量因子在激光冲击喷丸表面上保持不变。体积注量系数可以在约1200J / cm 3至1800J / cm 3的范围内，更特别地约在1500J / cm 3的范围内。该方法可以包括使用控制激光束激发的计算机程序在激光束中改变能量。可以使用诸如在执行烧制的激光器外部的光衰减器的装置来改变能量。

3. 发明申请

US20080078477A1 Varying fluence as a function of thickness during laser shock peening 有权
标题翻译：在激光冲击硬化过程中作为厚度的函数改变注量
公开(公告)号：US20080078477A1
公开(公告)日：2008-04-03
申请号：US11540186
申请日：2006-09-29
申请人： Mark Samuel Bailey , Michael Paul Hausfeld , Donald Eugene Williams , Todd Jay Rockstroh
发明人： Mark Samuel Bailey , Michael Paul Hausfeld , Donald Eugene Williams , Todd Jay Rockstroh
IPC分类号： B23K26/08
CPC分类号： C21D10/005 , C21D1/09 , C21D7/06 , F01D5/286 , F04D29/324 , F05D2240/303 , Y10T428/12389
摘要： A method for laser shock peening an article, such as a gas turbine engine airfoil, with varying thickness by varying a surface fluence of a laser beam over a laser shock peening surface as a function of the thickness beneath a laser shock peened spot formed by the beam on the surface. The fluence may be equal to the thickness multiplied by a volumetric fluence factor, the volumetric fluence factor being held constant over the laser shock peening surface. The volumetric fluence factor may be in a range of about 1200 J/cm3 to 1800 J/cm3 and more particularly about 1500 J/cm3. The method may include varying energy in the laser beam using a computer program controlling firing of the laser beam. A device such as an optical attenuator external to a laser performing firing may be used to vary the energy.
摘要翻译：一种通过在激光冲击硬化表面上改变激光束的表面能量密度来改变厚度变化的诸如燃气涡轮发动机翼型的物品的激光冲击冲击的方法，其作为由激光冲击硬化点形成的激光脉冲硬化点下方的厚度的函数光束在表面。流量可以等于厚度乘以体积注量因子，体积注量因子在激光冲击喷丸表面上保持不变。体积注量系数可以在约1200J / cm 3至1800J / cm 3之间的范围内，更特别地约为1500J / cm 3， SUP>。该方法可以包括使用控制激光束激发的计算机程序在激光束中改变能量。可以使用诸如在执行烧制的激光器外部的光衰减器的装置来改变能量。

4. 发明申请

US20100226780A1 VARYING FLUENCE AS A FUNCTION OF THICKNESS DURING LASER SHOCK PEENING 有权
标题翻译：变化的流动作为激光震动时的厚度函数
公开(公告)号：US20100226780A1
公开(公告)日：2010-09-09
申请号：US12782305
申请日：2010-05-18
申请人： Mark Samuel Bailey , Michael Paul Hausfeld , Donald Eugene William, JR. , Todd Jay Rockstroh
发明人： Mark Samuel Bailey , Michael Paul Hausfeld , Donald Eugene William, JR. , Todd Jay Rockstroh
IPC分类号： F01D5/14 , B32B3/30 , B23K26/00
CPC分类号： C21D10/005 , C21D1/09 , C21D7/06 , F01D5/286 , F04D29/324 , F05D2240/303 , Y10T428/12389
摘要： A method for simultaneously laser shock peening opposite laser shock peening surfaces on opposite sides of an article, such as a gas turbine engine airfoil, with varying thickness using oppositely aimed laser beams and varying surface fluence of the laser beams over the laser shock peening surfaces as a function of the thickness of the article beneath each one of a plurality of laser shock peened spots formed by the beams on the surfaces. The fluence may be equal to the thickness multiplied by a volumetric fluence factor, the volumetric fluence factor being held constant over the laser shock peening surface. The volumetric fluence factor may be in a range of about 1200 J/cm3 to 1800 J/cm3 and more particularly about 1500 J/cm3. Laser beam energy may be varied with a computer program controlling firing of the laser beam.
摘要翻译：一种用于在激光冲击喷丸表面上相对激光冲击喷丸处理的方法，该激光冲击喷丸表面在物品的相对侧上，例如燃气涡轮发动机翼型，具有不同厚度，使用相对目标的激光束，以及激光束在激光冲击喷丸表面上的变化的表面注量在由表面上的光束形成的多个激光冲击喷丸点的每一个下面的物品的厚度的函数。流量可以等于厚度乘以体积注量因子，体积注量因子在激光冲击喷丸表面上保持不变。体积注量系数可以在约1200J / cm 3至1800J / cm 3的范围内，更特别地约在1500J / cm 3的范围内。激光束能量可以随着控制激光束射击的计算机程序而变化。

5. 发明申请

US20100200189A1 METHOD OF FABRICATING TURBINE AIRFOILS AND TIP STRUCTURES THEREFOR 审中-公开
标题翻译：制造涡轮机空气的方法及其提升结构
公开(公告)号：US20100200189A1
公开(公告)日：2010-08-12
申请号：US12370115
申请日：2009-02-12
申请人： Huan Qi , Magdi Azer , Prabhjot Singh , Todd Jay Rockstroh , Sudhir K. Tewari , Joseph Giancarlo Sabato , Donald Brett Desander , Mark Douglas Gledhill
发明人： Huan Qi , Magdi Azer , Prabhjot Singh , Todd Jay Rockstroh , Sudhir K. Tewari , Joseph Giancarlo Sabato , Donald Brett Desander , Mark Douglas Gledhill
IPC分类号： B22D27/02 , B22F7/04 , B22D29/00 , B23P6/00
CPC分类号： B23K26/03 , B22F3/105 , B22F5/04 , B22F7/06 , B23K26/0622 , B23K26/32 , B23K26/34 , B23K26/342 , B23K26/60 , B23K35/0244 , B23K2101/001 , B23K2103/08 , B23K2103/18 , B23K2103/26 , B23P6/007 , Y10T29/49318
摘要： A method for making a turbine airfoil includes providing a mold core and an outer shell which cooperatively define a cavity in the shape of a hollow airfoil having an outer wall, a root, and a tip. A tip portion of the core extends completely through the portion of the cavity defining the tip of the airfoil. The core is restrained to prevent movement between the core and outer shell. Molten metal is introduced into the cavity and solidified to form an airfoil having at least one outer wall which defines an open tip and a hollow interior. A metallic tip cap is formed on the outer wall which substantially closes off the open tip. The tip cap may be formed by packing the airfoil with metallic powder; and laser sintering the exposed powder so as to form a tip cap which is metallurgically bonded to the outer wall.
摘要翻译：一种用于制造涡轮机翼的方法包括提供模具芯和外壳，其协作地限定具有外壁，根部和尖端的中空翼型形状的空腔。芯的尖端部分完全延伸穿过限定翼型的尖端的腔的部分。内芯被限制以防止芯和外壳之间的移动。将熔融金属引入空腔中并固化以形成具有至少一个限定开口尖端和中空内部的外壁的翼型件。在外壁上形成金属端盖，其基本上封闭开口尖端。顶盖可以通过用金属粉末包装翼型而形成; 并激光烧结暴露的粉末，以形成冶金结合到外壁的尖端盖。

6. 发明授权

US07784183B2 System and method for adjusting performance of manufacturing operations or steps 有权
标题翻译：用于调整制造操作或步骤性能的系统和方法
公开(公告)号：US07784183B2
公开(公告)日：2010-08-31
申请号：US11148191
申请日：2005-06-09
申请人： Todd Jay Rockstroh , James Joseph Hoffman
发明人： Todd Jay Rockstroh , James Joseph Hoffman
IPC分类号： B21D53/78 , B21K25/00 , B23P19/00 , B23P23/00
CPC分类号： B23P15/02 , B23P2700/06 , F01D5/18 , F01D25/00 , F05D2230/00 , G05B19/4099 , G05B2219/35198 , G05B2219/45147 , Y02T50/676 , Y10T29/4932 , Y10T29/49336 , Y10T29/49337 , Y10T29/49341 , Y10T29/5136 , Y10T29/52 , Y10T29/53048
摘要： A manufacturing system and manufacturing method for adjusting the performance of manufacturing operations or steps in manufacturing components having three-dimensional external structural characteristics. An embodiment of the system broadly comprises: (a) a plurality of manufacturing operations for processing a component having three-dimensional external structural characteristics; (b) at least one analytical device for analyzing at least one characteristic of the component after the performance of one or more manufacturing operations to generate a component data set; (c) at least one data storage device for storing the generated component data sets and for providing at least a relevant portion of accumulated component data; and (d) a communication mechanism for transmitting at least a relevant portion of accumulated component data to one or more manufacturing operations so that the performance thereof can be adjusted in response to the transmitted portion of accumulated component data. An embodiment of the method broadly comprises the following steps: (a) providing a component having three-dimensional external structural characteristics; (b) providing at least a relevant portion of accumulated component data comprising at least two different component data sets; and (c) performing a manufacturing step on the component to provide a processed component, wherein the at least relevant portion of accumulated component data is used to adjust the manner in which the manufacturing step is performed.
摘要翻译：一种制造系统和制造方法，用于调整具有三维外部结构特征的制造部件的制造操作或步骤的性能。该系统的实施例广泛地包括：（a）用于处理具有三维外部结构特征的部件的多个制造操作; （b）至少一个用于在执行一个或多个制造操作之后分析所述部件的至少一个特征以产生部件数据组的分析装置; （c）至少一个数据存储装置，用于存储所生成的分量数据集，并提供至少累积分量数据的相关部分; 以及（d）用于将累积分量数据的至少相关部分的至少一个传送到一个或多个制造操作的通信机制，以便响应于所累积的分量数据的发送部分来调整其性能。该方法的一个实施例广泛地包括以下步骤：（a）提供具有三维外部结构特征的部件; （b）提供至少包括至少两个不同分量数据集的累积分量数据的相关部分; 以及（c）对所述部件执行制造步骤以提供处理部件，其中所述累积部件数据的所述至少相关部分用于调整所述制造步骤的执行方式。

7. 发明申请

US20090165988A1 TURBINE AIRFOIL CASTING METHOD 审中-公开
标题翻译：涡轮机气流铸造方法
公开(公告)号：US20090165988A1
公开(公告)日：2009-07-02
申请号：US11968022
申请日：2007-12-31
申请人： Todd Jay Rockstroh , Sudhir K. Tewari , Joseph Giancarlo Sabato , Donald Brett Desander , David Henry Abbott , Mark Douglas Gledhill
发明人： Todd Jay Rockstroh , Sudhir K. Tewari , Joseph Giancarlo Sabato , Donald Brett Desander , David Henry Abbott , Mark Douglas Gledhill
IPC分类号： B22D27/02 , B22D23/00
CPC分类号： F01D5/187 , B22C9/04 , B22C9/10 , F05D2230/211 , F05D2260/202 , F05D2260/2212
摘要： A method for making a turbine airfoil includes: (a) providing a mold having: (i) a core; (ii) an outer shell surrounding the core such that the core and the outer shell cooperatively define a cavity in the shape of an airfoil having at least one outer wall; and (iii) a core support extending from the core to the outer shell through a portion of the cavity that defines the at least one sidewall; (b) introducing molten metal alloy into the cavity and surrounding the core support; (c) solidifying the alloy to form an airfoil casting having at least one outer wall which has at least one core support opening passing therethrough; (d) removing the mold so as to expose the airfoil; and (e) sealing the at least one core support opening in the airfoil with a metal alloy metallurgically bonded to the at least one outer wall.
摘要翻译：一种用于制造涡轮机翼型的方法包括：（a）提供具有：（i）芯体的模具; （ii）围绕所述芯的外壳，使得所述芯和所述外壳协调地限定具有至少一个外壁的翼型形状的空腔; 和（iii）从所述芯延伸到所述外壳的芯支撑体，所述芯支撑件限定所述至少一个侧壁的所述空腔的一部分; （b）将熔融金属合金引入空腔并围绕核心支撑件; （c）固化合金以形成具有至少一个外壁的翼型铸件，所述至少一个外壁具有穿过其中的至少一个芯支撑开口; （d）去除模具以暴露翼型件; 和（e）用金属合金密封所述翼型件中的所述至少一个芯支撑开口，所述金属合金与所述至少一个外壁冶金结合。

8. 发明授权

US07097720B2 Lower fluence boundary laser shock peening 有权
标题翻译：低能量密度边界激光冲击硬化
公开(公告)号：US07097720B2
公开(公告)日：2006-08-29
申请号：US10426816
申请日：2003-04-30
申请人： Seetha Ramaiah Mannava , Todd Jay Rockstroh , William Woodrow Shepherd , Ian Francis Prentice , Thomas Froats Broderick
发明人： Seetha Ramaiah Mannava , Todd Jay Rockstroh , William Woodrow Shepherd , Ian Francis Prentice , Thomas Froats Broderick
IPC分类号： C21D1/04 , C21D1/09 , C21D1/10
CPC分类号： F01D5/286 , C21D10/005
摘要： A method for laser shock peening an article including laser shock peening a first area with at least one high fluence laser beam and laser shock peening a border area between the first area and a non-laser shock peened area of the article with at least one first low fluence laser beam. The border area may be laser shock peened with a second low fluence laser beam or more low fluence laser beams wherein the second low fluence laser beam and others have a lower fluence than the first low fluence laser beam. The border area may be laser shock peened with progressively lower fluence laser beams starting with the one first fluence laser beam wherein the progressively lower fluence laser beams are in order of greatest fluence to least fluence in a direction outwardly from the first area through the border area to the non-laser shock peened area.
摘要翻译：一种用于激光冲击硬化处理物品的方法，所述方法包括用至少一个高注量激光束激光冲击第一区域的激光冲击，以及用所述第一区域和所述第一区域和所述第一区域之间的至少一个第一区域激光冲击所述第一区域和所述制品的非激光冲击硬化区域之间的边界区域低能量激光束。边界区域可以是用第二低注量激光束或更低的能量密度激光束进行激光冲击喷丸，其中第二低注量激光束和其它激光束具有比第一低注量激光束更低的能量密度。边界区域可以是激光冲击喷丸，其中以一个第一注量激光束开始逐渐降低的注量激光束，其中逐渐更低的注量激光束按照最小注量的顺序，在从第一区域通过边界区域向外的方向上的最小注量到非激光冲击硬化区域。

9. 发明授权

US06570126B2 Simultaneous offset dual sided laser shock peening using low energy laser beams 失效
公开(公告)号：US06570126B2
公开(公告)日：2003-05-27
申请号：US09945191
申请日：2001-08-31
申请人： Ui Won Suh , Seetharamaiah Mannava , Todd Jay Rockstroh
发明人： Ui Won Suh , Seetharamaiah Mannava , Todd Jay Rockstroh
IPC分类号： B23K2600
CPC分类号： C21D10/005 , F01D5/286
摘要： A method for laser shock peening an article by simultaneously firing low energy first and second laser beams to form pairs of longitudinally spaced apart first and second laser shock peened spots that are on opposite sides of the article, simultaneously laser shock peened, and transversely offset from each other. Each of the low energy first and second laser beams having a level of energy of between 1-10 joules.

10. 发明申请

US20090313823A1 IMPARTING DEEP COMPRESSIVE RESIDUAL STRESSES INTO A GAS TURBINE ENGINE AIRFOIL PERIPHERAL REPAIR WELDMENT 审中-公开
标题翻译：将深层压缩残余应力引入气体涡轮发动机气翼外围修复维修
公开(公告)号：US20090313823A1
公开(公告)日：2009-12-24
申请号：US12144940
申请日：2008-06-24
申请人： Todd Jay Rockstroh , Seetha Ramaiah Mannava , Roger Owen Barbe
发明人： Todd Jay Rockstroh , Seetha Ramaiah Mannava , Roger Owen Barbe
IPC分类号： B23P6/00
CPC分类号： B23P9/02 , B23P6/007 , B23P9/04 , C21D7/06 , C21D9/0068 , C21D10/005 , C21D2221/00 , F01D5/005 , F01D5/286 , F05D2230/10 , F05D2230/232 , F05D2230/90 , Y02T50/672 , Y02T50/673 , Y10T29/49318
摘要： A gas turbine engine airfoil is repaired by machining away airfoil material along at least a portion of at least one of leading and trailing edges and a radially outer tip forming at least one cut-back area and forming a weldment by welding successive beads of welding material into the cut-back area. Desired finished dimensions of the repaired airfoil are obtained by machining away some of the weld bead material in the weldment and then deep compressive residual stresses are imparted in a pre-stressed region extending into and encompassing the weldment and a portion of the airfoil adjacent the weldment. The compressive residual stresses may be are imparted after either rough machining or final finishing thereafter of the weldment. The cut-back area may extend up to about 90% of the airfoil's span and have a maximum cut-back depth up to about 0.22 inches.
摘要翻译：燃气涡轮发动机翼型件通过沿着前缘和后缘中的至少一个的至少一部分加工掉翼型材料和形成至少一个切割区域的径向外部尖端进行修复，并通过焊接连续的焊接材料珠形成焊件进入切割区域。修理的翼型件的期望成品尺寸通过机械加工焊接件中的一些焊缝材料而获得，然后在延伸到焊接件中并包围焊件的预应力区域中施加深度的压缩残余应力，并且靠近焊件的翼型件的一部分。可以在焊接后的粗加工或最终精加工之后赋予压缩残余应力。切割区域可以延伸至翼型跨度的大约90％，并且具有最大约为0.22英寸的切割深度。

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