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1. 发明申请

US20110308290A1 METHOD FOR ULTRASONIC PEENING OF GAS TURBINE ENGINE COMPONENTS WITHOUT ENGINE DISASSEMBLY 审中-公开
标题翻译：无发动机拆卸的燃气轮机发动机组件超声波接合方法
公开(公告)号：US20110308290A1
公开(公告)日：2011-12-22
申请号：US13197877
申请日：2011-08-04
申请人： Billie W. Bunting , Leonard Paul Palmisano , Edward R. Brown , David R. Malley , David A. Rutz
发明人： Billie W. Bunting , Leonard Paul Palmisano , Edward R. Brown , David R. Malley , David A. Rutz
IPC分类号： C21D7/06
CPC分类号： B23P6/002 , B23P9/04 , C21D7/06
摘要： A method for peening a component of a gas turbine engine, or a module of a gas turbine engine, without removing the component from the assembled gas turbine engine or module includes blending the damaged area of the component, determining parameters for peening the damaged component, and peening the damaged component without removing it from the engine.
摘要翻译：一种用于喷射燃气涡轮发动机的部件或燃气涡轮发动机的组件而不从组装的燃气涡轮发动机或模块中移除部件的方法包括混合部件的损坏区域，确定用于硬化损坏部件的参数，并且将损坏的部件硬化，而不将其从发动机中取出。

2. 发明申请

US20090094829A1 Method for ultrasonic peening of gas turbine engine components without engine disassembly 审中-公开
标题翻译：无发动机拆卸的燃气涡轮发动机部件的超声波喷丸处理方法
公开(公告)号：US20090094829A1
公开(公告)日：2009-04-16
申请号：US11974581
申请日：2007-10-15
申请人： Billie W. Bunting , Leonard Paul Palmisano , Edward R. Brown , David R. Malley , David A. Rutz
发明人： Billie W. Bunting , Leonard Paul Palmisano , Edward R. Brown , David R. Malley , David A. Rutz
IPC分类号： B23P6/00 , C21D7/06
CPC分类号： B23P6/002 , C21D7/06 , Y10T29/49238
摘要： A method for peening a component of a gas turbine engine, or a module of a gas turbine engine, without removing the component from the assembled gas turbine engine or module includes blending the damaged area of the component, determining parameters for peening the damaged component, and peening the damaged component without removing it from the engine.
摘要翻译：一种用于喷射燃气涡轮发动机的部件或燃气涡轮发动机的组件而不从组装的燃气涡轮发动机或模块中移除部件的方法包括混合部件的损坏区域，确定用于硬化损坏部件的参数，并且将损坏的部件硬化，而不将其从发动机中取出。

3. 发明申请

US20080029500A1 Brazing repairs 审中-公开
标题翻译：钎焊维修
公开(公告)号：US20080029500A1
公开(公告)日：2008-02-07
申请号：US11497100
申请日：2006-08-01
申请人： David R. Malley , James J. Moor , David A. Rutz
发明人： David R. Malley , James J. Moor , David A. Rutz
IPC分类号： B23K26/00
CPC分类号： B23K1/0018 , B23K1/0056 , B23K2101/001
摘要： A first component is bulk brazed to a second component. The bulk braze joint is inspected. Responsive to the inspection locating a defect site, the joint is laser brazed at the defect site.
摘要翻译：第一个组件是批量钎焊到第二个组件。检查散装钎焊接头。响应于检查定位缺陷部位，关节在缺陷部位进行激光钎焊。

4. 发明授权

US4654091A Elimination of quench cracking in superalloy disks 失效
标题翻译：消除超合金盘中的淬火裂纹
公开(公告)号：US4654091A
公开(公告)日：1987-03-31
申请号：US417760
申请日：1982-09-13
申请人： David R. Malley
发明人： David R. Malley
IPC分类号： C22F1/10
CPC分类号： C22F1/10
摘要： Quench cracking of nickel base superalloy articles is avoided by plating the articles with a layer of nickel or similar metal prior to heat treatment.
摘要翻译：镍基超级合金制品的淬火裂纹可以通过在热处理之前用镍或类似金属层进行电镀来避免。

5. 发明授权

US4579602A Forging process for superalloys 失效
标题翻译：超合金锻造工艺
公开(公告)号：US4579602A
公开(公告)日：1986-04-01
申请号：US565487
申请日：1983-12-27
申请人： Daniel F. Paulonis , David R. Malley , Edgar E. Brown
发明人： Daniel F. Paulonis , David R. Malley , Edgar E. Brown
IPC分类号： C22C19/05 , B21J1/06 , B21J5/00 , B21K1/32 , B21K1/36 , C22F1/10
CPC分类号： C22F1/10 , B21J5/00 , B21K1/32
摘要： Forging processes are described for cast superalloys. The forgeability of superalloy materials is improved by the development of overaged microstructure. The total forging process is usually performed in a series of steps with intervening heat treatments to reform the overaged microstructure.
摘要翻译：锻造工艺描述为铸造超级合金。超合金材料的锻造可以通过发展过高的微结构而得到改善。总锻造过程通常采用一系列步骤进行，其中介入热处理以改变过度的微结构。

6. 发明授权

US08127442B2 Compressor blade flow form technique for repair 有权
标题翻译：压缩机叶片流动形式修复技术
公开(公告)号：US08127442B2
公开(公告)日：2012-03-06
申请号：US11303579
申请日：2005-12-15
申请人： John F. Mullooly , William M. Rose , David R. Malley , Monika D. Kinstler
发明人： John F. Mullooly , William M. Rose , David R. Malley , Monika D. Kinstler
IPC分类号： B23P6/00
CPC分类号： B23P6/007 , C23C4/01 , C23C4/18 , C23C10/04 , F01D5/005 , F05D2230/90 , F05D2300/611 , Y10T29/49318 , Y10T29/49336 , Y10T29/49732 , Y10T29/49734 , Y10T29/49746 , Y10T29/4975
摘要： A method for repairing a turbine engine component is provided. The method broadly comprises the steps of providing a turbine engine component having an airfoil portion, applying a coating to the airfoil portion, and restoring a tip portion, a chord, and surfaces of the airfoil portion to original dimensions in a single operation. A system for repairing the turbine engine component is also described.
摘要翻译：提供了一种用于修理涡轮发动机部件的方法。该方法广泛地包括以下步骤：提供具有翼型部分的涡轮发动机部件，在翼型部分上施加涂层，以及在一次操作中将翼尖部分，弦杆和翼型部分的表面恢复到原始尺寸。还描述了用于修理涡轮发动机部件的系统。

7. 发明申请

US20090320287A1 Compressor blade flow form technique for repair 有权
标题翻译：压缩机叶片流动形式修复技术
公开(公告)号：US20090320287A1
公开(公告)日：2009-12-31
申请号：US11303579
申请日：2005-12-15
申请人： John F. Mullooly , William M. Rose , David R. Malley , Monika D. Kinstler
发明人： John F. Mullooly , William M. Rose , David R. Malley , Monika D. Kinstler
IPC分类号： B23P6/00
CPC分类号： B23P6/007 , C23C4/01 , C23C4/18 , C23C10/04 , F01D5/005 , F05D2230/90 , F05D2300/611 , Y10T29/49318 , Y10T29/49336 , Y10T29/49732 , Y10T29/49734 , Y10T29/49746 , Y10T29/4975
摘要： A method for repairing a turbine engine component is provided. The method broadly comprises the steps of providing a turbine engine component having an airfoil portion, applying a coating to the airfoil portion, and restoring a tip portion, a chord, and surfaces of the airfoil portion to original dimensions in a single operation. A system for repairing the turbine engine component is also described.
摘要翻译：提供了一种用于修理涡轮发动机部件的方法。该方法广泛地包括以下步骤：提供具有翼型部分的涡轮发动机部件，在翼型部分上施加涂层，以及在一次操作中将翼尖部分，弦杆和翼型部分的表面恢复到原始尺寸。还描述了用于修理涡轮发动机部件的系统。

8. 发明申请

US20070283560A1 Enhanced weldability for high strength cast and wrought nickel superalloys 有权
标题翻译：增强高强度铸造和锻造镍超级合金的可焊性
公开(公告)号：US20070283560A1
公开(公告)日：2007-12-13
申请号：US11446991
申请日：2006-06-05
申请人： David R. Malley
发明人： David R. Malley
IPC分类号： B23P6/00 , B29C73/00 , B23P19/04
CPC分类号： B23K15/0093 , B23K9/173 , B23K9/23 , B23K9/235 , B23K15/0006 , B23K15/0033 , B23K2101/001 , B23K2103/26 , C22F1/10 , F01D5/005 , F05D2230/232 , Y10T29/49318 , Y10T29/49718 , Y10T29/49723 , Y10T29/49726 , Y10T29/49728 , Y10T29/49748 , Y10T29/4975
摘要： A method for repairing a turbine engine component comprises the steps of providing a turbine engine component formed from a nickel-based superalloy, removing any defects from the turbine engine component, the removing step comprising subjecting the turbine engine component to a solutioning heat treatment using a heating rate in the range of from 29 degrees Fahrenheit/minute to approximately 40 degrees Fahrenheit/minute as the component passes through a temperature in the range of from 1100 degrees Fahrenheit to 1600 degrees Fahrenheit, and welding the turbine engine component to effect the repair. A deliberately slow post-solution treatment cooling rate is used to substantially prevent weld cracks.
摘要翻译：一种用于修理涡轮发动机部件的方法包括以下步骤：提供由镍基超级合金形成的涡轮发动机部件，从涡轮发动机部件去除任何缺陷，所述移除步骤包括使涡轮发动机部件进行固溶热处理，使用当组件通过1100华氏度至1600华氏度的温度时，加热速率在29华氏度/分钟至约40华氏度/分钟的范围内，并且焊接涡轮发动机部件进行修理。使用故意缓慢的固溶后处理冷却速度来基本上防止焊缝裂纹。

9. 发明授权

US07244320B2 Methods for repairing gas turbine engine components 有权
标题翻译：修理燃气涡轮发动机部件的方法
公开(公告)号：US07244320B2
公开(公告)日：2007-07-17
申请号：US10858365
申请日：2004-06-01
申请人： David R. Malley , Carl E. Kelly , Robert P. Schaefer
发明人： David R. Malley , Carl E. Kelly , Robert P. Schaefer
IPC分类号： C22C30/00 , C21D1/70 , C22F1/16
CPC分类号： B23P6/005 , C21D9/50
摘要： Systems and methods for repairing Thermo-Span® gas turbine engine components are described herein. Embodiments of these methods minimize post-weld residual stresses in a weld repaired Thermo-Span® component by solution heat treating the component by heating the component to about 2000° F.±25° F., holding the component at about 2000° F.±25° F. for about one hour; and cooling the component to below about 700° F. at a rate equivalent to cooling in air; and precipitation heat treating the component by heating the component to about 1325° F.±25° F., holding the component at about 1325° F.±25° F. for about 8 hours, cooling the component to about 1150° F.±25° F. at a maximum rate of about 100° F./hour, holding the component at about 1150° F.±25° F. for about 8 hours, and cooling the component at a predetermined cooling rate. Dimensions of the fully-machined and weld repaired component are maintained during solution heat treating and precipitation heat treating via custom designed furnace tools.
摘要翻译：本文描述了用于修理Thermo-Span（R）燃气涡轮发动机部件的系统和方法。这些方法的实施例通过将组件加热至约2000°F±25°F，将组件保持在约2000°，通过对部件进行固溶热处理，使焊接修补的Thermo-Span（R）部件中的焊后残余应力最小化 F.±25°F约1小时; 并以相当于在空气中冷却的速率将组分冷却至约700°F以下; 并通过将组分加热至约1325°F±25°F进行沉淀热处理，将组分保持在约1325°F±25°F下约8小时，将组分冷却至约1150°F ±25°F，最大速率为约100°F /小时，将组分保持在约1150°F±25°F约8小时，并以预定的冷却速率冷却组分。在通过定制设计的炉具的固溶热处理和沉淀热处理期间，维持完全加工和焊接修补部件的尺寸。

10. 发明授权

US07854064B2 Enhanced weldability for high strength cast and wrought nickel superalloys 有权
标题翻译：增强高强度铸造和锻造镍超级合金的可焊性
公开(公告)号：US07854064B2
公开(公告)日：2010-12-21
申请号：US11446991
申请日：2006-06-05
申请人： David R. Malley
发明人： David R. Malley
IPC分类号： B23P6/00 , C22F1/10
CPC分类号： B23K15/0093 , B23K9/173 , B23K9/23 , B23K9/235 , B23K15/0006 , B23K15/0033 , B23K2101/001 , B23K2103/26 , C22F1/10 , F01D5/005 , F05D2230/232 , Y10T29/49318 , Y10T29/49718 , Y10T29/49723 , Y10T29/49726 , Y10T29/49728 , Y10T29/49748 , Y10T29/4975
摘要： A method for repairing a turbine engine component comprises the steps of providing a turbine engine component formed from a nickel-based superalloy, removing any defects from the turbine engine component, the removing step comprising subjecting the turbine engine component to a solutioning heat treatment using a heating rate in the range of from 29 degrees Fahrenheit/minute to approximately 40 degrees Fahrenheit/minute as the component passes through a temperature in the range of from 1100 degrees Fahrenheit to 1600 degrees Fahrenheit, and welding the turbine engine component to effect the repair. A deliberately slow post-solution treatment cooling rate is used to substantially prevent weld cracks.
摘要翻译：一种用于修理涡轮发动机部件的方法包括以下步骤：提供由镍基超级合金形成的涡轮发动机部件，从涡轮发动机部件去除任何缺陷，所述移除步骤包括使涡轮发动机部件进行固溶热处理，使用当组件通过1100华氏度至1600华氏度的温度时，加热速率在29华氏度/分钟至约40华氏度/分钟的范围内，并且焊接涡轮发动机部件进行修理。使用故意缓慢的固溶后处理冷却速度来基本上防止焊缝裂纹。

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