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公开(公告)号：US20090038151A1
公开(公告)日：2009-02-12
申请号：US11835452
申请日：2007-08-08
Applicant: Ephraim C. Davis , Christopher J. Bischof
Inventor： Ephraim C. Davis , Christopher J. Bischof
IPC: B23P15/02
CPC classification number: B23P6/002 , F01D5/005 , F05D2230/80 , F05D2260/94 , F05D2270/44 , Y10T29/49318 , Y10T29/49336 , Y10T29/49718 , Y10T29/49725 , Y10T29/49771
Abstract: A method for use in repairing gas turbine engine components includes applying a stress to a first gas turbine engine component to cause surface cracking on the first gas turbine engine component and establishing a location of an elevated stress region of a second gas turbine engine component based upon the location of the surface cracking on the first gas turbine engine component.
Abstract translation: 一种用于修复燃气涡轮发动机部件的方法包括：向第一燃气涡轮发动机部件施加应力以在第一燃气涡轮发动机部件上引起表面开裂，并且基于第二燃气涡轮发动机部件的升高的应力区域的位置，基于 在第一燃气涡轮发动机部件上的表面开裂的位置。
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公开(公告)号：US08291589B2
公开(公告)日：2012-10-23
申请号：US11835452
申请日：2007-08-08
Applicant: Ephraim C. Davis , Christopher J. Bischof
Inventor： Ephraim C. Davis , Christopher J. Bischof
CPC classification number: B23P6/002 , F01D5/005 , F05D2230/80 , F05D2260/94 , F05D2270/44 , Y10T29/49318 , Y10T29/49336 , Y10T29/49718 , Y10T29/49725 , Y10T29/49771
Abstract: A method for use in repairing gas turbine engine components includes applying a stress to a first gas turbine engine component to cause surface cracking on the first gas turbine engine component and establishing a location of an elevated stress region of a second gas turbine engine component based upon the location of the surface cracking on the first gas turbine engine component.
Abstract translation: 一种用于修复燃气涡轮发动机部件的方法包括：向第一燃气涡轮发动机部件施加应力以在第一燃气涡轮发动机部件上引起表面开裂，并且基于第二燃气涡轮发动机部件的升高的应力区域的位置，基于 在第一燃气涡轮发动机部件上的表面开裂的位置。
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3.发明授权Method for developing a repair process to correct a deformed gas turbine engine component 有权用于开发修复过程以校正变形的燃气涡轮发动机部件的方法公开(公告)号：US07970555B2
公开(公告)日：2011-06-28
申请号：US12082865
申请日：2008-04-15
Applicant: Garrett Kernozicky , Ephraim C. Davis , Thomas P. Cap
Inventor： Garrett Kernozicky , Ephraim C. Davis , Thomas P. Cap
CPC classification number: B23P6/002 , F01D5/005 , F05D2260/80 , Y02T50/673 , Y10T29/49318
Abstract: A method of developing a repair process for a gas turbine engine component deformed during engine operation includes determining peak stress locations in a model of the component, applying loads to sample components based on the model to produce geometrical correction values in the samples, generating data from the samples including the loads applied and the geometrical correction values produced, destructively analyzing the samples at the peak stress locations for structural imperfections, and correlating the loads applied to the geometrical correction values produced to determine allowable loads necessary to produce target geometrical correction values in a used component substantially free of structural imperfections.
Abstract translation: 在发动机运行过程中对于燃气涡轮发动机部件发生变形的修复过程的方法包括：确定部件模型中的峰值应力位置，基于该模型对载荷施加到采样部件，以产生样本中的几何校正值， 包括施加的载荷和所产生的几何校正值的样本，破坏性地分析在峰值应力位置处的结构缺陷的样品，并且将施加到所产生的几何校正值的载荷相关联，以确定产生目标几何校正值所需的允许载荷 使用的组分基本上没有结构缺陷。
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Patent Agency Ranking
公开(公告)号：US20090255307A1
公开(公告)日：2009-10-15
申请号：US12082896
申请日：2008-04-15
Applicant: Ephraim C. Davis , Bryan G. Parrette , Larry D. Cronin
Inventor： Ephraim C. Davis , Bryan G. Parrette , Larry D. Cronin
CPC classification number: F01D5/005 , B23P6/002 , Y02T50/673 , Y10T29/53704 , Y10T29/53796 , Y10T29/5387 , Y10T29/53961 , Y10T29/53978 , Y10T29/53996
Abstract: A tool for correcting the twist angle of a turbine blade includes an adaptor configured to engage a tip of the blade, a socket drive configured to engage the adaptor, a first handle connected to a first side of the socket drive, a second handle connected to a second side of the socket drive, and a torque gauge configured to measure a load applied to the blade.
Abstract translation: 用于校正涡轮机叶片的扭转角度的工具包括配置成接合刀片的尖端的适配器，被配置为接合适配器的插座驱动器，连接到插座驱动器的第一侧的第一手柄，连接到 插座驱动器的第二侧和配置成测量施加到叶片的负载的扭矩计。
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公开(公告)号：US08127581B2
公开(公告)日：2012-03-06
申请号：US12082896
申请日：2008-04-15
Applicant: Ephraim C. Davis , Bryan G. Parrette , Larry D. Cronin
Inventor： Ephraim C. Davis , Bryan G. Parrette , Larry D. Cronin
CPC classification number: F01D5/005 , B23P6/002 , Y02T50/673 , Y10T29/53704 , Y10T29/53796 , Y10T29/5387 , Y10T29/53961 , Y10T29/53978 , Y10T29/53996
Abstract: A tool for correcting the twist angle of a turbine blade includes an adaptor configured to engage a tip of the blade, a socket drive configured to engage the adaptor, a first handle connected to a first side of the socket drive, a second handle connected to a second side of the socket drive, and a torque gauge configured to measure a load applied to the blade.
Abstract translation: 用于校正涡轮机叶片的扭转角度的工具包括配置成接合刀片的尖端的适配器，被配置为接合适配器的插座驱动器，连接到插座驱动器的第一侧的第一手柄，连接到 插座驱动器的第二侧和配置成测量施加到叶片的负载的扭矩计。
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6.发明申请Method for developing a repair process to correct a deformed gas turbine engine component 有权用于开发修复过程以校正变形的燃气涡轮发动机部件的方法公开(公告)号：US20090255115A1
公开(公告)日：2009-10-15
申请号：US12082865
申请日：2008-04-15
Applicant: Garrett Kernozicky , Ephraim C. Davis , Thomas P. Cap
Inventor： Garrett Kernozicky , Ephraim C. Davis , Thomas P. Cap
IPC: B23P6/00
CPC classification number: B23P6/002 , F01D5/005 , F05D2260/80 , Y02T50/673 , Y10T29/49318
Abstract: A method of developing a repair process for a gas turbine engine component deformed during engine operation includes determining peak stress locations in a model of the component, applying loads to sample components based on the model to produce geometrical correction values in the samples, generating data from the samples including the loads applied and the geometrical correction values produced, destructively analyzing the samples at the peak stress locations for structural imperfections, and correlating the loads applied to the geometrical correction values produced to determine allowable loads necessary to produce target geometrical correction values in a used component substantially free of structural imperfections.
Abstract translation: 在发动机运行过程中对于燃气涡轮发动机部件发生变形的修复过程的方法包括：确定部件模型中的峰值应力位置，基于该模型对载荷施加到采样部件，以产生样本中的几何校正值， 包括施加的载荷和所产生的几何校正值的样本，破坏性地分析在峰值应力位置处的结构缺陷的样品，并且将施加到所产生的几何校正值的载荷相关联，以确定产生目标几何校正值所需的允许载荷 使用的组分基本上没有结构缺陷。
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公开(公告)号：US08122601B2
公开(公告)日：2012-02-28
申请号：US12082864
申请日：2008-04-15
Applicant: Garrett Kernozicky , Ephraim C. Davis , Thomas P. Cap , Paul Balko
Inventor： Garrett Kernozicky , Ephraim C. Davis , Thomas P. Cap , Paul Balko
IPC: B23P6/00
CPC classification number: B23P6/002 , F01D5/005 , F05D2230/40 , F05D2230/50 , Y02T50/673 , Y10T29/49318 , Y10T29/49718
Abstract: A method of correcting a twist angle of a gas turbine engine blade includes measuring an existing twist angle of the blade, applying a first angular load to a first end of the blade; and measuring a repaired twist angle of the blade. The first angular load applied to the first end of the blade is based on an empirical correlation between a plurality of angular loads necessary to produce a plurality of twist angle correction values.
Abstract translation: 一种校正燃气涡轮发动机叶片的扭转角度的方法包括测量叶片的现有扭转角，向叶片的第一端施加第一角度载荷; 并测量刀片的修复扭转角度。 施加到叶片的第一端的第一角度载荷基于产生多个扭转角校正值所需的多个角度载荷之间的经验相关性。
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公开(公告)号：US20090255114A1
公开(公告)日：2009-10-15
申请号：US12082864
申请日：2008-04-15
Applicant: Garrett Kernozicky , Ephraim C. Davis , Thomas P. Cap , Paul Balko
Inventor： Garrett Kernozicky , Ephraim C. Davis , Thomas P. Cap , Paul Balko
IPC: B23P6/00
CPC classification number: B23P6/002 , F01D5/005 , F05D2230/40 , F05D2230/50 , Y02T50/673 , Y10T29/49318 , Y10T29/49718
Abstract: A method of correcting a twist angle of a gas turbine engine blade includes measuring an existing twist angle of the blade, applying a first angular load to a first end of the blade; and measuring a repaired twist angle of the blade. The first angular load applied to the first end of the blade is based on an empirical correlation between a plurality of angular loads necessary to produce a plurality of twist angle correction values.
Abstract translation: 一种校正燃气涡轮发动机叶片的扭转角度的方法包括测量叶片的现有扭转角，向叶片的第一端施加第一角度载荷; 并测量刀片的修复扭转角度。 施加到叶片的第一端的第一角度载荷基于产生多个扭转角校正值所需的多个角度载荷之间的经验相关性。
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