公开(公告)号：US20090260206A1

公开(公告)日：2009-10-22

申请号：US12372168

申请日：2009-02-17

申请人： Martin C. Gosling ,  Jefferson Davis ,  Yong Kang

发明人： Martin C. Gosling ,  Jefferson Davis ,  Yong Kang

IPC分类号： B23P6/00

CPC分类号： B23P6/002 ,  F01D5/005 ,  F05D2230/80 ,  Y10T29/37 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/49325 ,  Y10T29/49336 ,  Y10T29/49716 ,  Y10T29/49718 ,  Y10T29/53

摘要： A system and method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the system may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.

摘要翻译： 一种用于重新配置涡轮叶片段的翼型的系统和方法。 在至少一个实施例中，该系统可以用于矫直涡轮叶片段的翼型件以去除倾斜，扭转或翻倒，或其任何组合。 可以通过沿与涡轮叶片段的外护罩大致相切的方向向内护罩施加负载来使翼型矫直。 孔可以被切入机翼吸入侧，在外护罩的内侧，以便矫直过程。 在完成该过程之后，可以密封孔。

公开(公告)号：US07536783B2

公开(公告)日：2009-05-26

申请号：US11591908

申请日：2006-11-02

申请人： Jefferson Davis ,  Martin C. Gosling ,  Yong Kang

发明人： Jefferson Davis ,  Martin C. Gosling ,  Yong Kang

IPC分类号： B21D53/78 ,  B23P6/00

CPC分类号： F01D5/005 ,  B23P6/002 ,  F05D2230/80 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/4932 ,  Y10T29/49325 ,  Y10T29/49336 ,  Y10T29/49716 ,  Y10T29/49721

摘要： A method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the method may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by heating the airfoil to no more than 750 degrees F. while applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. The load is up to 6000 lbf. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.

摘要翻译： 一种用于重新配置涡轮叶片段的翼型的方法。 在至少一个实施例中，该方法可以用于矫直涡轮叶片段的翼型以去除倾斜，扭转或翻倒，或其任何组合。 通过将翼型件加热至不超过750华氏度，同时在与涡轮叶片段的外护罩大致相切的方向上向内护罩施加负载的情况下，翼型件可被矫直。 负载高达6000 lbf。 孔可以被切入机翼吸入侧，在外护罩的内侧，以便矫直过程。 在完成该过程之后，可以密封孔。

公开(公告)号：US07730756B2

公开(公告)日：2010-06-08

申请号：US12372168

申请日：2009-02-17

申请人： Martin C. Gosling ,  Jefferson Davis ,  Yong Kang

发明人： Martin C. Gosling ,  Jefferson Davis ,  Yong Kang

IPC分类号： B21D53/78 ,  B21D3/16 ,  B23P6/00

CPC分类号： B23P6/002 ,  F01D5/005 ,  F05D2230/80 ,  Y10T29/37 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/49325 ,  Y10T29/49336 ,  Y10T29/49716 ,  Y10T29/49718 ,  Y10T29/53

摘要： A system and method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the system may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.

摘要翻译： 一种用于重新配置涡轮叶片段的翼型的系统和方法。 在至少一个实施例中，该系统可以用于矫直涡轮叶片段的翼型件以去除倾斜，扭转或翻倒，或其任何组合。 可以通过沿与涡轮叶片段的外护罩大致相切的方向向内护罩施加负载来使翼型矫直。 孔可以被切入机翼吸入侧，在外护罩的内侧，以便矫直过程。 在完成该过程之后，可以密封孔。

公开(公告)号：US07503113B2

公开(公告)日：2009-03-17

申请号：US11249791

申请日：2005-10-13

申请人： Martin C. Gosling ,  Jefferson Davis ,  Yong Kang

发明人： Martin C. Gosling ,  Jefferson Davis ,  Yong Kang

IPC分类号： B21D53/78

CPC分类号： B23P6/002 ,  F01D5/005 ,  F05D2230/80 ,  Y10T29/37 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/49325 ,  Y10T29/49336 ,  Y10T29/49716 ,  Y10T29/49718 ,  Y10T29/53

摘要： A system and method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the system may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.

摘要翻译： 一种用于重新配置涡轮叶片段的翼型的系统和方法。 在至少一个实施例中，该系统可以用于矫直涡轮叶片段的翼型件以去除倾斜，扭转或翻倒，或其任何组合。 可以通过沿与涡轮叶片段的外护罩大致相切的方向向内护罩施加负载来使翼型矫直。 孔可以被切入机翼吸入侧，在外护罩的内侧，以便矫直过程。 在完成该过程之后，可以密封孔。

公开(公告)号：US20070084050A1

公开(公告)日：2007-04-19

申请号：US11591908

申请日：2006-11-02

申请人： Jefferson Davis ,  Martin Gosling ,  Yong Kang

发明人： Jefferson Davis ,  Martin Gosling ,  Yong Kang

IPC分类号： B21K21/16 ,  B23P19/04

CPC分类号： F01D5/005 ,  B23P6/002 ,  F05D2230/80 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/4932 ,  Y10T29/49325 ,  Y10T29/49336 ,  Y10T29/49716 ,  Y10T29/49721

摘要： A method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the method may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by heating the airfoil to no more than 750 degrees F. while applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. The load is up to 6000 lbf. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.

摘要翻译： 一种用于重新配置涡轮叶片段的翼型的方法。 在至少一个实施例中，该方法可以用于矫直涡轮叶片段的翼型以去除倾斜，扭转或翻倒，或其任何组合。 通过将翼型件加热至不超过750华氏度，同时在与涡轮叶片段的外护罩大致相切的方向上向内护罩施加负载的情况下，翼型件可被矫直。 负载高达6000 lbf。 孔可以被切入机翼吸入侧，在外护罩的内侧，以便矫直过程。 在完成该过程之后，可以密封孔。

公开(公告)号：US20070084048A1

公开(公告)日：2007-04-19

申请号：US11249791

申请日：2005-10-13

申请人： Martin Gosling ,  Jefferson Davis ,  Yong Kang

发明人： Martin Gosling ,  Jefferson Davis ,  Yong Kang

IPC分类号： B21K21/16 ,  B23P6/00

CPC分类号： B23P6/002 ,  F01D5/005 ,  F05D2230/80 ,  Y10T29/37 ,  Y10T29/49316 ,  Y10T29/49318 ,  Y10T29/49325 ,  Y10T29/49336 ,  Y10T29/49716 ,  Y10T29/49718 ,  Y10T29/53

摘要： A system and method for reconfiguring an airfoil of a turbine vane segment. In at least one embodiment, the system may be used to straighten an airfoil of a turbine vane segment to remove lean, twist, or racking, or any combination thereof. The airfoil may be straightened by applying a load to an inner shroud in a direction that is generally tangential to an outer shroud of the turbine vane segment. Orifices may be cut into the airfoil suction side, inboard of the outer shroud, to facilitate the straightening process. The orifices may be sealed upon completion of the process.

摘要翻译： 一种用于重新配置涡轮叶片段的翼型的系统和方法。 在至少一个实施例中，该系统可以用于矫直涡轮叶片段的翼型件以去除倾斜，扭转或翻倒，或其任何组合。 可以通过沿与涡轮叶片段的外护罩大致相切的方向向内护罩施加负载来使翼型矫直。 孔可以被切入机翼吸入侧，在外护罩的内侧，以便矫直过程。 在完成该过程之后，可以密封孔。

公开(公告)号：US06991843B2

公开(公告)日：2006-01-31

申请号：US10163169

申请日：2002-06-04

申请人： Luis Parellada Armela ,  Juan Sánchez ,  William Clune ,  Jefferson Davis ,  Christopher M. Gallant ,  Melissa Spezzafero ,  Mark A. Clarner ,  William L. Huber ,  David P. Kraus, Jr. ,  George A. Provost ,  Howard A. Kingsford ,  Michel Labrecque

发明人： Luis Parellada Armela ,  Juan Sánchez ,  William Clune ,  Jefferson Davis ,  Christopher M. Gallant ,  Melissa Spezzafero ,  Mark A. Clarner ,  William L. Huber ,  David P. Kraus, Jr. ,  George A. Provost ,  Howard A. Kingsford ,  Michel Labrecque

IPC分类号： B32B3/00

CPC分类号： B29C43/222 ,  A44B18/0049 ,  A44B18/0065 ,  A61F13/625 ,  B29C43/46 ,  B29C67/0044 ,  B29C2043/461 ,  B29C2043/465 ,  B29L2031/729 ,  Y10T24/2717 ,  Y10T24/2742 ,  Y10T24/2783 ,  Y10T24/2792 ,  Y10T428/24008 ,  Y10T428/24017 ,  Y10T428/24182

摘要： A method of forming a fastener is provided, including (a) forming, from a thermoformable material, a preform product having a sheet-form base and an array of preform stems integrally molded with and extending from the base to corresponding terminal ends; (b) heating the terminal ends of the stems to a predetermined softening temperature, while maintaining the sheet-form base and a lower portion of each stem at a temperature lower than the softening temperature; and (c) contacting the terminal ends with a contact surface that is at a predetermined forming temperature, lower than the softening temperature, to deform the terminal ends to form heads therefrom that overhang the sheet-form base. Fasteners and other methods of forming them are also provided.

公开(公告)号：US20050091805A1

公开(公告)日：2005-05-05

申请号：US11005185

申请日：2004-12-06

申请人： Luis Armela ,  Juan Sanchez ,  William Clune ,  Jefferson Davis ,  Christopher Gallant ,  Melissa Spezzafero ,  Mark Clarner ,  William Huber ,  David Kraus ,  George Provost ,  Howard Kingsford ,  Michel Labrecque

发明人： Luis Armela ,  Juan Sanchez ,  William Clune ,  Jefferson Davis ,  Christopher Gallant ,  Melissa Spezzafero ,  Mark Clarner ,  William Huber ,  David Kraus ,  George Provost ,  Howard Kingsford ,  Michel Labrecque

IPC分类号： A44B18/00 ,  A61F13/62 ,  B29C43/22 ,  B29C67/00 ,  A44B1/04

CPC分类号： B29C43/222 ,  A44B18/0049 ,  A44B18/0065 ,  A61F13/625 ,  B29C43/46 ,  B29C67/0044 ,  B29C2043/461 ,  B29C2043/465 ,  B29L2031/729 ,  Y10T24/2717 ,  Y10T24/2742 ,  Y10T24/2783 ,  Y10T24/2792 ,  Y10T428/24008 ,  Y10T428/24017 ,  Y10T428/24182

摘要： A method of forming a fastener is provided, including (a) forming, from a thermoformable material, a preform product having a sheet-form base and an array of preform stems integrally molded with and extending from the base to corresponding terminal ends; (b) heating the terminal ends of the stems to a predetermined softening temperature, while maintaining the sheet-form base and a lower portion of each stem at a temperature lower than the softening temperature; and (c) contacting the terminal ends with a contact surface that is at a predetermined forming temperature, lower than the softening temperature, to deform the terminal ends to form heads therefrom that overhang the sheet-form base. Fasteners and other methods of forming them are also provided.

摘要翻译： 提供了一种形成紧固件的方法，包括（a）从可热成型材料形成具有片状基底和与基底整体模塑并从基底延伸到相应末端的预成型体棒阵列的预制品; （b）将茎的末端加热至预定的软化温度，同时将片状基底和每个茎的下部保持在低于软化温度的温度; 和（c）使终端与接触表面接触，所述接触表面处于低于软化温度的预定的形成温度，以使端部端部变形，从而形成从其延伸到片状基底的头部。 还提供了紧固件和其它形成方法。

公开(公告)号：USRE42475E1

公开(公告)日：2011-06-21

申请号：US12610534

申请日：2009-11-02

申请人： Luis Parellada Armela ,  Juan Sanchez ,  William P. Clune ,  Jefferson Davis ,  Christopher M. Gallant ,  Melissa Spezzafero ,  Mark A. Clarner ,  William L. Huber ,  David P. Kraus, Jr. ,  George A. Provost ,  Howard A. Kingsford ,  Michel Labrecque

发明人： Luis Parellada Armela ,  Juan Sanchez ,  William P. Clune ,  Jefferson Davis ,  Christopher M. Gallant ,  Melissa Spezzafero ,  Mark A. Clarner ,  William L. Huber ,  David P. Kraus, Jr. ,  George A. Provost ,  Howard A. Kingsford ,  Michel Labrecque

IPC分类号： B32B3/00

CPC分类号： A44B18/0049 ,  A44B18/0065 ,  A61F13/625 ,  B29C43/222 ,  B29C67/0044 ,  B29C2043/465 ,  B29L2031/729 ,  Y10T24/27 ,  Y10T24/2792 ,  Y10T428/24008 ,  Y10T428/24182

摘要： A method of forming a fastener is provided, including (a) forming, from a thermoformable material, a preform product having a sheet-form base and an array of preform stems integrally molded with and extending from the base to corresponding terminal ends; (b) heating the terminal ends of the stems to a predetermined softening temperature, while maintaining the sheet-form base and a lower portion of each stem at a temperature lower than the softening temperature; and (c) contacting the terminal ends with a contact surface that is at a predetermined forming temperature, lower than the softening temperature, to deform the terminal ends to form heads therefrom that overhang the sheet-form base. Fasteners and other methods of forming them are also provided.

摘要翻译： 提供了一种形成紧固件的方法，包括（a）从可热成型材料形成具有片状基底和与基底整体模塑并从基底延伸到相应末端的预成型体棒阵列的预制品; （b）将茎的末端加热至预定的软化温度，同时将片状基底和每个茎的下部保持在低于软化温度的温度; 和（c）使终端与接触表面接触，所述接触表面处于低于软化温度的预定的形成温度，以使端部端部变形，从而形成从其延伸到片状基底的头部。 还提供了紧固件和其它形成方法。

公开(公告)号：US08545740B2

公开(公告)日：2013-10-01

申请号：US13288343

申请日：2011-11-03

申请人： Christopher M. Gallant ,  Mark A. Clarner ,  Derrick Slowikowski ,  Jefferson Davis ,  Wallace L. Kurtz, Jr.

发明人： Christopher M. Gallant ,  Mark A. Clarner ,  Derrick Slowikowski ,  Jefferson Davis ,  Wallace L. Kurtz, Jr.

IPC分类号： B29C67/00

CPC分类号： A44B18/0003 ,  A61F13/625 ,  B65D33/24 ,  B65D2313/02 ,  Y10T24/15 ,  Y10T24/27 ,  Y10T24/2708 ,  Y10T24/2733 ,  Y10T24/2775 ,  Y10T24/2792 ,  Y10T428/24017

摘要： The present disclosure provides embodiments of a releasable fastening arrangement that can include a first fastening strip secured to and extending over a substrate surface and having a first surface carrying first fastening elements extending from the surface. The releasable fastening arrangement can also include a second fastening strip having a second surface carrying second fastening elements that are engageable by the first fastening elements to form a releasable fastening. The first surface can include a flexible flap that is formed therein, and that is surrounded by other portions of the first surface. The flap can carry at least one of the first fastening elements, and can flap have a distal edge that is displaceable from the substrate surface under peel loads applied to the at least one first fastening element carried by the flap.

摘要翻译： 本公开提供了可释放紧固装置的实施例，其可以包括固定到衬底表面上并在衬底表面上延伸的第一紧固条，并且具有承载从表面延伸的第一紧固元件的第一表面。 可释放的紧固装置还可以包括第二紧固带，其具有承载第二紧固元件的第二表面，第二紧固元件可由第一紧固元件接合以形成可释放的紧固件。 第一表面可以包括形成在其中并且被第一表面的其它部分包围的柔性折板。 翼片可以承载第一紧固元件中的至少一个，并且翼片具有远离边缘，所述远侧边缘在施加到由翼片承载的至少一个第一紧固元件的剥离载荷下可从基底表面移位。