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1. 发明授权

US09109873B1 Apparatus and method for inspecting a turbine blade tip shroud 有权
标题翻译：用于检查涡轮叶片尖端护罩的装置和方法
公开(公告)号：US09109873B1
公开(公告)日：2015-08-18
申请号：US13425461
申请日：2012-03-21
申请人： Gareth Lewis , John David Ward, Jr.
发明人： Gareth Lewis , John David Ward, Jr.
IPC分类号： G01B3/14 , G01B3/20 , G01B5/00
CPC分类号： G01B3/14 , G01B3/20 , G01B5/00
摘要： An apparatus for inspecting a tip shroud includes a frame having top and bottom surfaces. A first stop is connected to the bottom surface to contact a first side surface of the tip shroud, and a second stop is in sliding engagement with the frame to contact a second side surface of the tip shroud. A method for inspecting a tip shroud includes placing an apparatus against the tip shroud, wherein the apparatus has a first stop connected to a frame and a second stop in sliding engagement with the frame. The method further includes engaging the first stop with a first side surface of the tip shroud and sliding the second stop with respect to the frame until the second stop contacts a second side surface of the tip shroud.
摘要翻译：用于检查尖端护罩的装置包括具有顶表面和底表面的框架。第一止动件连接到底表面以接触尖端护罩的第一侧表面，并且第二止挡件与框架滑动接合以接触尖端护罩的第二侧表面。用于检查尖端护罩的方法包括将装置放置在尖端护罩上，其中该装置具有连接到框架的第一止动件和与框架滑动接合的第二止动件。该方法还包括使第一止动件与尖端护罩的第一侧表面接合并且使第二止动件相对于框架滑动，直到第二止挡件接触尖端护罩的第二侧表面。

2. 发明授权

US09033669B2 Rotating airfoil component with platform having a recessed surface region therein 有权
标题翻译：具有其中具有凹入表面区域的平台的旋转翼型件
公开(公告)号：US09033669B2
公开(公告)日：2015-05-19
申请号：US13524026
申请日：2012-06-15
申请人： Sheo Narain Giri , Harish Bommanakatte , Mohankumar Banakar , John David Ward, Jr. , Jonathan Matthew Lomas
发明人： Sheo Narain Giri , Harish Bommanakatte , Mohankumar Banakar , John David Ward, Jr. , Jonathan Matthew Lomas
IPC分类号： F01D5/14
CPC分类号： F01D5/143 , F01D5/147 , F05D2240/80
摘要： A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform.
摘要翻译：涡轮机的旋转翼型部件，其中部件具有在部件的翼展方向上对齐的翼型，柄以及横向于翼展方向定向的平台。平台具有邻近翼型的外径向表面，以及限定在其外径向表面中的至少一个凹陷区域。凹陷区域从包含在凹陷区域的上游和下游的外部径向表面的部分的平台平面相对于翼展方向延伸。凹陷区域与平台的端壁邻接并从其向翼型延伸。凹陷区域限定了边界由平台平面包围的表面形状，并且具有从端壁向翼型延伸的轮廓形状。凹陷区域的尺寸和形状可以增加平台的刚度。

3. 发明授权

US07493809B1 Method and system for measuring deformation in turbine blades 有权
标题翻译：测量涡轮叶片变形的方法和系统
公开(公告)号：US07493809B1
公开(公告)日：2009-02-24
申请号：US11867619
申请日：2007-10-04
申请人： John David Ward, Jr.
发明人： John David Ward, Jr.
IPC分类号： G01M19/00
CPC分类号： G01M5/0016
摘要： Disclosed is a method for measuring deformation of a turbine blade, the method including identifying at least one measuring point disposed on the turbine blade, retaining information pertaining to a first position of the at least one measuring point, operating the turbine blade over a period of time, measuring a spatial distance traveled by the at least one measuring point after the operating of the turbine blade over the period of time, the spatial distance being measured relative to the first position of the at least one measuring point; and determining an amount of deformation in the blade based on the measuring of the spatial distance.
摘要翻译：公开了一种用于测量涡轮叶片的变形的方法，该方法包括识别设置在涡轮叶片上的至少一个测量点，保持关于至少一个测量点的第一位置的信息，在涡轮叶片的一段时间，测量所述涡轮叶片在一段时间内操作之后由所述至少一个测量点行进的空间距离，所述空间距离是相对于所述至少一个测量点的第一位置被测量的; 以及基于所述空间距离的测量来确定所述叶片中的变形量。

4. 发明申请

US20130180107A1 METHOD FOR REFURBISHING A TURBO-MACHINE COMPONENT 审中-公开
标题翻译：一种涡轮机组件的改造方法
公开(公告)号：US20130180107A1
公开(公告)日：2013-07-18
申请号：US13350782
申请日：2012-01-15
申请人： Steven Charles Woods , John David Ward, JR. , Antonio Rodriguez
发明人： Steven Charles Woods , John David Ward, JR. , Antonio Rodriguez
IPC分类号： B23P6/00
CPC分类号： F01D5/005 , B23P6/002 , Y10T29/49318
摘要： A method for preparing to refurbish a turbo-machine component includes virtually refurbishing the turbo-machine component, actually refurbishing the turbo-machine component, and comparing the virtually refurbished turbo-machine component to the actually refurbished turbo-machine component.
摘要翻译：准备翻新涡轮机部件的方法包括：实际上翻新涡轮机部件，实际上翻新涡轮机部件，以及将实际翻新的涡轮机部件与实际翻新的涡轮机部件进行比较。

5. 发明授权

US09851279B2 Methods for determining strain on turbine components using traversable strain sensor readers 有权
公开(公告)号：US09851279B2
公开(公告)日：2017-12-26
申请号：US14633597
申请日：2015-02-27
申请人： Gregory Lee Hovis , John David Ward, Jr. , William Farris Ranson
发明人： Gregory Lee Hovis , John David Ward, Jr. , William Farris Ranson
IPC分类号： G01M15/02 , G01B21/32 , F01D17/04
CPC分类号： G01M15/02 , F01D17/04 , G01B21/32
摘要： Traversable strain sensor readers for reading a plurality strain sensor reference features on a turbine component include a traversing system configured to traverse the traversable strain sensor reader along at least a portion of the turbine component, and a reader configured to read at least a portion of the plurality of strain sensor reference features while the traversing system traverses the traversable strain sensor reader along at least the portion of the turbine component.

6. 发明申请

US20130336801A1 ROTATING AIRFOIL COMPONENT WITH PLATFORM HAVING A RECESSED SURFACE REGION THEREIN 有权
标题翻译：带有平台的旋转空气动力部件具有一个残留的表面区域
公开(公告)号：US20130336801A1
公开(公告)日：2013-12-19
申请号：US13524026
申请日：2012-06-15
申请人： Sheo Narain Giri , Harish Bommanakatte , Mohankumar Banakar , John David Ward, JR. , Jonathan Matthew Lomas
发明人： Sheo Narain Giri , Harish Bommanakatte , Mohankumar Banakar , John David Ward, JR. , Jonathan Matthew Lomas
IPC分类号： F01D5/14
CPC分类号： F01D5/143 , F01D5/147 , F05D2240/80
摘要： A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform.
摘要翻译：涡轮机的旋转翼型部件，其中部件具有在部件的翼展方向上对齐的翼型，柄以及横向于翼展方向定向的平台。平台具有邻近翼型的外径向表面，以及限定在其外径向表面中的至少一个凹陷区域。凹陷区域从包含在凹陷区域的上游和下游的外部径向表面的部分的平台平面相对于翼展方向延伸。凹陷区域与平台的端壁邻接并从其向翼型延伸。凹陷区域限定了边界由平台平面包围的表面形状，并且具有从端壁向翼型延伸的轮廓形状。凹陷区域的尺寸和形状可以增加平台的刚度。

7. 发明申请

US20160252427A1 METHODS FOR DETERMINING STRAIN ON TURBINE COMPONENTS USING TRAVERSABLE STRAIN SENSOR READERS 有权
标题翻译：使用可转移应变传感器读数器确定涡轮机组件应变的方法
公开(公告)号：US20160252427A1
公开(公告)日：2016-09-01
申请号：US14633597
申请日：2015-02-27
申请人： Gregory Lee Hovis , John David Ward, JR. , William Farris Ranson
发明人： Gregory Lee Hovis , John David Ward, JR. , William Farris Ranson
IPC分类号： G01M15/02
CPC分类号： G01M15/02 , F01D17/04 , G01B21/32
摘要： Traversable strain sensor readers for reading a plurality strain sensor reference features on a turbine component include a traversing system configured to traverse the traversable strain sensor reader along at least a portion of the turbine component, and a reader configured to read at least a portion of the plurality of strain sensor reference features while the traversing system traverses the traversable strain sensor reader along at least the portion of the turbine component.
摘要翻译：用于读取涡轮机部件上的多个应变传感器参考特征的可移动应变传感器读取器包括构造成沿着涡轮机部件的至少一部分横越可穿过应变传感器读取器的横动系统，以及被配置为读取至少一部分多个应变传感器参考特征，而横向系统沿着涡轮机部件的至少部分横穿可移动应变传感器读取器。

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