公开(公告)号：US08515711B2

公开(公告)日：2013-08-20

申请号：US12909194

申请日：2010-10-21

申请人： David J. Mitchell ,  Ramesh Subramanian ,  Nancy H. Ulerich ,  Paul J. Zombo

发明人： David J. Mitchell ,  Ramesh Subramanian ,  Nancy H. Ulerich ,  Paul J. Zombo

IPC分类号： G06F11/30 ,  G06F11/00

CPC分类号： F01D21/003 ,  F05D2260/80 ,  Y02T50/67

摘要： A diagnostic system and method for monitoring operating conditions of turbine machine components (18, 19, 22, 23) that comprise one or more non-contact sensors (24, 31) that detect an operating condition of a turbine component (18, 19, 22, 23) over a defined region of the component. In addition, point sensors (50) are provided that detect and monitor the same operating condition within the defined region. Data generated from the point sensor (50) is used to calibrate the non-contact sensor (24, 31) and the data generated by the non-contact sensor (24, 31).

摘要翻译： 一种用于监测涡轮机组件（18,19,22,23）的操作条件的诊断系统和方法，所述操作条件包括一个或多个非接触式传感器（24,31），其检测涡轮机部件（18,19， 22,23）在部件的限定区域上。 此外，提供了点传感器（50），其检测并监视在限定区域内的相同操作条件。 从点传感器（50）产生的数据用于校准非接触式传感器（24,31）和由非接触传感器（24,31）产生的数据。

公开(公告)号：US20120101775A1

公开(公告)日：2012-04-26

申请号：US12909194

申请日：2010-10-21

申请人： David J. Mitchell ,  Ramesh Subramanian ,  Nancy H. Ulerich ,  Paul J. Zombo

发明人： David J. Mitchell ,  Ramesh Subramanian ,  Nancy H. Ulerich ,  Paul J. Zombo

IPC分类号： G06F15/00

CPC分类号： F01D21/003 ,  F05D2260/80 ,  Y02T50/67

摘要： A diagnostic system and method for monitoring operating conditions of turbine machine components (18, 19, 22, 23) that comprise one or more non-contact sensors (24, 31) that detect an operating condition of a turbine component (18, 19, 22, 23) over a defined region of the component. In addition, point sensors (50) are provided that detect and monitor the same operating condition within the defined region. Data generated from the point sensor (50) is used to calibrate the non-contact sensor (24, 31) and the data generated by the non-contact sensor (24, 31).

摘要翻译： 一种用于监测涡轮机组件（18,19,22,23）的操作条件的诊断系统和方法，所述操作条件包括一个或多个非接触式传感器（24,31），其检测涡轮机部件（18,19， 22,23）在部件的限定区域上。 此外，提供了点传感器（50），其检测并监视在限定区域内的相同操作条件。 从点传感器（50）产生的数据用于校准非接触式传感器（24,31）和由非接触传感器（24,31）产生的数据。

公开(公告)号：US20120034097A1

公开(公告)日：2012-02-09

申请号：US12850147

申请日：2010-08-04

申请人： John J. Marra ,  Paul J. Zombo

发明人： John J. Marra ,  Paul J. Zombo

IPC分类号： F01D5/14 ,  G01M15/14

CPC分类号： F01D5/141 ,  B22C9/04 ,  B22C9/10 ,  F01D5/147 ,  F01D21/003 ,  F05D2250/182

摘要： A turbine airfoil can be formed with features to facilitate measurement of its wall thickness. An outer wall of the airfoil can include an outer surface and an inner surface. The outer surface of the airfoil can have an outer inspection target surface, and the inner surface of the airfoil can have an inner inspection target surface. The inner and outer target surfaces can define substantially flat regions in surfaces that are otherwise highly contoured. The inner and outer inspection target surfaces can be substantially aligned with each other. The inner and outer target surfaces can be substantially parallel to each other. As a result of these arrangements, a highly accurate measurement of wall thickness can be obtained. In one embodiment, the outer inspection target surface can be defined by an innermost surface of a groove formed in the outer surface of the outer wall of the airfoil.

摘要翻译： 涡轮机翼型可以形成有特征以便于测量其壁厚。 翼型件的外壁可以包括外表面和内表面。 翼型件的外表面可以具有外部检查目标表面，并且翼型件的内表面可以具有内部检查目标表面。 内外目标表面可以在表面上限定基本上平坦的区域，否则高度轮廓。 内部和外部检查目标表面可以基本上彼此对准。 内外目标表面可以基本上彼此平行。 作为这些布置的结果，可以获得高精度的壁厚测量。 在一个实施例中，外部检查目标表面可以由形成在翼型件的外壁的外表面中的凹槽的最内表面限定。

公开(公告)号：US06193141B1

公开(公告)日：2001-02-27

申请号：US09558131

申请日：2000-04-25

申请人： Michael A. Burke ,  Paul J. Zombo

发明人： Michael A. Burke ,  Paul J. Zombo

IPC分类号： B23K3102

CPC分类号： F01D5/005 ,  B23K20/023 ,  B23K20/16 ,  B23K35/004 ,  B23K35/3033 ,  B23K2101/001 ,  B23P15/04 ,  Y10T29/4932 ,  Y10T29/49336

摘要： A method of bonding together at least two long, metal alloy segments, of turbine components, such as turbine blade segments (18, 19, 20 and 21) by: putting a melting point depressant between the segments at bond planes (34) between contracting segments; forming a heated zone across the segments and a heated front (32); where melt pools (36) form in a molten zone (38) at the heated front which front (32), pools (36) and zone (38) continuously move and pass along the bond planes (34); where crystal re-growth (35) occurs along the bonding planes to form bonds (34) between the individual segments (18, 19, 20 and 21) behind the moving molten zone (38).

摘要翻译： 一种通过以下方式将至少两个长的金属合金段结合在一起的涡轮机部件，例如涡轮机叶片段（18,19,20和21）：通过在接合平面（34）处的段之间放置熔点降低剂 段; 跨越所述段和加热的前部（32）形成加热区; 其中熔融池（36）在加热的前部形成在熔融区域（38）中，前部（32），池（36）和区域（38）连续地移动并沿着粘合平面（34）移动; 其中晶体再生长（35）沿着接合平面发生，以在移动熔融区（38）后面的各个段（18,19,20和21）之间形成接合（34）。

公开(公告)号：US5670879A

公开(公告)日：1997-09-23

申请号：US165289

申请日：1993-12-13

申请人： Paul J. Zombo ,  Paul Guenther ,  Charles C. Moore ,  Michael J. Metala

发明人： Paul J. Zombo ,  Paul Guenther ,  Charles C. Moore ,  Michael J. Metala

IPC分类号： G01N27/90 ,  G01N29/06 ,  G01N29/22 ,  G01M1/22 ,  G01N27/82

CPC分类号： G01N29/223 ,  G01N27/9013 ,  G01N29/0618 ,  G01N29/0645 ,  G01N2291/2693

摘要： A nondestructive inspection device and a method of monitoring a defective condition in a rotating member of a combustion turbine engine using a nondestructive inspection device is presented. The nondestructive inspection device includes a sensor for monitoring the rotating member and a holder assembly for positioning the sensor near the rotating member without disassembling the combustion turbine engine. The holder assembly is capable of interchangeably positioning either an ultrasound transducer or an eddy current sensor. Signals indicative of the monitored condition are recorded and compared to a signal representation generated from a reference standard having a known defect so that a defective condition can be ascertained. The location of a defective condition is ascertained by using a magnetic belt having a plurality of magnets wrapped around the rotating member and an additional sensor to detect the magnets as they rotate. A signal indicative of the detected magnets is recorded along with the signal indicative of the monitored condition so that the angular position of the rotating member can be correlated with a detected defect.

摘要翻译： 提出了一种非破坏性检查装置和使用非破坏性检查装置监测燃气涡轮发动机的旋转构件的缺陷状况的方法。 非破坏性检查装置包括用于监测旋转构件的传感器和用于将传感器定位在旋转构件附近而不拆卸燃气涡轮发动机的保持器组件。 保持器组件能够互换地定位超声换能器或涡流传感器。 记录指示监视条件的信号，并将其与从具有已知缺陷的参考标准产生的信号表示进行比较，从而可以确定缺陷状况。 通过使用具有缠绕在旋转构件上的多个磁体的磁带和附加的传感器来确定有缺陷状况的位置，以便在旋转时检测磁体。 指示检测到的磁体的信号与指示监视条件的信号一起被记录，使得旋转部件的角位置可以与检测到的缺陷相关联。

公开(公告)号：US10704958B2

公开(公告)日：2020-07-07

申请号：US13274766

申请日：2011-10-17

申请人： Paul J. Zombo ,  Dennis H. Lemieux ,  Clifford Hatcher

发明人： Paul J. Zombo ,  Dennis H. Lemieux ,  Clifford Hatcher

IPC分类号： G01J5/00 ,  G01J5/08

摘要： A method for monitoring a high-temperature region of interest in a turbine engine (10) is provided. The method includes providing an internally-cooled stationary vane (12). The method may further include locating at least one monitoring port (14) in the stationary vane and operatively connecting a monitoring instrument (16) to the monitoring port to provide a field of view of a region of interest.

公开(公告)号：US20130343424A1

公开(公告)日：2013-12-26

申请号：US13922367

申请日：2013-06-20

申请人： Paul J. Zombo ,  James F. Landy ,  Joseph L. Rose ,  Steven E. Owens ,  Fei Yan ,  Cody J. Borigo

发明人： Paul J. Zombo ,  James F. Landy ,  Joseph L. Rose ,  Steven E. Owens ,  Fei Yan ,  Cody J. Borigo

IPC分类号： G01K11/22

CPC分类号： G01K11/22 ,  G01N25/72 ,  G01N29/0672 ,  G01N29/262 ,  G01N2291/0425

摘要： Methods and systems (10) based on guided wave thermography for non-destructively inspecting structural flaws that may be present in a structure (15). For example, such systems and methods may provide the ability to selectively deliver sonic or ultrasonic energy to provide focusing and/or beam steering throughout the structure from a fixed transducer location (12, 14, 16). Moreover, such systems and methods may provide the ability to selectively apply sonic or ultrasonic energy having excitation characteristics (FIGS. 11 and 12) which may be uniquely tailored to enhance the thermal response (FIGS. 5 and 7) of a particular flaw geometry and/or flaw location.

摘要翻译： 基于导波热像仪的方法和系统（10）可以存在于结构（15）中的非破坏性检查结构缺陷。 例如，这样的系统和方法可以提供选择性地传送声波或超声波能量以从固定换能器位置（12,14,16）提供整个结构的聚焦和/或光束转向的能力。 此外，这样的系统和方法可以提供选择性地应用具有激发特性的声波或超声能量（图11和12）的能力，其可以被唯一地定制以增强特定缺陷几何的热响应（图5和图7） /或缺陷位置。

公开(公告)号：US07690840B2

公开(公告)日：2010-04-06

申请号：US10610214

申请日：2003-06-30

申请人： Paul J. Zombo ,  Dennis Lemieux ,  Evangelos Diatzikis

发明人： Paul J. Zombo ,  Dennis Lemieux ,  Evangelos Diatzikis

IPC分类号： G01N25/72 ,  G01K13/00 ,  G01J5/00 ,  G01N17/00

CPC分类号： G01J5/0022 ,  F01D5/288 ,  F01D21/003 ,  F01D21/12 ,  F01D21/14 ,  F05D2230/90 ,  F05D2270/11 ,  F05D2270/303 ,  F05D2300/611 ,  G01N25/72 ,  Y02T50/67

摘要： A method of remotely monitoring the radiant energy (6) emitted from a turbine component such as a turbine blade (1) having a low-reflective surface coating (3) which may be undergoing potential degradation is used to determine whether erosion, spallation, delamination, or the like, of the coating (3) is occurring.

摘要翻译： 使用远程监测从具有可能经历潜在劣化的低反射表面涂层（3）的诸如涡轮机叶片（1）的涡轮机部件发射的辐射能（6）的方法来确定侵蚀，剥落，分层 ，或类似物，发生涂层（3）。

公开(公告)号：US09410853B2

公开(公告)日：2016-08-09

申请号：US13922367

申请日：2013-06-20

申请人： Paul J. Zombo ,  James F. Landy ,  Joseph L. Rose ,  Steven E. Owens ,  Fei Yan ,  Cody J. Borigo

发明人： Paul J. Zombo ,  James F. Landy ,  Joseph L. Rose ,  Steven E. Owens ,  Fei Yan ,  Cody J. Borigo

IPC分类号： G01K11/22 ,  G01N25/72 ,  G01N29/26 ,  G01N29/06

CPC分类号： G01K11/22 ,  G01N25/72 ,  G01N29/0672 ,  G01N29/262 ,  G01N2291/0425

摘要： Methods and systems (10) based on guided wave thermography for non-destructively inspecting structural flaws that may be present in a structure (15). For example, such systems and methods may provide the ability to selectively deliver sonic or ultrasonic energy to provide focusing and/or beam steering throughout the structure from a fixed transducer location (12, 14, 16). Moreover, such systems and methods may provide the ability to selectively apply sonic or ultrasonic energy having excitation characteristics (FIGS. 11 and 12) which may be uniquely tailored to enhance the thermal response (FIGS. 5 and 7) of a particular flaw geometry and/or flaw location.

摘要翻译： 基于导波热像仪的方法和系统（10）可以存在于结构（15）中的非破坏性检查结构缺陷。 例如，这样的系统和方法可以提供选择性地传送声波或超声波能量以从固定换能器位置（12,14,16）提供整个结构的聚焦和/或光束转向的能力。 此外，这样的系统和方法可以提供选择性地应用具有激发特性的声波或超声能量（图11和12）的能力，其可以被唯一地定制以增强特定缺陷几何的热响应（图5和图7） /或缺陷位置。

公开(公告)号：US20150132102A1

公开(公告)日：2015-05-14

申请号：US14077338

申请日：2013-11-12

申请人： Dennis H. Lemieux ,  Vinay Jonnalagadda ,  Paul J. Zombo

发明人： Dennis H. Lemieux ,  Vinay Jonnalagadda ,  Paul J. Zombo

IPC分类号： F02C7/00

CPC分类号： F02C7/00 ,  F05D2260/80 ,  F05D2270/303

摘要： Apparatus and method for determining a two-dimensional temperature distribution in a cross-sectional path of a hot-temperature flow in a turbine engine (10). A grid (22, 24, 38) is located in a path of a hot-temperature flow in the turbine engine. A thermal imager (34) has a field of view configured to sense infrared emissions from the grid. A processor (50) is configured to generate data indicative of a two-dimensional temperature distribution in a cross-sectional path of the flow based on the sensed infrared emissions.

摘要翻译： 用于确定涡轮发动机（10）中的热流的横截面路径中的二维温度分布的装置和方法。 格栅（22,24,38）位于涡轮发动机中的热温流的路径中。 热像仪（34）具有被配置为感测来自电网的红外发射的视场。 处理器（50）被配置为基于所感测的红外发射，在流的横截面路径中产生指示二维温度分布的数据。