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1. 发明申请

US20110069165A1 Flexible Imaging Fiber Bundle Monitoring System for Combustion Turbines 有权
标题翻译：用于燃烧涡轮机的柔性成像光纤束监测系统
公开(公告)号：US20110069165A1
公开(公告)日：2011-03-24
申请号：US12562196
申请日：2009-09-18
申请人： Paul J. Zombo , Vinay Jonnalagadda , Erwan Baleine
发明人： Paul J. Zombo , Vinay Jonnalagadda , Erwan Baleine
IPC分类号： H04N7/18
CPC分类号： G02B23/26 , F01D21/003 , G02B23/2484 , G02B23/2492
摘要： An imaging system for on-line imaging of a component in a gas turbine engine. The imaging system includes a flexible imaging bundle formed by a plurality of optical elements. An imaging end of the optical elements images a component in a hot gas path of the engine during operation of the engine and a viewing end provides an image of the component at a location displaced from the hot gas path. The optical elements are surrounded by a flexible metal sheath that is permeable to air to provide cooling air the optical elements from an air source surrounding the flexible imaging bundle.
摘要翻译：一种用于燃气涡轮发动机中的部件的在线成像的成像系统。该成像系统包括由多个光学元件形成的柔性成像束。在发动机操作期间，光学元件的成像端将发动机的热气路径中的部件成像，并且观察端在偏离热气体路径的位置处提供部件的图像。光学元件由柔性金属护套包围，该柔性金属护套对于空气可透过以提供来自围绕柔性成像束的空气源的光学元件的冷却空气。

2. 发明授权

US08184151B2 Flexible imaging fiber bundle monitoring system for combustion turbines 有权
标题翻译：用于燃气轮机的灵活成像光纤束监测系统
公开(公告)号：US08184151B2
公开(公告)日：2012-05-22
申请号：US12562196
申请日：2009-09-18
申请人： Paul J. Zombo , Vinay Jonnalagadda , Erwan Baleine
发明人： Paul J. Zombo , Vinay Jonnalagadda , Erwan Baleine
IPC分类号： H04N7/18
CPC分类号： G02B23/26 , F01D21/003 , G02B23/2484 , G02B23/2492
摘要： An imaging system for on-line imaging of a component in a gas turbine engine. The imaging system includes a flexible imaging bundle formed by a plurality of optical elements. An imaging end of the optical elements images a component in a hot gas path of the engine during operation of the engine and a viewing end provides an image of the component at a location displaced from the hot gas path. The optical elements are surrounded by a flexible metal sheath that is permeable to air to provide cooling air the optical elements from an air source surrounding the flexible imaging bundle.
摘要翻译：一种用于燃气涡轮发动机中的部件的在线成像的成像系统。成像系统包括由多个光学元件形成的柔性成像束。在发动机操作期间，光学元件的成像端将发动机的热气路径中的部件成像，并且观察端在偏离热气体路径的位置处提供部件的图像。光学元件由柔性金属护套包围，该柔性金属护套对于空气可透过以提供来自围绕柔性成像束的空气源的光学元件的冷却空气。

3. 发明申请

US20150015693A1 SYSTEM AND METHOD FOR OPTICAL FIBER BASED IMAGE ACQUISITION SUITABLE FOR USE IN TURBINE ENGINES 有权
标题翻译：适用于涡轮发动机的基于光纤的图像采集系统和方法
公开(公告)号：US20150015693A1
公开(公告)日：2015-01-15
申请号：US13937331
申请日：2013-07-09
申请人： Erwan Baleine , Varun A V , Paul J. Zombo , Zubin Varghese
发明人： Erwan Baleine , Varun A V , Paul J. Zombo , Zubin Varghese
IPC分类号： H04N7/18
CPC分类号： H04N7/183 , G02B23/2469 , G02B23/26 , G02B27/58 , G02B2207/129
摘要： A system and a method for image acquisition suitable for use in a turbine engine are disclosed. Light received from a field of view in an object plane is projected onto an image plane through an optical modulation device and is transferred through an image conduit to a sensor array. The sensor array generates a set of sampled image signals in a sensing basis based on light received from the image conduit. Finally, the sampled image signals are transformed from the sensing basis to a representation basis and a set of estimated image signals are generated therefrom. The estimated image signals are used for reconstructing an image and/or a motion-video of a region of interest within a turbine engine.
摘要翻译：公开了一种适用于涡轮发动机的图像采集系统和方法。从物体平面中的视野接收的光通过光学调制装置投影到图像平面上，并通过图像导管传送到传感器阵列。传感器阵列基于从图像导管接收的光在感测的基础上产生一组采样的图像信号。最后，将采样的图像信号从感测基础变换为基于表示，并从其生成一组估计的图像信号。估计的图像信号用于重建涡轮发动机内的感兴趣区域的图像和/或运动视频。

4. 发明申请

US20150132102A1 APPARATUS AND METHOD FOR DETERMINING A TEMPERATURE DISTRIBUTION OF A HOT-TEMPERATURE FLOW IN A TURBINE ENGINE 有权
标题翻译：用于确定涡轮发动机温度流量温度分布的装置和方法
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。

5. 发明授权

US08063372B2 Apparatus and method for temperature mapping a rotating turbine component in a high temperature combustion environment 有权
标题翻译：用于在高温燃烧环境中对旋转涡轮机部件进行温度测绘的装置和方法
公开(公告)号：US08063372B2
公开(公告)日：2011-11-22
申请号：US12699936
申请日：2010-02-04
申请人： Dennis H. Lemieux , Paul J. Zombo , Vinay Jonnalagadda
发明人： Dennis H. Lemieux , Paul J. Zombo , Vinay Jonnalagadda
IPC分类号： G01J5/02
CPC分类号： G02B13/16 , G01D18/008 , G01J5/0022 , G01J5/0088 , G01J5/02 , G01J5/025 , G01J5/04 , G01J5/042 , G01J5/08 , G01J5/0803 , G01J5/0846
摘要： Apparatus and method for temperature mapping a rotating component (12) in a high temperature combustion environment. The apparatus includes a thermal imager (14) having a field of view to sense infrared (IR) emissions. Emissivity of a surface of the component is subject to variation in the combustion environment. A radiance emitter (18) defines a spot within the field of view of the thermal imager. The spot indicates a respective emissivity value. A processor (30) is connected to the thermal imager to generate a radiance map of the component based on the IR emissions from the component. The processor includes a thermal calibration module configured to calibrate the radiance map based on the emissivity value of the spot within the field of view of the thermal imager to generate a calibrated thermal map of the component that displays absolute temperature over the surface of the component.
摘要翻译：用于在高温燃烧环境中对旋转部件（12）进行温度映射的装置和方法。该装置包括具有感测红外（IR）发射的视野的热像仪（14）。部件表面的发射率在燃烧环境中会发生变化。辐射发射器（18）限定了热像仪的视野内的光点。该点表示各自的发射率值。处理器（30）连接到热成像仪，以基于来自组件的IR发射来生成部件的辐射图。处理器包括热校准模块，其被配置为基于热成像仪的视场内的光斑的发射率值来校准辐射图，以产生在组件的表面上显示绝对温度的部件的校准热图。

6. 发明申请

US20100224772A1 Apparatus and Method for Temperature Mapping a Rotating Turbine Component in a High Temperature Combustion Environment 有权
标题翻译：用于在高温燃烧环境中对旋转涡轮机部件进行温度映射的装置和方法
公开(公告)号：US20100224772A1
公开(公告)日：2010-09-09
申请号：US12699936
申请日：2010-02-04
申请人： Dennis H. Lemieux , Paul J. Zombo , Vinay Jonnalagadda
发明人： Dennis H. Lemieux , Paul J. Zombo , Vinay Jonnalagadda
IPC分类号： G02F1/01 , G01D18/00
CPC分类号： G02B13/16 , G01D18/008 , G01J5/0022 , G01J5/0088 , G01J5/02 , G01J5/025 , G01J5/04 , G01J5/042 , G01J5/08 , G01J5/0803 , G01J5/0846
摘要： Apparatus and method for temperature mapping a rotating component (12) in a high temperature combustion environment. The apparatus includes a thermal imager (14) having a field of view to sense infrared (IR) emissions. Emissivity of a surface of the component is subject to variation in the combustion environment. A radiance emitter (18) defines a spot within the field of view of the thermal imager. The spot indicates a respective emissivity value. A processor (30) is connected to the thermal imager to generate a radiance map of the component based on the IR emissions from the component. The processor includes a thermal calibration module configured to calibrate the radiance map based on the emissivity value of the spot within the field of view of the thermal imager to generate a calibrated thermal map of the component that displays absolute temperature over the surface of the component.
摘要翻译：用于在高温燃烧环境中对旋转部件（12）进行温度映射的装置和方法。该装置包括具有感测红外（IR）发射的视野的热像仪（14）。部件表面的发射率在燃烧环境中会发生变化。辐射发射器（18）限定了热像仪的视野内的光点。该点表示各自的发射率值。处理器（30）连接到热成像仪，以基于来自组件的IR发射来生成部件的辐射图。处理器包括热校准模块，其被配置为基于热成像仪的视场内的光斑的发射率值来校准辐射图，以产生在组件的表面上显示绝对温度的部件的校准热图。

7. 发明申请

US20120034097A1 COMPONENT WITH INSPECTION-FACILITATING FEATURES 有权
标题翻译：具有检查功能的组件
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。

8. 发明授权

US06193141B1 Single crystal turbine components made using a moving zone transient liquid phase bonded sandwich construction 有权
标题翻译：使用移动区域瞬态液相粘结夹层结构制造的单晶涡轮机组件
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）。

9. 发明授权

US5670879A Nondestructive inspection device and method for monitoring defects inside a turbine engine 失效
标题翻译：用于监测涡轮发动机内的缺陷的非破坏性检查装置和方法
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。

10. 发明授权

US10704958B2 Method for monitoring a high-temperature region of interest in a turbine engine 有权
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.

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