公开(公告)号：US20130194411A1

公开(公告)日：2013-08-01

申请号：US13362365

申请日：2012-01-31

申请人： Erwan Baleine ,  Vinay Jonnalagadda ,  Michael Savard

发明人： Erwan Baleine ,  Vinay Jonnalagadda ,  Michael Savard

IPC分类号： H04N7/18 ,  G03B17/00

CPC分类号： G02B23/2492 ,  G02B7/028 ,  G03B17/12 ,  G03B17/55

摘要： Optical camera systems for nondestructive internal inspection of online, operating power generation turbines, including gas turbine combustor and turbine sections that are at high operating temperatures in the range of over 600° C. (1112° F.). The system includes one or more temperature and vibration-compensating lens systems in the optical tube mount. The lens is circumferentially retained within a lens mount, with a mounting ring in contact with only the lens axial face. A biasing element exerts axially oriented biasing force on the first lens face through the first mounting ring, allowing for mount flexure in response to operational turbine vibration and temperature changes. The lens mount is advantageously combined with aspheric lenses capable of withstanding continuous operating temperatures above 600° C. The aspheric lenses, alone or in combination with spherical lenses, establish a wider field of view, and require fewer lenses in combination than lens mounts incorporating only spherical lenses.

摘要翻译： 在超过600°C（1112°F）范围内工作温度高的在线工作发电涡轮机（包括燃气轮机燃烧器和涡轮机部分）进行非破坏性内部检查的光学相机系统。 该系统在光学管座中包括一个或多个温度和振动补偿透镜系统。 透镜周向地保持在透镜安装件内，安装环仅与透镜轴向面接触。 偏置元件通过第一安装环在第一透镜面上施加轴向取向的偏压力，从而允许响应于涡轮机运行的振动和温度变化而进行安装弯曲。 透镜支架有利地与能够承受高于600℃的连续工作温度的非球面透镜组合。非球面透镜单独或与球面透镜组合建立了更宽的视野，并且与仅包括的透镜座相比，需要更少的透镜组合 球面镜片。

公开(公告)号：US09366855B2

公开(公告)日：2016-06-14

申请号：US13362365

申请日：2012-01-31

申请人： Erwan Baleine ,  Vinay Jonnalagadda ,  Michael Savard

发明人： Erwan Baleine ,  Vinay Jonnalagadda ,  Michael Savard

IPC分类号： H04N7/18 ,  G02B23/24 ,  G02B7/02 ,  G03B17/12 ,  G03B17/55

CPC分类号： G02B23/2492 ,  G02B7/028 ,  G03B17/12 ,  G03B17/55

摘要： Optical camera systems for nondestructive internal inspection of online, operating power generation turbines, including gas turbine combustor and turbine sections that are at high operating temperatures in the range of over 600° C. (1112° F.). The system includes one or more temperature and vibration-compensating lens systems in the optical tube mount. The lens is circumferentially retained within a lens mount, with a mounting ring in contact with only the lens axial face. A biasing element exerts axially oriented biasing force on the first lens face through the first mounting ring, allowing for mount flexure in response to operational turbine vibration and temperature changes. The lens mount is advantageously combined with aspheric lenses capable of withstanding continuous operating temperatures above 600° C. The aspheric lenses, alone or in combination with spherical lenses, establish a wider field of view, and require fewer lenses in combination than lens mounts incorporating only spherical lenses.

摘要翻译： 在超过600°C（1112°F）范围内工作温度高的在线工作发电涡轮机（包括燃气轮机燃烧器和涡轮机部分）进行非破坏性内部检查的光学相机系统。 该系统在光学管座中包括一个或多个温度和振动补偿透镜系统。 透镜周向地保持在透镜安装件内，安装环仅与透镜轴向面接触。 偏置元件通过第一安装环在第一透镜面上施加轴向取向的偏压力，从而允许响应于涡轮机运行的振动和温度变化而进行安装弯曲。 透镜支架有利地与能够承受高于600℃的连续工作温度的非球面透镜组合。非球面透镜单独或与球面透镜组合建立了更宽的视野，并且与仅包括的透镜座相比，需要更少的透镜组合 球面镜片。

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。

公开(公告)号：US08896661B2

公开(公告)日：2014-11-25

申请号：US13362308

申请日：2012-01-31

申请人： Erwan Baleine ,  Vinay Jonnalagadda

发明人： Erwan Baleine ,  Vinay Jonnalagadda

IPC分类号： G02B3/00 ,  H04N7/00 ,  G02B3/02 ,  G02B23/24 ,  H04N7/18

CPC分类号： G02B23/2492 ,  G02B3/00 ,  G02B3/02 ,  H04N5/23287 ,  H04N7/00 ,  H04N7/18 ,  H04N2005/2255

摘要： Optical camera systems for nondestructive internal inspection of online, operating power generation turbines, including gas turbine combustor and turbine sections that are at high operating temperatures in the range of over 600° C. (1112° F.) and which include combustion gas contaminants. The inspection system includes one or more aspheric lenses capable of withstanding continuous operating temperatures above 600° C. The aspheric lenses, alone or in combination with spherical lenses, establish a wider field of view, and require fewer lenses in combination than lens mounts incorporating only spherical lenses. A cooling system incorporated in the inspection system facilitates continuous operation and inhibits lens external surface fouling from combustion gasses.

摘要翻译： 用于在线，工作发电涡轮机（包括燃气轮机燃烧器和涡轮机部分）的非破坏性内部检查的光学照相机系统，其处于高于600℃（1112°F）的高工作温度并且包括燃烧气体污染物。 该检查系统包括能够承受高于600℃的连续工作温度的一个或多个非球面透镜。单独或与球面透镜组合的非球面透镜建立更宽的视场，并且与仅包括的透镜座相比，需要较少的透镜组合 球面镜片。 结合在检查系统中的冷却系统便于连续操作，并且抑制来自燃烧气体的透镜外表面结垢。

公开(公告)号：US20130194379A1

公开(公告)日：2013-08-01

申请号：US13362308

申请日：2012-01-31

申请人： Erwan Baleine ,  Vinay Jonnalagadda

发明人： Erwan Baleine ,  Vinay Jonnalagadda

IPC分类号： H04N7/00 ,  G02B3/00 ,  H04N7/18 ,  G02B3/02

CPC分类号： G02B23/2492 ,  G02B3/00 ,  G02B3/02 ,  H04N5/23287 ,  H04N7/00 ,  H04N7/18 ,  H04N2005/2255

摘要： Optical camera systems for nondestructive internal inspection of online, operating power generation turbines, including gas turbine combustor and turbine sections that are at high operating temperatures in the range of over 600° C. (1112° F.) and which include combustion gas contaminants. The inspection system includes one or more aspheric lenses capable of withstanding continuous operating temperatures above 600° C. The aspheric lenses, alone or in combination with spherical lenses, establish a wider field of view, and require fewer lenses in combination than lens mounts incorporating only spherical lenses. A cooling system incorporated in the inspection system facilitates continuous operation and inhibits lens external surface fouling from combustion gasses.

摘要翻译： 用于在线，工作发电涡轮机（包括燃气轮机燃烧器和涡轮机部分）的非破坏性内部检查的光学照相机系统，其处于高于600℃（1112°F）的高工作温度并且包括燃烧气体污染物。 该检查系统包括能够承受高于600℃的连续工作温度的一个或多个非球面透镜。单独或与球面透镜组合的非球面透镜建立更宽的视场，并且与仅包括的透镜座相比，需要较少的透镜组合 球面镜片。 结合在检查系统中的冷却系统便于连续操作，并且抑制来自燃烧气体的透镜外表面结垢。

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。

公开(公告)号：US07551289B2

公开(公告)日：2009-06-23

申请号：US11399632

申请日：2006-04-06

申请人： Aristide Dogariu ,  Erwan Baleine

发明人： Aristide Dogariu ,  Erwan Baleine

IPC分类号： G01B9/02

CPC分类号： G01N21/4738 ,  G01N21/49 ,  G01N2011/008

摘要： A light scattering sensing system and method. In one embodiment, the system includes a sample branch configured to collect light signals backscattered from scattering centers contained in a coherence volume of a medium under evaluation, the sample branch including a multi-mode optical waveguide. In one embodiment, the method includes radiating low-coherence light into a scattering medium using a multi-mode optical waveguide, and collecting light signals backscattered by the scattering centers and light reflected by an end surface of the multi-mode optical waveguide using the multi-mode optical waveguide.

摘要翻译： 一种光散射感测系统及方法。 在一个实施例中，系统包括样本分支，该样本分支被配置为收集从包含在待评估介质的相干体积中的散射中心反向散射的光信号，所述样本分支包括多模光波导。 在一个实施例中，该方法包括使用多模光波导将低相干光照射到散射介质中，并且收集由散射中心反向散射的光信号和由多模光波导的端面反射的光，使用多 模式光波导。

公开(公告)号：US09217852B2

公开(公告)日：2015-12-22

申请号：US13597919

申请日：2012-08-29

申请人： Erwan Baleine

发明人： Erwan Baleine

IPC分类号： G01J5/00 ,  G02B17/06 ,  G01N21/00 ,  G02B23/24 ,  G01N21/95 ,  G01N21/954

CPC分类号： G02B17/0652 ,  G01N21/00 ,  G01N21/95 ,  G01N21/954 ,  G02B23/2492

摘要： An optical inspection system for nondestructive internal visual inspection and non-contact infra-red (IR) temperature monitoring of an online, operating power generation turbine. The optical inspection system includes an optical tube having a viewing port, at least one reflective mirror or a mirror array having a reflectivity spectral range from 550 nm to 20 μm, and capable of continuous operation at temperatures greater than 932 degrees Fahrenheit (500 degrees Celsius), and a transparent window with high transmission within the same spectral range mounted distal the viewing port. The same optical mirror array may be used to measure selectively surface temperature of metal turbine blades in the near IR range (approximately 1 μm wavelength) and of thermal barrier coated turbine blades in the long IR range (approximately 10 μm wavelength).

摘要翻译： 一种用于在线，运行发电机组的非破坏性内部视觉检测和非接触式红外（IR）温度监测的光学检测系统。 光学检查系统包括具有观察口的光学管，至少一个反射镜或反射镜阵列，其反射光谱范围为550nm至20μm，并能够在大于932华氏度（500摄氏度）的温度下连续工作 ）和在观察端口远端安装的相同光谱范围内具有高透射率的透明窗口。 可以使用相同的光学镜阵列在近红外范围（大约1μm波长）中选择性地测量金属涡轮叶片的表面温度以及在长IR范围（约10μm波长）中的热障涂覆的涡轮叶片。

公开(公告)号：US08866084B2

公开(公告)日：2014-10-21

申请号：US13604668

申请日：2012-09-06

申请人： Erwan Baleine ,  James F. Landy ,  Ching-Pang Lee ,  Stephanie Stinelli

发明人： Erwan Baleine ,  James F. Landy ,  Ching-Pang Lee ,  Stephanie Stinelli

IPC分类号： G01J5/02

CPC分类号： G01J5/522 ,  G01J5/0088 ,  G01J2005/0048 ,  G01J2005/0077 ,  G01J2005/0081 ,  G01N25/72

摘要： A method of nondestructive evaluation and related system. The method includes arranging a test piece (14) having an internal passage (18) and an external surface (15) and a thermal calibrator (12) within a field of view (42) of an infrared sensor (44); generating a flow (16) of fluid characterized by a fluid temperature; exposing the test piece internal passage (18) and the thermal calibrator (12) to fluid from the flow (16); capturing infrared emission information of the test piece external surface (15) and of the thermal calibrator (12) simultaneously using the infrared sensor (44), wherein the test piece infrared emission information includes emission intensity information, and wherein the thermal calibrator infrared emission information includes a reference emission intensity associated with the fluid temperature; and normalizing the test piece emission intensity information against the reference emission intensity.

摘要翻译： 一种无损检测方法及相关系统。 该方法包括在红外传感器（44）的视场（42）内布置具有内部通道（18）和外表面（15）和热校准器（12）的测试件（14）。 产生以流体温度为特征的流体流（16）; 将测试件内部通道（18）和热校准器（12）暴露于来自流动（16）的流体; 使用红外传感器（44）同时捕获测试件外表面（15）和热校准器（12）的红外发射信息，其中测试件红外发射信息包括发射强度信息，并且其中热校准器红外发射信息 包括与流体温度相关联的参考发射强度; 并根据参考发射强度对测试片发射强度信息进行归一化。

公开(公告)号：US20120200698A1

公开(公告)日：2012-08-09

申请号：US13023774

申请日：2011-02-09

申请人： Erwan Baleine ,  Danny M. Sheldon

发明人： Erwan Baleine ,  Danny M. Sheldon

IPC分类号： H04N7/18

CPC分类号： H04N7/18 ,  G01J5/00 ,  G01J5/0022 ,  G01J5/0088 ,  G01J5/02 ,  G01J5/025 ,  G01J5/08 ,  G01J5/0806 ,  G01J2005/0048 ,  G01J2005/0077 ,  G05B2219/37211 ,  G05B2219/37509

摘要： Method and system for calibrating a thermal radiance map of a turbine component in a combustion environment. At least one spot (18) of material is disposed on a surface of the component. An infrared (IR) imager (14) is arranged so that the spot is within a field of view of the imager to acquire imaging data of the spot. A processor (30) is configured to process the imaging data to generate a sequence of images as a temperature of the combustion environment is increased. A monitor (42, 44) may be coupled to the processor to monitor the sequence of images of to determine an occurrence of a physical change of the spot as the temperature is increased. A calibration module (46) may be configured to assign a first temperature value to the surface of the turbine component when the occurrence of the physical change of the spot is determined.

摘要翻译： 用于在燃烧环境中校准涡轮机部件的热辐射图的方法和系统。 至少一个材料点（18）设置在部件的表面上。 红外线（IR）成像器（14）被布置成使得该点位于成像器的视场内以获取该点的成像数据。 处理器（30）被配置为当燃烧环境的温度增加时，处理成像数据以产生图像序列。 监视器（42,44）可以耦合到处理器以监视图像序列，以确定当温度升高时点的物理变化的发生。 校准模块（46）可以被配置为当确定点的物理变化的发生时，将第一温度值分配给涡轮机部件的表面。