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1. 发明授权

US07887234B2 Maximum blade surface temperature estimation for advanced stationary gas turbines in near-infrared (with reflection) 有权
标题翻译：近红外（带反射）的先进固定式燃气轮机的最大叶片表面温度估算
公开(公告)号：US07887234B2
公开(公告)日：2011-02-15
申请号：US11872758
申请日：2007-10-16
申请人： Vinay Jonnalagadda , Dennis H. Lemieux , Visvanathan Ramesh , Matthias Voigt
发明人： Vinay Jonnalagadda , Dennis H. Lemieux , Visvanathan Ramesh , Matthias Voigt
IPC分类号： G01J5/00 , G01K13/08 , G01N21/00
CPC分类号： G01J5/0003 , G01J5/0022 , G01J5/0088 , G01J5/06 , G01J5/522 , G01J5/60 , G01J2005/0059 , G01J2005/0077 , G01J2005/0081
摘要： Methods for maximum scene surface temperature estimation for blades with reflective surface properties in advanced stationary gas turbines are disclosed. The approach utilizes high speed infrared imagery provided by an online monitor system using a focal plan array (FPA) for near-infrared monitoring during engine runtime up to base load. The one waveband method for temperature estimation is assumed as starting point. A lower surface emissivity and higher surface reflectance of thermal barrier coating (TBC) in near-infrared can cause systematic estimation errors. Methods using the one wave band method, with the purpose to reduce estimation errors for maximum temperatures are also disclosed. Theoretical results, data from numerical simulations, and real data from engine test are provided. A system for performing temperature estimation methods is also disclosed.
摘要翻译：公开了在高级固定式燃气轮机中具有反射表面特性的叶片的最大场景表面温度估计方法。该方法利用在线监测系统提供的高速红外图像，使用焦点计划阵列（FPA）在发动机运行时到基本负载时进行近红外监测。假定温度估计的一种波段方法作为起点。近红外热阻层（TBC）的较低表面发射率和较高的表面反射率可导致系统的估计误差。还公开了使用一波段方法的方法，其目的是减少最大温度的估计误差。提供了理论结果，数值模拟数据和发动机试验的实际数据。还公开了一种用于执行温度估计方法的系统。

2. 发明申请

US20080095212A1 Maximum Blade Surface Temperature Estimation for Advanced Stationary Gas Turbines in Near-Infrared (with Reflection) 有权
标题翻译：近红外高级固定式燃气轮机的最大叶片表面温度估计（带反射）
公开(公告)号：US20080095212A1
公开(公告)日：2008-04-24
申请号：US11872758
申请日：2007-10-16
申请人： Vinay Jonnalagadda , Dennis Lemieux , Visvanathan Ramesh , Matthias Voigt
发明人： Vinay Jonnalagadda , Dennis Lemieux , Visvanathan Ramesh , Matthias Voigt
IPC分类号： G01J5/00
CPC分类号： G01J5/0003 , G01J5/0022 , G01J5/0088 , G01J5/06 , G01J5/522 , G01J5/60 , G01J2005/0059 , G01J2005/0077 , G01J2005/0081
摘要： Methods for maximum scene surface temperature estimation for blades with reflective surface properties in advanced stationary gas turbines are disclosed. The approach utilizes high speed infrared imagery provided by an online monitor system using a focal plan array (FPA) for near-infrared monitoring during engine runtime up to base load. The one waveband method for temperature estimation is assumed as starting point. A lower surface emissivity and higher surface reflectance of thermal barrier coating (TBC) in near-infrared can cause systematic estimation errors. Methods using the one wave band method, with the purpose to reduce estimation errors for maximum temperatures are also disclosed. Theoretical results, data from numerical simulations, and real data from engine test are provided. A system for performing temperature estimation methods is also disclosed.
摘要翻译：公开了在高级固定式燃气轮机中具有反射表面特性的叶片的最大场景表面温度估计方法。该方法利用在线监测系统提供的高速红外图像，使用焦点计划阵列（FPA）在发动机运行时到基本负载时进行近红外监测。假定温度估计的一种波段方法作为起点。近红外热阻层（TBC）的较低表面发射率和较高的表面反射率可导致系统的估计误差。还公开了使用一波段方法的方法，其目的是减少最大温度的估计误差。提供了理论结果，数值模拟数据和发动机试验的实际数据。还公开了一种用于执行温度估计方法的系统。

3. 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。

4. 发明授权

US08439630B2 Optical monitoring system for a turbine engine 有权
标题翻译：涡轮发动机光学监测系统
公开(公告)号：US08439630B2
公开(公告)日：2013-05-14
申请号：US12727582
申请日：2010-03-19
申请人： Dennis H. Lemieux , Jan P. Smed , James P. Williams , Vinay Jonnalagadda
发明人： Dennis H. Lemieux , Jan P. Smed , James P. Williams , Vinay Jonnalagadda
IPC分类号： G02B23/00 , F01D25/00
CPC分类号： F01D21/003 , F05D2260/80 , G01N21/15 , G01N21/85 , G01N21/954 , G01N2021/151 , G01N2201/08 , G02B23/2492
摘要： The monitoring system for a gas turbine engine including a viewing tube assembly having an inner end and an outer end. The inner end is located adjacent to a hot gas flow path within the gas turbine engine and the outer end is located adjacent to an outer casing of the gas turbine engine. An aperture wall is located at the inner end of the viewing tube assembly and an optical element is located within the viewing tube assembly adjacent to the inner end and is spaced from the aperture wall to define a cooling and purge chamber therebetween. An aperture is defined in the aperture wall for passage of light from the hot gas flow path to the optical element. Swirl passages are defined in the viewing tube assembly between the aperture wall and the optical element for passage of cooling air from a location outside the viewing tube assembly into the chamber, wherein swirl passages effect a swirling movement of air in a circumferential direction within the chamber.
摘要翻译：一种用于燃气涡轮发动机的监测系统，其包括具有内端和外端的观察管组件。内端位于燃气涡轮发动机内的热气流路径附近，外端位于燃气涡轮发动机的外壳附近。孔壁位于观察管组件的内端，并且光学元件位于观察管组件内邻近内端并且与孔壁间隔开以在其间限定冷却和净化室。在孔壁中限定有一个孔，用于使光从热气流通道通过到光学元件。涡流通道限定在孔壁组件和光学元件之间，用于使冷却空气从观察管组件外部的位置进入腔室，其中旋转通道在腔室内沿圆周方向起作用的旋转运动。

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

US20110229307A1 Optical Monitoring System for a Turbine Engine 有权
标题翻译：涡轮发动机光学监测系统
公开(公告)号：US20110229307A1
公开(公告)日：2011-09-22
申请号：US12727582
申请日：2010-03-19
申请人： Dennis H. Lemieux , Jan P. Smed , James P. Williams , Vinay Jonnalagadda
发明人： Dennis H. Lemieux , Jan P. Smed , James P. Williams , Vinay Jonnalagadda
IPC分类号： F02C7/18 , F02C7/00
CPC分类号： F01D21/003 , F05D2260/80 , G01N21/15 , G01N21/85 , G01N21/954 , G01N2021/151 , G01N2201/08 , G02B23/2492
摘要： The monitoring system for a gas turbine engine including a viewing tube assembly having an inner end and an outer end. The inner end is located adjacent to a hot gas flow path within the gas turbine engine and the outer end is located adjacent to an outer casing of the gas turbine engine. An aperture wall is located at the inner end of the viewing tube assembly and an optical element is located within the viewing tube assembly adjacent to the inner end and is spaced from the aperture wall to define a cooling and purge chamber therebetween. An aperture is defined in the aperture wall for passage of light from the hot gas flow path to the optical element. Swirl passages are defined in the viewing tube assembly between the aperture wall and the optical element for passage of cooling air from a location outside the viewing tube assembly into the chamber, wherein swirl passages effect a swirling movement of air in a circumferential direction within the chamber.
摘要翻译：一种用于燃气涡轮发动机的监测系统，其包括具有内端和外端的观察管组件。内端位于燃气涡轮发动机内的热气流路径附近，外端位于燃气涡轮发动机的外壳附近。孔壁位于观察管组件的内端，并且光学元件位于观察管组件内邻近内端并且与孔壁间隔开以在其间限定冷却和净化室。在孔壁中限定有一个孔，用于使光从热气流通道通过到光学元件。涡流通道限定在孔壁组件和光学元件之间，用于使冷却空气从观察管组件外部的位置进入腔室，其中旋转通道在腔室内沿圆周方向起作用的旋转运动。

7. 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。

8. 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。

9. 发明申请

US20130194411A1 SYSTEM AND METHOD FOR ONLINE INSPECTION OF TURBINES INCLUDING TEMPERATURE AND VIBRATION COMPENSATING LENS MOUNT 有权
标题翻译：用于在线检查涡轮机的系统和方法，包括温度和振动补偿镜头安装
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。

10. 发明申请

US20120197597A1 WIRELESS TELEMETRY SYSTEM FOR A TURBINE ENGINE 有权
标题翻译：涡轮发动机无线电报系统
公开(公告)号：US20120197597A1
公开(公告)日：2012-08-02
申请号：US13018469
申请日：2011-02-01
申请人： David J. Mitchell , Ramesh Subramanian , Cora Schillig , Anand A. Kulkarni , Vinay Jonnalagadda , Bulent Acar , Sankar Nellian , James P. Williams , Edward R. Roesch
发明人： David J. Mitchell , Ramesh Subramanian , Cora Schillig , Anand A. Kulkarni , Vinay Jonnalagadda , Bulent Acar , Sankar Nellian , James P. Williams , Edward R. Roesch
IPC分类号： G06F15/00
CPC分类号： F01D17/02 , F01D17/20
摘要： A telemetry system for use in a combustion turbine engine (10) having a compressor (12), a combustor and a turbine (16) and includes a sensor (118) in connection with a turbine blade (111) or vane (23). A transmitter assembly (117) includes a telemetry transmitter circuit/transceiver may be affixed on a turbine blade (111) or seal plate (115) proximate the turbine blade with a first connecting material (119) deposited on the turbine blade (111) for routing electronic data signals, indicative of a condition of the turbine blade (111), from the sensor (118) to the telemetry transmitter circuit/transceiver. An induction power system for powering the telemetry transmitter circuit/transceiver may include a rotating data antenna (116) affixed to the seal plate (115) with an electrical connection (122) between the telemetry transmitting circuit/transceiver for routing electronic data signals from the telemetry transmitter circuit/transceiver to the rotating data antenna (119).
摘要翻译：一种用于具有压缩机（12），燃烧器和涡轮机（16）的燃气涡轮发动机（10）中的遥测系统，并且包括与涡轮机叶片（111）或叶片（23）连接的传感器（118）。发射器组件（117）包括遥测发射器电路/收发器可以用沉积在涡轮叶片（111）上的第一连接材料（119）固定在靠近涡轮机叶片的涡轮叶片（111）或密封板（115）上，用于将表示涡轮叶片（111）的状况的电子数据信号从传感器（118）路由到遥测发射机电路/收发器。用于为遥测发射器电路/收发器供电的感应电力系统可以包括在遥测发射电路/收发器之间的电连接（122）固定到密封板（115）的旋转数据天线（116），用于从遥测发射机电路/收发器到旋转数据天线（119）。

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