公开(公告)号：WO2011034661A1

公开(公告)日：2011-03-24

申请号：PCT/US2010/043859

申请日：2010-07-30

Applicant: SIEMENS ENERGY, INC. ,  ZOMBO, Paul J. ,  JONNALAGADDA, Vinay ,  BALEINE, Erwan

Inventor： ZOMBO, Paul J. ,  JONNALAGADDA, Vinay ,  BALEINE, Erwan

IPC: G02B23/24 ,  G02B23/26 ,  B23Q17/24 ,  G02B6/06

CPC classification number: G02B23/26 ,  F01D21/003 ,  G02B23/2484 ,  G02B23/2492

Abstract: 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

Abstract translation: 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，该柔性金属护套对空气是可透过的，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：WO2011152906A2

公开(公告)日：2011-12-08

申请号：PCT/US2011/027636

申请日：2011-03-09

Applicant: SIEMENS ENERGY, INC. ,  LEMIEUX, Dennis H. ,  SMED, Jan P. ,  WILLIAMS, James P. ,  JONNALAGADDA, Vinay

Inventor： LEMIEUX, Dennis H. ,  SMED, Jan P. ,  WILLIAMS, James P. ,  JONNALAGADDA, Vinay

IPC: F02C7/18 ,  F02C7/00

CPC classification number: F01D21/003 ,  F05D2260/80 ,  G01N21/15 ,  G01N21/85 ,  G01N21/954 ,  G01N2021/151 ,  G01N2201/08 ,  G02B23/2492

Abstract: 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.

Abstract translation: 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和光学元件之间的观察管组件中，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 。

公开(公告)号：WO2011094658A1

公开(公告)日：2011-08-04

申请号：PCT/US2011/023095

申请日：2011-01-31

Applicant: SIEMENS ENERGY, INC. ,  SUBRAMANIAN, Ramesh ,  KULKARNI, Anand A. ,  JONNALAGADDA, Vinay ,  MITCHELL, David, J.

Inventor： SUBRAMANIAN, Ramesh ,  KULKARNI, Anand A. ,  JONNALAGADDA, Vinay ,  MITCHELL, David, J.

IPC: F01D17/08 ,  F01D21/00

CPC classification number: F01D17/085 ,  F01D21/003 ,  F05D2270/303 ,  F05D2300/143 ,  G01K7/04 ,  G01K17/00

Abstract: A gas turbine component (49) may be instrumented to provide a plurality of signals indicative of thermal measurements in a high temperature combustion environment of the gas turbine. A thermocouple arrangement may include a first thermocouple leg (50) disposed within a thickness of the component. At least two or more thermocouple legs (52, 53, 54) is each electrically connected to the first leg to form individual thermocouple junctions (56, 57, 58, 59) along the first leg for conversion of respective thermal gradients to respective electrical signals, such as electromotive force (emf) based voltages. The thermocouple arrangement may be used in combination with a thermographic system (70) to calculate heat flux over a region of the turbine component.

Abstract translation: 燃气轮机部件（49）可被装配以提供表示在燃气轮机的高温燃烧环境中的热测量的多个信号。 热电偶布置可以包括设置在部件的厚度内的第一热电偶腿部（50）。 至少两个或更多个热电偶腿（52,53,54）每个电连接到第一腿以沿着第一腿形成单独的热电偶接头（56,57,58,59），用于将相应的热梯度转换成相应的电信号 ，例如基于电动势（emf）的电压。 热电偶装置可以与热成像系统（70）组合使用以计算涡轮机部件的区域上的热通量。

公开(公告)号：WO2013116079A1

公开(公告)日：2013-08-08

申请号：PCT/US2013/022929

申请日：2013-01-24

Applicant: SIEMENS ENERGY, INC. ,  BALEINE, Erwan ,  JONNALAGADDA, Vinay

Inventor： BALEINE, Erwan ,  JONNALAGADDA, Vinay

IPC: G02B23/24

CPC classification number: G02B23/2492 ,  G02B7/028 ,  G03B17/12 ,  G03B17/55 ,  H04N5/23287 ,  H04N2005/2255

Abstract: 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.

Abstract translation: 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相机系统，其处于超过600℃（1112°F）范围内的高工作温度并且包括燃烧气体污染物。 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。 非球面透镜单独或与球面透镜组合建立了更宽的视野，并且与仅包含球面透镜的透镜座相比，需要较少的透镜组合。 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：WO2013116006A1

公开(公告)日：2013-08-08

申请号：PCT/US2013/022013

申请日：2013-01-18

Applicant: SIEMENS ENERGY, INC. ,  BALEINE, Erwan ,  JONNALAGADDA, Vinay ,  SAVARD, Michael

Inventor： BALEINE, Erwan ,  JONNALAGADDA, Vinay ,  SAVARD, Michael

IPC: G02B7/02 ,  G02B23/24

CPC classification number: G02B23/2492 ,  G02B7/028 ,  G03B17/12 ,  G03B17/55 ,  H04N5/23287 ,  H04N2005/2255

Abstract: 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.

Abstract translation: 在超过600°C（1112°F）范围内的高工作温度下在线，运行的发电涡轮机，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。 透镜座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，并且与仅包含球面透镜的透镜座相比，需要较少的透镜组合。

公开(公告)号：WO2008051441A3

公开(公告)日：2008-07-03

申请号：PCT/US2007022243

申请日：2007-10-18

Applicant: SIEMENS CORP RES INC ,  SIEMENS POWER GENERATION INC ,  JONNALAGADDA VINAY ,  LEMIEUX DENNIS H ,  RAMESH VISVANATHAN ,  VOIGT MATTHIAS

Inventor： JONNALAGADDA VINAY ,  LEMIEUX DENNIS H ,  RAMESH VISVANATHAN ,  VOIGT MATTHIAS

IPC: G01J5/00 ,  G01J5/06 ,  G01J5/52 ,  G01J5/60

CPC classification number: G01J5/0003 ,  G01J5/0022 ,  G01J5/0088 ,  G01J5/06 ,  G01J5/522 ,  G01J5/60 ,  G01J2005/0059 ,  G01J2005/0077 ,  G01J2005/0081

Abstract: 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.

Abstract translation: 公开了用于在先进固定燃气轮机中对具有反射表面特性的叶片进行最大景物表面温度估计的方法。 该方法利用由在线监测系统提供的高速红外图像，该系统使用焦平面阵列（FPA）在发动机运行期间的近红外监测直至基本负载。 温度估算的一种波段方法被认为是起点。 近红外热障涂层（TBC）的较低表面发射率和较高表面反射率可能导致系统估计误差。 还公开了使用单波段方法的方法，其目的是减少最大温度下的估计误差。 提供了理论结果，数值模拟的数据和发动机测试的实际数据。 还公开了一种用于执行温度估计方法的系统。

公开(公告)号：WO2011152906A3

公开(公告)日：2012-01-26

申请号：PCT/US2011027636

申请日：2011-03-09

Applicant: SIEMENS ENERGY INC ,  LEMIEUX DENNIS H ,  SMED JAN P ,  WILLIAMS JAMES P ,  JONNALAGADDA VINAY

Inventor： LEMIEUX DENNIS H ,  SMED JAN P ,  WILLIAMS JAMES P ,  JONNALAGADDA VINAY

IPC: F01D21/00 ,  F01D25/00 ,  F02C7/00 ,  G02B23/24

CPC classification number: F01D21/003 ,  F05D2260/80 ,  G01N21/15 ,  G01N21/85 ,  G01N21/954 ,  G01N2021/151 ,  G01N2201/08 ,  G02B23/2492

Abstract: The monitoring system (10) for a gas turbine engine including a viewing tube assembly (32) having an inner end (34) and an outer end (36). 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 (68) is located at the inner end of the viewing tube assembly and an optical element (42) 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 (72) therebetween. An aperture (96) is defined in the aperture wall for passage of light from the hot gas flow path to the optical element. Swirl passages (80) 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 (72), wherein swirl passages effect a swirling movement of air in a circumferential direction within the chamber.

Abstract translation: 一种用于燃气涡轮发动机的监视系统（10），其包括具有内端（34）和外端（36）的观察管组件（32）。 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（68）位于观察管组件的内端，并且光学元件（42）位于观察管组件内邻近内端并且与孔壁间隔开以限定冷却和净化室 （72）。 在孔壁中限定出孔（96），用于将光从热气流路传到光学元件。 涡流通道（80）被限定在孔壁和光学元件之间的观察管组件中，用于使冷却空气从观察管组件外部的位置进入腔室（72），其中涡流通道影响空气的旋转运动 室内圆周方向。

公开(公告)号：WO2008051441A2

公开(公告)日：2008-05-02

申请号：PCT/US2007/022243

申请日：2007-10-18

Applicant: SIEMENS CORPORATE RESEARCH, INC. ,  SIEMENS POWER GENERATION, INC. ,  JONNALAGADDA, Vinay ,  LEMIEUX, Dennis H. ,  RAMESH, Visvanathan ,  VOIGT, Matthias

Inventor： JONNALAGADDA, Vinay ,  LEMIEUX, Dennis H. ,  RAMESH, Visvanathan ,  VOIGT, Matthias

CPC classification number: G01J5/0003 ,  G01J5/0022 ,  G01J5/0088 ,  G01J5/06 ,  G01J5/522 ,  G01J5/60 ,  G01J2005/0059 ,  G01J2005/0077 ,  G01J2005/0081

Abstract: 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.

Abstract translation: 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。