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公开(公告)号：US10704958B2
公开(公告)日：2020-07-07
申请号：US13274766
申请日：2011-10-17
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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2.发明授权System for monitoring a high-temperature region of interest in a turbine engine 有权用于监测涡轮发动机中的高温感兴趣区域的系统公开(公告)号：US09015002B2
公开(公告)日：2015-04-21
申请号：US13274692
申请日：2011-10-17
CPC分类号： G01J5/00 , G01J5/0022 , G01J5/0088 , G01J5/08 , G01J5/0821 , G01J5/0859 , G01J2005/0077
摘要： A system (8) for monitoring a high-temperature region of interest in a turbine engine (10) is provided. The system includes an internally cooled stationary vane (12) located in a path of a working gas of the turbine. A monitoring port (14) is located in the stationary vane. A monitoring instrument (16) is operatively connected to the monitoring port of the stationary vane to provide a field of view of the region of interest.
摘要翻译： 提供了一种用于监测涡轮发动机（10）中的高温感兴趣区域的系统（8）。 该系统包括位于涡轮机的工作气体的路径中的内部冷却的固定叶片（12）。 监测口（14）位于固定叶片中。 监测仪器（16）可操作地连接到静止叶片的监测端口，以提供感兴趣区域的视场。
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3.发明申请公开(公告)号：US20120101769A1
公开(公告)日：2012-04-26
申请号：US13274692
申请日：2011-10-17
CPC分类号： G01J5/00 , G01J5/0022 , G01J5/0088 , G01J5/08 , G01J5/0821 , G01J5/0859 , G01J2005/0077
摘要： A system (8) for monitoring a high-temperature region of interest in a turbine engine (10) is provided. The system includes an internally cooled stationary vane (12) located in a path of a working gas of the turbine. A monitoring port (14) is located in the stationary vane. A monitoring instrument (16) is operatively connected to the monitoring port of the stationary vane to provide a field of view of the region of interest.
摘要翻译： 提供了一种用于监测涡轮发动机（10）中的高温感兴趣区域的系统（8）。 该系统包括位于涡轮机的工作气体的路径中的内部冷却的固定叶片（12）。 监测口（14）位于固定叶片中。 监测仪器（16）可操作地连接到静止叶片的监测端口，以提供感兴趣区域的视场。
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4.发明申请公开(公告)号：US20150132102A1
公开(公告)日：2015-05-14
申请号：US14077338
申请日：2013-11-12
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。
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5.发明授权Apparatus and method for temperature mapping a rotating turbine component in a high temperature combustion environment 有权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
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。
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6.发明授权Methods regarding optical probe having an inner tube with separable tube sections to house optical elements 有权关于光学探头的方法，具有具有可分离的管部分以容纳光学元件的内管公开(公告)号：US09182285B2
公开(公告)日：2015-11-10
申请号：US14077443
申请日：2013-11-12
CPC分类号： G01J5/0088 , A61B1/0011 , A61B1/0017 , G01J2005/0077 , G02B23/2423 , G02B23/2476 , G02B23/2492 , Y10T29/49718 , Y10T29/49721 , Y10T29/49723 , Y10T29/4973 , Y10T29/49789 , Y10T29/49794 , Y10T29/49798 , Y10T29/49826
摘要： In an optical probe (10) having an inner tube (30) arranged to house one or more optical elements (32), a method is provided which allows constructing the inner tube to have at least two corresponding inner tube sections (32, 34) separable from one another along a longitudinal axis of the inner tube. While corresponding inner tube sections (32, 34) are detached from one another, one or more of the optical elements may be disposed into either of the inner tube sections. The inner tube sections may be attached to one another by way of at least one removable affixing element to facilitate servicing of the probe.
摘要翻译： 在具有布置成容纳一个或多个光学元件（32）的内管（30）的光学探针（10）中，提供一种允许构造内管以具有至少两个对应的内管部分（32,34）的方法， 沿着内管的纵向轴线彼此分离。 当对应的内管部分（32,34）彼此分离时，一个或多个光学元件可以设置在任一个内管部分中。 内管部分可以通过至少一个可拆卸的固定元件彼此附接，以便于探针的维修。
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7.发明申请METHODS REGARDING OPTICAL PROBE HAVING AN INNER TUBE WITH SEPARABLE TUBE SECTIONS TO HOUSE OPTICAL ELEMENTS 有权关于具有可分离管段的内管的光学探针对住宅光学元件的方法公开(公告)号：US20150047166A1
公开(公告)日：2015-02-19
申请号：US14077443
申请日：2013-11-12
IPC分类号： G01J5/00
CPC分类号： G01J5/0088 , A61B1/0011 , A61B1/0017 , G01J2005/0077 , G02B23/2423 , G02B23/2476 , G02B23/2492 , Y10T29/49718 , Y10T29/49721 , Y10T29/49723 , Y10T29/4973 , Y10T29/49789 , Y10T29/49794 , Y10T29/49798 , Y10T29/49826
摘要： In an optical probe (10) having an inner tube (30) arranged to house one or more optical elements (32), a method is provided which allows constructing the inner tube to have at least two corresponding inner tube sections (32, 34) separable from one another along a longitudinal axis of the inner tube. While corresponding inner tube sections (32, 34) are detached from one another, one or more of the optical elements may be disposed into either of the inner tube sections. The inner tube sections may be attached to one another by way of at least one removable affixing element to facilitate servicing of the probe.
摘要翻译： 在具有布置成容纳一个或多个光学元件（32）的内管（30）的光学探针（10）中，提供一种允许构造内管以具有至少两个对应的内管部分（32,34）的方法， 沿着内管的纵向轴线彼此分离。 当对应的内管部分（32,34）彼此分离时，一个或多个光学元件可以设置在任一个内管部分中。 内管部分可以通过至少一个可拆卸的固定元件彼此附接，以便于探针的维修。
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8.发明申请Apparatus and Method for Temperature Mapping a Rotating Turbine Component in a High Temperature Combustion Environment 有权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
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。
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9.发明申请公开(公告)号：US20080101683A1
公开(公告)日：2008-05-01
申请号：US11800789
申请日：2007-05-07
申请人： Paul J. Zombo , Michael Twerdochlib , Jan P. Smed , Dennis H. Lemieux , Evangelos V. Diatzikis , Hans-Gerd Brummel
发明人： Paul J. Zombo , Michael Twerdochlib , Jan P. Smed , Dennis H. Lemieux , Evangelos V. Diatzikis , Hans-Gerd Brummel
CPC分类号： G01N25/72 , F01D21/003 , F01D21/12 , F05D2270/112 , F05D2270/3032 , F05D2270/44 , G01J5/0022 , G01J2005/0077 , G01M15/14
摘要： Aspects of the invention are directed to a visual-based system and method for non-destructively evaluating an uncoated turbine engine component. Aspects of the invention are well suited for high speed, high temperature components. Radiant energy emitted from an uncoated turbine engine component can be captured remotely and converted into a useful form, such as a high resolution image of the component. A plurality of images of the component can be captured over time and evaluated to identify failure modes. The system can also measure and map the temperature and/or radiance of the component. The system can facilitate the non-destructive evaluation of uncoated turbine components during engine operation without disassembly of the engine, thereby providing significant time and cost savings. Further, the system presents data to a user with sufficient context that allows an engine operator can evaluate the information with an increased degree of confidence and certainty.
摘要翻译： 本发明的方面涉及一种用于非破坏性评估未涂覆的涡轮发动机部件的基于视觉的系统和方法。 本发明的方面非常适用于高速，高温组件。 从未涂覆的涡轮发动机部件发射的辐射能量可以被远程捕获并转换成有用的形式，例如部件的高分辨率图像。 可以随时间捕获组件的多个图像，并进行评估以识别故障模式。 该系统还可以测量和映射组件的温度和/或辐射。 该系统可以促进在发动机运行期间对未涂覆的涡轮机部件进行非破坏性评估，而无需拆卸发动机，从而节省大量的时间和成本。 此外，系统向具有足够上下文的用户呈现数据，允许引擎操作者可以以更高的置信度和确定性来评估信息。
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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
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。
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