专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 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。

2. 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。

3. 发明授权

US07231817B2 Inspection system for a turbine blade region of a turbine engine 有权
标题翻译：涡轮发动机的涡轮叶片区域的检查系统
公开(公告)号：US07231817B2
公开(公告)日：2007-06-19
申请号：US11036993
申请日：2005-01-18
申请人： Jan P. Smed , Dennis H. Lemieux , James P. Williams
发明人： Jan P. Smed , Dennis H. Lemieux , James P. Williams
IPC分类号： G01L3/26 , G01L5/13 , G01M15/00
CPC分类号： G01M15/10 , F01D21/003 , F05D2260/80
摘要： An inspection system formed at least from a viewing tube for inspecting aspects of a turbine engine during operation of the turbine engine. An outer housing of the viewing tube may be positioned within a turbine engine using at least one bearing configured to fit into an indentation of a support housing to form a ball and socket joint enabling the viewing tube to move during operation as a result of vibrations and other movements. The viewing tube may also include one or more lenses positioned within the viewing tube for viewing the turbine components. The lenses may be kept free of contamination by maintaining a higher pressure in the viewing tube than a pressure outside of the viewing tube and enabling gases to pass through an aperture in a cap at a viewing end of the viewing tube.
摘要翻译：至少从观察管形成的检查系统，用于在涡轮发动机的运行期间检查涡轮发动机的方面。观察管的外壳可以使用至少一个轴承来定位在涡轮发动机内，所述至少一个轴承配置成装配到支撑壳体的凹陷中以形成球窝接头，使得观察管在操作期间由于振动而移动，并且其他动作。观察管还可以包括位于观察管内的一个或多个透镜，用于观察涡轮机部件。通过在观察管中保持较高的压力，透镜可以保持没有污染，而不是观察管外的压力，并且使得气体能够通过观察管的观察端处的盖中的孔。

4. 发明授权

US09182285B2 Methods regarding optical probe having an inner tube with separable tube sections to house optical elements 有权
标题翻译：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
申请人： Dennis H. Lemieux , David W. Fox , James P. Williams , Jan P. Smed , Paul J. Zombo
发明人： Dennis H. Lemieux , David W. Fox , James P. Williams , Jan P. Smed , Paul J. Zombo
IPC分类号： G01M15/00 , A61B1/00 , G02B23/24 , 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。

5. 发明申请

US20150047166A1 METHODS REGARDING OPTICAL PROBE HAVING AN INNER TUBE WITH SEPARABLE TUBE SECTIONS TO HOUSE OPTICAL ELEMENTS 有权
标题翻译：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
申请人： Dennis H. Lemieux , David W. Fox , James P. Williams , Jan P. Smed , Paul J. Zombo
发明人： Dennis H. Lemieux , David W. Fox , James P. Williams , Jan P. Smed , Paul J. Zombo
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。

6. 发明申请

US20080101683A1 System and method of evaluating uncoated turbine engine components 审中-公开
标题翻译：评估未涂覆的涡轮发动机部件的系统和方法
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
IPC分类号： G01M15/14 , G01N25/72 , G06K9/00 , G02F1/01 , H01L31/00
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。

7. 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。

8. 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。

9. 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。

10. 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。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式