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    • 4. 发明授权
    • Optical monitoring system for a turbine engine
    • 涡轮发动机光学监测系统
    • US08439630B2
    • 2013-05-14
    • US12727582
    • 2010-03-19
    • Dennis H. LemieuxJan P. SmedJames P. WilliamsVinay Jonnalagadda
    • Dennis H. LemieuxJan P. SmedJames P. WilliamsVinay Jonnalagadda
    • G02B23/00F01D25/00
    • F01D21/003F05D2260/80G01N21/15G01N21/85G01N21/954G01N2021/151G01N2201/08G02B23/2492
    • 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.
    • 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 。
    • 6. 发明申请
    • Optical Monitoring System for a Turbine Engine
    • 涡轮发动机光学监测系统
    • US20110229307A1
    • 2011-09-22
    • US12727582
    • 2010-03-19
    • Dennis H. LemieuxJan P. SmedJames P. WilliamsVinay Jonnalagadda
    • Dennis H. LemieuxJan P. SmedJames P. WilliamsVinay Jonnalagadda
    • F02C7/18F02C7/00
    • F01D21/003F05D2260/80G01N21/15G01N21/85G01N21/954G01N2021/151G01N2201/08G02B23/2492
    • 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.
    • 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 。
    • 9. 发明申请
    • SYSTEM AND METHOD FOR ONLINE INSPECTION OF TURBINES INCLUDING TEMPERATURE AND VIBRATION COMPENSATING LENS MOUNT
    • 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
    • US20130194411A1
    • 2013-08-01
    • US13362365
    • 2012-01-31
    • Erwan BaleineVinay JonnalagaddaMichael Savard
    • Erwan BaleineVinay JonnalagaddaMichael Savard
    • H04N7/18G03B17/00
    • G02B23/2492G02B7/028G03B17/12G03B17/55
    • 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.
    • 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。