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1.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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2.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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3.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：US07231817B2
公开(公告)日：2007-06-19
申请号：US11036993
申请日：2005-01-18
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。
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公开(公告)号：US20110229307A1
公开(公告)日：2011-09-22
申请号：US12727582
申请日：2010-03-19
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 。
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公开(公告)号：US08439630B2
公开(公告)日：2013-05-14
申请号：US12727582
申请日：2010-03-19
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 。
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公开(公告)号：US4576548A
公开(公告)日：1986-03-18
申请号：US571612
申请日：1984-01-17
CPC分类号： F01D11/005
摘要： An arrangement is provided for statically sealing between the inner shroud 12 of individual stator vanes of a gas turbine, and a seal housing 14 provided with a radially outwardly open channel 22 into which is received a plurality of outer seal segments 24, and which includes a radially outwardly open channel 33 throughout the length of each outer seal segment and with a plurality of inner seal segments received in the channel, with the outer seal segments being biased outwardly by the springs 36, and the inner seal segments 34 being biased outwardly into sealing contact with individual inner shrouds by the concentric inner compression springs 38 carried by the outer seal segments 24.
摘要翻译： 提供了一种用于在燃气轮机的单个定子叶片的内护罩12和设置有径向向外敞开的通道22的密封壳体14之间进行静态密封的装置，容纳多个外部密封段24的管道22包括一个 径向向外开放的通道33遍及每个外部密封段的整个长度，并且多个内部密封段被容纳在通道中，其中外部密封段被弹簧36向外偏压，并且内部密封段34被向外偏压到密封 通过由外部密封段24承载的同心内部压缩弹簧38与各个内部护罩接触。
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公开(公告)号：US06883807B2
公开(公告)日：2005-04-26
申请号：US10244132
申请日：2002-09-13
申请人： Jan P. Smed
发明人： Jan P. Smed
CPC分类号： F01D11/005 , F05D2240/55 , F16J15/0887
摘要： A turbine seal closure mechanism for sealing an opening in a turbine component or between one or more turbine components. The turbine seal may include a main body having a longitudinal axis positioned transverse to the axial direction of the turbine and having at least one arm for sealing the main body to a surface of a turbine component and configured to fit within a recess in a turbine component. The turbine seal may also have one or more arms coupled to a side of the main body opposite to the first side having arms attached thereto for sealing the turbine seal to another turbine surface.
摘要翻译： 一种用于密封涡轮机部件中的开口或者在一个或多个涡轮机部件之间的涡轮机密封闭合机构。 涡轮机密封件可以包括主体，该主体具有横向于涡轮机的轴向方向的纵向轴线，并且具有至少一个臂，用于将主体密封到涡轮机部件的表面并且被构造成装配在涡轮部件的凹部内 。 涡轮机密封件还可以具有联接到主体的与第一侧相对的侧面的一个或多个臂，其具有附接到其上的臂，用于将涡轮机密封件密封到另一个涡轮机表面。
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公开(公告)号：US4887432A
公开(公告)日：1989-12-19
申请号：US255577
申请日：1988-10-07
申请人： Stephen E. Mumford , Jan P. Smed
发明人： Stephen E. Mumford , Jan P. Smed
CPC分类号： F23R3/045
摘要： A gas turbine combustion chamber with an inlet and outlet has apertures in the combustion chamber wall and air scoops provided in the apertures, the air scoops having an outer tubular member and coaxially spaced inner tubular member. The spaced tubular members have inner cylindrical portions and outwardly extending flanges, with spacers disposed between and secured to the flanges with cooling air passing therebetween and through the annular air flow passage into the combustion chamber. Preferably, a radially outwardly extending arcuate section on the inner tubular member has a radius at least about one-third of the inner diameter of the inner cylindrical portion thereof.
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公开(公告)号：US4863343A
公开(公告)日：1989-09-05
申请号：US194689
申请日：1988-05-16
申请人： Jan P. Smed
发明人： Jan P. Smed
CPC分类号： F01D11/005 , F01D9/042
摘要： In an axial flow turbine having a casing disposed about a rotor, a liner also disposed about the rotor and in a radially spaced relationship with the casing, such that the spaced relationship defines an annular opening, and an annular row of stationary blades positioned within the annular opening, apparatus for maintaining the efficiency of said turbine is shown to include a sealing mechanism, connected to the stationary blades, for preventing motive fluid applied to the annular opening from circumventing the stationary blades so that the efficiency of the turbine is maintained. The sealing mechanism includes a pair of sealing bars disposed between the stationary blades, the casing and the liner.
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