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1. 发明申请

US20120092179A1 System and Method for Turbine Bucket Tip Shroud Deflection Measurement 失效
标题翻译：涡轮铲斗头护罩偏心测量系统与方法
公开(公告)号：US20120092179A1
公开(公告)日：2012-04-19
申请号：US12907548
申请日：2010-10-19
申请人： KrishnaKumar PG , Daniel Howard Tragesser , Saurav Dugar , Joseph Vincent Pawlowski
发明人： KrishnaKumar PG , Daniel Howard Tragesser , Saurav Dugar , Joseph Vincent Pawlowski
IPC分类号： G08B21/00 , G01B21/16
CPC分类号： F01D21/003 , G01B21/16
摘要： A measurement system measures a gap between a plurality of rotating bucket tips and a stationary shroud surface. The system includes a sensor secured to the shroud surface, where the sensor senses a distance between each of the rotating bucket tips and the shroud surface, and a key phasor indexing each of the plurality of rotating bucket tips. A processor receives data from the sensor and the key phasor and calculates a shift against each of the plurality of buckets. The processor determines a time to bucket replacement based on current service hours of the plurality of rotating buckets tips.
摘要翻译：测量系统测量多个旋转铲斗前端和固定护罩表面之间的间隙。该系统包括固定到护罩表面的传感器，其中传感器感测每个旋转铲斗前端和护罩表面之间的距离，以及将多个旋转铲斗前端中的每一个分开的按键相量。处理器从传感器和键相量接收数据，并计算针对多个桶中的每一个的移位。处理器基于多个旋转铲斗尖端的当前服务时间确定铲斗更换的时间。

2. 发明授权

US08593296B2 System and method for turbine bucket tip shroud deflection measurement 失效
标题翻译：涡轮叶片护罩挠度测量系统及方法
公开(公告)号：US08593296B2
公开(公告)日：2013-11-26
申请号：US12907548
申请日：2010-10-19
申请人： KrishnaKumar Pg , Daniel Howard Tragesser , Saurav Dugar , Joseph Vincent Pawlowski
发明人： KrishnaKumar Pg , Daniel Howard Tragesser , Saurav Dugar , Joseph Vincent Pawlowski
IPC分类号： G08B21/00
CPC分类号： F01D21/003 , G01B21/16
摘要： A measurement system measures a gap between a plurality of rotating bucket tips and a stationary shroud surface. The system includes a sensor secured to the shroud surface, where the sensor senses a distance between each of the rotating bucket tips and the shroud surface, and a key phasor indexing each of the plurality of rotating bucket tips. A processor receives data from the sensor and the key phasor and calculates a shift against each of the plurality of buckets. The processor determines a time to bucket replacement based on current service hours of the plurality of rotating buckets tips.
摘要翻译：测量系统测量多个旋转铲斗前端和固定护罩表面之间的间隙。该系统包括固定到护罩表面的传感器，其中传感器感测每个旋转铲斗前端和护罩表面之间的距离，以及将多个旋转铲斗前端中的每一个分开的按键相量。处理器从传感器和键相量接收数据，并计算针对多个桶中的每一个的移位。处理器基于多个旋转铲斗尖端的当前服务时间确定铲斗更换的时间。

3. 发明申请

US20120121424A1 TURBINE BLADE COMBINED DAMPER AND SEALING PIN AND RELATED METHOD 有权
标题翻译：涡轮叶片组合阻尼器和密封件及相关方法
公开(公告)号：US20120121424A1
公开(公告)日：2012-05-17
申请号：US12948364
申请日：2010-11-17
申请人： Stephen Paul WASSYNGER , Daniel Howard TRAGESSER , Matthew Durham COLLIER
发明人： Stephen Paul WASSYNGER , Daniel Howard TRAGESSER , Matthew Durham COLLIER
IPC分类号： F01D5/26
CPC分类号： F01D5/24 , F01D5/22 , F01D11/006 , F05D2260/96
摘要： A damper pin for a turbine bucket includes an elongated main body portion having a first substantially uniform cross-sectional shape and axially-aligned, leading and trailing end portions having a second relatively smaller cross-sectional shape at opposite ends of the main body portion. A seal element is provided on one or both of the opposite leading and trailing end portions projecting radially outwardly beyond the main body portion.
摘要翻译：用于涡轮机叶片的阻尼器销包括细长主体部分，其具有第一基本上均匀的横截面形状，并且在主体部分的相对端处具有第二相对较小横截面形状的轴向对准的前端部和后端部。在相对的前端部和后端部之间的一个或两个上设置有密封元件，其径向向外突出超过主体部分。

4. 发明授权

US08876478B2 Turbine blade combined damper and sealing pin and related method 有权
标题翻译：涡轮叶片组合阻尼器和密封销及相关方法
公开(公告)号：US08876478B2
公开(公告)日：2014-11-04
申请号：US12948364
申请日：2010-11-17
申请人： Stephen Paul Wassynger , Daniel Howard Tragesser , Matthew Durham Collier
发明人： Stephen Paul Wassynger , Daniel Howard Tragesser , Matthew Durham Collier
IPC分类号： F01D5/10 , F01D5/26 , F01D25/04 , F01D5/24 , F01D11/00
CPC分类号： F01D5/24 , F01D5/22 , F01D11/006 , F05D2260/96
摘要： A damper pin for a turbine bucket includes an elongated main body portion having a first substantially uniform cross-sectional shape and axially-aligned, leading and trailing end portions having a second relatively smaller cross-sectional shape at opposite ends of the main body portion. A seal element is provided on one or both of the opposite leading and trailing end portions projecting radially outwardly beyond the main body portion.
摘要翻译：用于涡轮机叶片的阻尼器销包括细长主体部分，其具有第一基本上均匀的横截面形状，并且在主体部分的相对端处具有第二相对较小横截面形状的轴向对准的前端部和后端部。在相对的前端部和后端部之间的一个或两个上设置有密封元件，其径向向外突出超过主体部分。

5. 发明申请

US20120107135A1 APPARATUS, SYSTEMS AND METHODS FOR COOLING THE PLATFORM REGION OF TURBINE ROTOR BLADES 审中-公开
标题翻译：用于冷却涡轮转子叶片平台区域的装置，系统和方法
公开(公告)号：US20120107135A1
公开(公告)日：2012-05-03
申请号：US12915501
申请日：2010-10-29
申请人： John Wesley Harris, JR. , Daniel Howard Tragesser , Anthony Louis Giglio
发明人： John Wesley Harris, JR. , Daniel Howard Tragesser , Anthony Louis Giglio
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D5/186 , F01D5/187 , F05D2240/81 , F05D2260/202 , Y02T50/676 , Y10T29/49341
摘要： A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root, wherein the rotor blade includes an interior cooling passage that extends to the approximate radial height of the platform, and wherein, a pressure side of the platform comprises a planar topside that extends circumferentially from the airfoil to a pressure side slashface, and a suction side of the platform comprises a substantially planar topside that extends circumferentially from the airfoil to a suction side slashface. The platform cooling arrangement may include a linear plenum residing just inboard of the planar topside and linearly extending through the platform from either the pressure side slashface or the suction side slashface to a connection with the interior cooling passage, the linear plenum having a longitudinal axis that is approximately parallel to the planar topside; and a plurality of cooling apertures linearly extending from a topside outlet formed on the topside of the platform to a connection with the linear plenum, wherein the cooling apertures are configured such that each forms an acute angle with the topside of the platform.
摘要翻译：涡轮转子叶片中的平台冷却装置，其具有在翼型件和根部之间的界面处的平台，其中转子叶片包括延伸到平台的近似径向高度的内部冷却通道，并且其中，平台包括从翼型件到圆周方向延伸到压力侧斜面的平面顶面，并且平台的吸力侧包括从翼型件周向延伸到吸力侧斜面的基本平坦的顶侧。平台冷却装置可以包括位于平坦顶侧的刚好内侧并且从压力侧斜面或吸力侧斜面直线延伸穿过平台的线性增压室到与内部冷却通道的连接，线性增压室具有纵向轴线，大致平行于平面顶面; 以及多个冷却孔，其从形成在所述平台顶部上的顶部出口线性地延伸到与所述线性压力室的连接，其中所述冷却孔配置成使得每个与所述平台的顶侧形成锐角。

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