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公开(公告)号：US09062557B2
公开(公告)日：2015-06-23
申请号：US13226547
申请日：2011-09-07
申请人： Kok-Mun Tham , Ching-Pang Lee , Abdullatif M. Chehab , Gm Salam Azad , Shantanu P. Mhetras , Manjit Shivanand , Vincent P. Laurello , Christopher Rawlings
发明人： Kok-Mun Tham , Ching-Pang Lee , Abdullatif M. Chehab , Gm Salam Azad , Shantanu P. Mhetras , Manjit Shivanand , Vincent P. Laurello , Christopher Rawlings
CPC分类号： F01D11/001 , F01D11/04
摘要： A gas turbine having rotor discs (9), a disc cavity (13) and a stator stage (25) extending to the disc cavity (13). Seal housing flanges (43, 44) extend from a seal housing (29) of the stator stage (25). Rotor flanges (41i, 41o) extend from a rotor disk (9-1). An inner rotor flange (41i) and first seal housing flange (43) are inward from a second seal housing flange (44). One rotor flange (41o) is outward from the second seal housing flange (44). The inner rotor flange (41i) and first seal housing flange (43) extend toward one another to limit movement of main gas flow (17). An inlet (47) injects air (50) between the outward rotor flange (41o) and second seal housing flange (44).
摘要翻译： 一种具有转子盘（9），延伸到盘腔（13）的盘腔（13）和定子级（25）的燃气轮机。 密封壳体凸缘（43,44）从定子台（25）的密封壳体（29）延伸。 转子凸缘（41i，41o）从转子盘（9-1）延伸。 内转子凸缘（41i）和第一密封壳体凸缘（43）从第二密封壳体凸缘（44）向内。 一个转子凸缘（41o）从第二密封壳体凸缘（44）向外。 内转子凸缘（41i）和第一密封壳体凸缘（43）朝向彼此延伸以限制主气流（17）的移动。 入口（47）在外转子凸缘（41o）和第二密封壳体凸缘（44）之间注入空气（50）。
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公开(公告)号：US08820091B2
公开(公告)日：2014-09-02
申请号：US13670788
申请日：2012-11-07
申请人： Kok-Mun Tham , Ching-Pang Lee , Vincent P. Laurello , Abdullatif M. Chehab , David A. Kemp , John A. Fussner , Yan Yin , Bijay K. Sultanian , Weidong Cai
发明人： Kok-Mun Tham , Ching-Pang Lee , Vincent P. Laurello , Abdullatif M. Chehab , David A. Kemp , John A. Fussner , Yan Yin , Bijay K. Sultanian , Weidong Cai
摘要： A cooling fluid air injection system for use in a gas turbine engine includes at an external cooling fluid source, at least one rotor cooling pipe, which is used to inject cooling fluid from the source into a rotor chamber, a piping system that provides fluid communication between the source and the rotor cooling pipe(s), a blower system for conveying the cooling fluid through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent cooling fluid from the source from passing through the piping system, and open during less than full load engine operation to allow cooling fluid from the source to pass through the piping system.
摘要翻译： 用于燃气涡轮发动机的冷却流体空气喷射系统包括在外部冷却流体源处的至少一个转子冷却管，其用于将来自所述源的冷却流体注入到转子室中;提供流体连通的管道系统 在源和转子冷却管之间，用于将冷却流体通过管道系统和转子冷却管输送到转子室中的鼓风机系统和阀系统。 在全负载发动机运行期间，阀系统关闭，以防止来自源的冷却流体通过管道系统，并且在小于满载发动机运行期间打开以允许来自源的冷却流体通过管道系统。
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公开(公告)号：US20140123657A1
公开(公告)日：2014-05-08
申请号：US13670788
申请日：2012-11-07
申请人： Kok-Mun Tham , Ching-Pang Lee , Vincent P. Laurello , Abdullatif M. Chehab , David A. Kemp , John A. Fussner , Yan Yin , Bijay K. Sultanian , Weidong Cai
发明人： Kok-Mun Tham , Ching-Pang Lee , Vincent P. Laurello , Abdullatif M. Chehab , David A. Kemp , John A. Fussner , Yan Yin , Bijay K. Sultanian , Weidong Cai
IPC分类号： F02C7/12
摘要： A cooling fluid air injection system for use in a gas turbine engine includes at an external cooling fluid source, at least one rotor cooling pipe, which is used to inject cooling fluid from the source into a rotor chamber, a piping system that provides fluid communication between the source and the rotor cooling pipe(s), a blower system for conveying the cooling fluid through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent cooling fluid from the source from passing through the piping system, and open during less than full load engine operation to allow cooling fluid from the source to pass through the piping system.
摘要翻译： 用于燃气涡轮发动机的冷却流体空气喷射系统包括在外部冷却流体源处的至少一个转子冷却管，其用于将来自所述源的冷却流体注入到转子室中;提供流体连通的管道系统 在源和转子冷却管之间，用于将冷却流体通过管道系统和转子冷却管输送到转子室中的鼓风机系统和阀系统。 在全负载发动机运行期间，阀系统关闭，以防止来自源的冷却流体通过管道系统，并且在小于满载发动机运行期间打开以允许来自源的冷却流体通过管道系统。
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4.发明申请SEAL SYSTEM FOR COOLING FLUID FLOW THROUGH A ROTOR ASSEMBLY IN A GAS TURBINE ENGINE 审中-公开用于通过气体涡轮发动机中的转子组件冷却流体的密封系统公开(公告)号：US20120183389A1
公开(公告)日：2012-07-19
申请号：US13005752
申请日：2011-01-13
IPC分类号： F01D5/18
CPC分类号： F01D5/3015
摘要： A sealing system for a rotor assembly in a gas turbine engine is disclosed. The sealing system may include a seal formed from a side block and an upper seal that seals a gap between a radially outward extending first rotor supply channel in a rotor assembly terminating at an inlet of an axially extending second rotor supply channel that is in fluid communication with an internal blade cooling system of a turbine blade. The seal may include components that enhance the flow of cooling fluids over conventional configurations. In another embodiment, the sealing system may include an integrated sealing block configured to seal a gap between adjacent turbine blades at an intersection between the first and second rotor supply channels. The integrated sealing block may be formed from a radially inward extending leg and central body.
摘要翻译： 公开了一种用于燃气涡轮发动机中的转子组件的密封系统。 密封系统可以包括由侧块形成的密封件和上密封件，其密封位于轴向延伸的第二转子供应通道的入口处的转子组件中的径向向外延伸的第一转子供应通道之间的间隙，该第二转子供应通道处于流体连通 具有涡轮叶片的内部叶片冷却系统。 密封件可以包括增强冷却流体超过常规结构的流动的部件。 在另一个实施例中，密封系统可以包括集成密封块，其被配置为在第一和第二转子供应通道之间的交叉处密封相邻涡轮叶片之间的间隙。 集成密封块可以由径向向内延伸的腿和中心体形成。
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公开(公告)号：US20140119880A1
公开(公告)日：2014-05-01
申请号：US13663737
申请日：2012-10-30
CPC分类号： F01D9/065 , F01D25/162 , F02C7/18 , F05D2260/601
摘要： A turbine engine including an intermediate space defined between outer and inner portions of the turbine engine. A flow energizer is provided including a flow body located within the intermediate space and including an inlet port, an outlet port and a flow passage extending within the flow body between the inlet and outlet ports. The inlet port receives a flow of a first medium located within the intermediate space and the flow body injects an energizing flow of a second medium to a portion of the first medium within the flow body to create an energized flow of a mixed medium from the outlet portion, the energized flow of mixed medium creates a flow of the first medium adjacent to the flow body within the intermediate space.
摘要翻译： 一种涡轮发动机，包括在涡轮发动机的外部和内部之间限定的中间空间。 提供了一种流动增压器，其包括位于中间空间内的流动体，并且包括入口端口，出口端口和在入口和出口之间的流体内延伸的流动通道。 入口端口接收位于中间空间内的第一介质流，并且流体将第二介质的通电流注入流体内的第一介质的一部分，以从出口产生混合介质的通电流 混合介质的通电流在中间空间内产生与流体相邻的第一介质的流动。
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公开(公告)号：US08684669B2
公开(公告)日：2014-04-01
申请号：US13027354
申请日：2011-02-15
IPC分类号： F01D11/14
CPC分类号： F01D11/122 , F01D17/02 , F05D2240/11 , G01B5/14
摘要： A measuring assembly for use in a gas turbine engine includes an indicia portion that extends radially inwardly from an inner surface of a ring seal structure to a location radially inwardly from tips of blades mounted on a rotor. The indicia portion of the measuring assembly comprises a section that is abraded by the blades during rotational movement of the rotor to provide a visual indication of a distance between the tips of the blades and the inner surface.
摘要翻译： 用于燃气涡轮发动机的测量组件包括从环形密封结构的内表面径向向内延伸到从安装在转子上的叶片的尖端径向向内的位置的标记部分。 测量组件的标记部分包括在转子的旋转运动期间被叶片磨损的部分，以提供叶片的尖端和内表面之间的距离的视觉指示。
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7.发明申请INNER RING WITH INDEPENDENT THERMAL EXPANSION FOR MOUNTING GAS TURBINE FLOW PATH COMPONENTS 有权具有独立热膨胀的内环，用于安装气体涡轮机流路组件公开(公告)号：US20100031671A1
公开(公告)日：2010-02-11
申请号：US11506096
申请日：2006-08-17
CPC分类号： F01D25/246 , F01D11/18 , F05D2230/60 , F05D2230/642 , F05D2300/50212 , Y10T29/4932 , Y10T29/49323
摘要： An inner mounting ring (20) for gas turbine flow path components such as shroud ring segments (24). The inner ring (20) may be mounted to an outer ring (22) on radially slidable mounts (26, 28) that maintain the two rings (20, 22) in coaxial relationship, but allows them to thermally expand at different rates. This allows matching of the radial expansion rate of the inner ring (20) to that of the turbine blade tips (32), thus providing reduced clearance (33) between the turbine blade tips (32) and the inner surface of the shroud ring segments (24) under all engine operating conditions. The inner ring (20) may be made of a material with a lower coefficient of thermal expansion than that of the outer ring (22).
摘要翻译： 用于燃气轮机流动路径部件（例如护罩环段）的内部安装环（20）。 内环（20）可以安装在径向可滑动的安装件（26,28）上的外环（22）上，其保持两个环（20,22）处于同轴的关系，但允许它们以不同的速率热膨胀。 这允许内环（20）的径向膨胀速率与涡轮叶片尖端（32）的径向膨胀速率匹配，从而在涡轮叶片尖端（32）和护罩环段的内表面之间提供减小的间隙（33） （24）在所有发动机运行条件下。 内圈（20）可以由比外圈（22）的热膨胀系数低的材料制成。
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公开(公告)号：US09091171B2
公开(公告)日：2015-07-28
申请号：US13663737
申请日：2012-10-30
CPC分类号： F01D9/065 , F01D25/162 , F02C7/18 , F05D2260/601
摘要： A turbine engine including an intermediate space defined between outer and inner portions of the turbine engine. A flow energizer is provided including a flow body located within the intermediate space and including an inlet port, an outlet port and a flow passage extending within the flow body between the inlet and outlet ports. The inlet port receives a flow of a first medium located within the intermediate space and the flow body injects an energizing flow of a second medium to a portion of the first medium within the flow body to create an energized flow of a mixed medium from the outlet portion, the energized flow of mixed medium creates a flow of the first medium adjacent to the flow body within the intermediate space.
摘要翻译： 一种涡轮发动机，包括在涡轮发动机的外部和内部之间限定的中间空间。 提供了一种流动增压器，其包括位于中间空间内的流动体，并且包括入口端口，出口端口和在入口和出口之间的流体内延伸的流动通道。 入口端口接收位于中间空间内的第一介质流，并且流体将第二介质的通电流注入流体内的第一介质的一部分，以从出口产生混合介质的通电流 混合介质的通电流在中间空间内产生与流体相邻的第一介质的流动。
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公开(公告)号：US09068906B2
公开(公告)日：2015-06-30
申请号：US14043878
申请日：2013-10-02
CPC分类号： G01M15/02 , F01D5/30 , F01D5/32 , F01D11/14 , F01D11/20 , F01D11/22 , F01D17/02 , F01D17/20 , F01D17/24 , F01D21/003 , F16M13/02 , G01B11/14 , G01B21/16
摘要： Turbine blade tip clearance is measured in a fully assembled turbine casing by mounting a non-contact displacement probe or sensor on a turbine blade that generates data indicative of sensor distance from the turbine casing that circumferentially surrounds the blade. The sensor is mounted on the blade with a sensor fixture, which includes a clamping mechanism and a sensor retention mechanism that retains and calibrates the sensor by selective movement of the sensor relative to the retention mechanism. Variations in sensor distance data are recorded when the turbine is operated in turning gear mode. Blade rotational position data are collected by a rotational position sensor. A data processing system correlates the distance and rotational position data with localized blade tip gap at angular positions about the turbine casing circumference. This method and apparatus facilitate assessment of turbine casing deformation impact on blade tip clearance and rotor/casing alignment.
摘要翻译： 在完全组装的涡轮机壳体中通过将非接触位移探头或传感器安装在涡轮机叶片上来测量涡轮叶片顶端间隙，该涡轮叶片产生指示周向围绕叶片的涡轮机壳体的传感器距离的数据。 传感器安装在具有传感器夹具的传感器固定装置上，传感器夹具包括夹紧机构和传感器保持机构，通过传感器相对于保持机构的选择性移动来保持和校准传感器。 传感器距离数据的变化记录在涡轮机转向齿轮模式时。 刀片旋转位置数据由旋转位置传感器收集。 数据处理系统将距离和旋转位置数据与围绕涡轮机壳体周边的角位置处的局部叶片尖端间隙相关联。 这种方法和设备有助于评估涡轮机壳体对叶片间隙和转子/壳体对准的影响。
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10.发明授权Gas turbine engine with structure for directing compressed air on a blade ring 有权具有用于将压缩空气引导到叶片环上的结构的燃气涡轮发动机公开(公告)号：US09003807B2
公开(公告)日：2015-04-14
申请号：US13291147
申请日：2011-11-08
CPC分类号： F01D11/24 , F01D25/10 , F05D2260/201
摘要： The present invention comprises a gas turbine engine and a process for operating a gas turbine engine. A fluid structure receives compressed air from a compressor and extends toward a stationary blade ring in a turbine to discharge the compressed air directly against a surface of the blade ring such that the compressed air impinges on the blade ring surface. The compressed air then passes through at least one opening in the stationary blade ring and into cooling passages of a corresponding row of vanes.
摘要翻译： 本发明包括燃气涡轮发动机和用于操作燃气涡轮发动机的过程。 流体结构从压缩机接收压缩空气并朝向涡轮机中的固定叶片环延伸，以将压缩空气直接排放到叶片环的表面上，使得压缩空气冲击叶片环表面。 然后，压缩空气通过固定叶片环中的至少一个开口并进入相应行叶片的冷却通道。
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