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1. 发明申请

WO2021216090A1 NON-CONTACT SEAL ASSEMBLY IN GAS TURBINE ENGINE 审中-公开
公开(公告)号：WO2021216090A1
公开(公告)日：2021-10-28
申请号：PCT/US2020/029861
申请日：2020-04-24
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： KHANNA, Maneesh , BAKER, Jonathon , PILAPIL, Patrick , ROSS, Christopher , CHEHAB, Abdullatif M. , PELTIER, Vincent
IPC分类号： F01D11/00 , F01D11/02
摘要： A gas turbine engine includes a stationary component, a rotating component rotatable relative to the stationary component, and a non-contact seal assembly arranged between the stationary component and rotating component to seal a gap therebetween. The non-contact seal assembly includes a plurality of seal segments circumferentially arranged adjacent to and spaced apart from each other. Each seal segment includes a seal carrier attached to the stationary component, a seal shoe movable with respect to the rotating component and the seal carrier, a coupling assembly separate from the seal carrier and seal shoe and coupled to the seal carrier and seal shoe to allow movement of the seal shoe, a back plate connected to the seal carrier, and a front plate connected to the seal carrier such that the seal carrier is disposed between the back plate and the front plate.

2. 发明申请

WO2014164724A1 TURBINE ENGINE SHUTDOWN TEMPERATURE CONTROL SYSTEM WITH NOZZLE INJECTION FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：涡轮发动机喷油温度控制系统，用于气体涡轮发动机喷嘴注射
公开(公告)号：WO2014164724A1
公开(公告)日：2014-10-09
申请号：PCT/US2014/023326
申请日：2014-03-11
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： LOHSE, Uwe , LANDRUM, Evan C. , ZHANG, Jiping , CHEHAB, Abdullatif M.
IPC分类号： F01D25/26 , F01D11/24 , F01D21/12
CPC分类号： F02C7/26 , F01D11/24 , F01D21/12 , F01D25/26 , F05D2250/18 , F05D2260/201
摘要： A turbine engine shutdown temperature control system (10) configured to limit thermal gradients from being created within an outer casing (12) surrounding a turbine blade assembly (14) during shutdown of a gas turbine engine (16) is disclosed. By reducing thermal gradients caused by hot air buoyancy within the mid-region cavities (18) in the outer casing (12), arched and sway-back bending of the outer casing (12) is prevented, thereby reducing the likelihood of blade tip rub, and potential blade damage, during a warm restart of the gas turbine engine (16). The turbine engine shutdown temperature control system (10) may operate during the shutdown process where the rotor (26) is still powered by combustion gases or during turning gear system operation after shutdown of the gas turbine engine, or both, to allow the outer casing (12) to uniformly, from top to bottom, cool down.
摘要翻译：公开了一种涡轮发动机关闭温度控制系统（10），其被配置为在燃气涡轮发动机（16）关闭期间限制在围绕涡轮叶片组件（14）的外壳（12）内产生的热梯度。通过减小外壳（12）中的中间腔（18）内由热空气浮力引起的热梯度，防止了外壳（12）的拱形和摇摆弯曲，从而降低了叶片尖端摩擦的可能性，并且在燃气涡轮发动机（16）的暖启动期间具有潜在的叶片损坏。涡轮发动机关闭温度控制系统（10）可以在关闭过程中操作，其中转子（26）仍然由燃烧气体驱动，或者在关闭燃气涡轮发动机或两者之后转动齿轮系统操作期间允许外壳（12）从上到下均匀地冷却。

3. 发明申请

WO2017014737A1 GAS TURBINE SEAL ARRANGEMENT 审中-公开
标题翻译：气体涡轮密封装置
公开(公告)号：WO2017014737A1
公开(公告)日：2017-01-26
申请号：PCT/US2015/041056
申请日：2015-07-20
申请人： SIEMENS ENERGY, INC.
发明人： THAM, Kok-Mun , CHEHAB, Abdullatif M. , PILAPIL, Patrick M. , YIN, Yan , CAMPBELL, Christian Xavier , LAURELLO, Vincent Paul
IPC分类号： F01D11/00
CPC分类号： F01D11/001
摘要： A turbine arrangement including a rotor and a stator surrounding the rotor and comprising guide vane segments, each guide vane segment comprising an airfoil (14) and a radially inner vane platform (16). A seal arrangement (30) includes a static seal (31) inward from the inner vane platforms and having a radially extending face plate (34), first (36) and second (40) cylindrical seal walls extending from outer and inner ends of the annular face plate, an annular seal plate (44) extending radially from the second cylindrical seal wall, and an angel wing (48) extending between the first cylindrical seal wall (36) and the annular seal plate (44) to define a first annular cavity (C 1 ) and a second annular cavity (C 2 ). Circumferentially spaced cut-outs (68) define passages through the annular seal plate (44) between the first and second annular cavities and are aligned with fasteners (64) that attach the annular face plate (34) to a support ring (62) for supporting the inner vane platform (16).
摘要翻译：一种涡轮机装置，包括转子和围绕转子的定子，包括导叶段，每个导叶段包括翼型件（14）和径向内叶片平台（16）。密封装置（30）包括从内部叶片平台向内的静态密封件（31），并具有径向延伸的面板（34），第一（36）和第二（40）圆柱形密封壁，其从外部和内部端部延伸环形面板，从第二圆柱形密封壁径向延伸的环形密封板（44）和在第一圆柱形密封壁（36）和环形密封板（44）之间延伸的天使翼（48），以限定第一环形空腔（C1）和第二环形空腔（C2）。周向间隔开的切口（68）限定通过第一和第二环形空腔之间的环形密封板（44）的通道，并且与将环形面板（34）连接到支撑环（62）的紧固件（64）对准，用于支撑内叶片平台（16）。

4. 发明申请

WO2015191039A1 GAS TURBINE ENGINE WITH ROTOR CENTERING COOLING SYSTEM IN AN EXHAUST DIFFUSER 审中-公开
标题翻译：具有转子中心冷却系统的气体涡轮发动机在排气歧管中
公开(公告)号：WO2015191039A1
公开(公告)日：2015-12-17
申请号：PCT/US2014/041649
申请日：2014-06-10
申请人： SIEMENS ENERGY, INC.
发明人： THAM, Kok-Mun , CHEHAB, Abdullatif M. , PETERSON, Ross
IPC分类号： F01D25/10 , F01D25/14 , F02C3/04 , F01D25/12 , F01D9/06 , F01D25/30 , F02C7/18 , F01D25/28
CPC分类号： F02C7/18 , F01D9/04 , F01D9/065 , F01D25/125 , F01D25/14 , F01D25/28 , F01D25/30 , F05D2220/32 , F05D2260/205 , F05D2260/601
摘要： A gas turbine engine (10) having a rotor centering cooling system (12) for cooling struts (14) within an exhaust diffuser (16) and turbine case to reduce tip rub during hot restarts is disclosed. In particular, the rotor centering cooling system (12) may be positioned within struts (14) in the exhaust diffuser (16) downstream from a turbine assembly (18) for limiting thermal gradients between top and bottom struts (20) to prevent the exhaust bearing body (24) from becoming off-center during steady state operation as a result of the top struts (20) becoming hotter than the bottom struts. The rotor centering cooling system (12) may reduce the temperature at the exhaust diffuser (16) and turbine case, thereby reducing the thermal gradient between the top and bottom struts (20, 22) and top and bottom (28, 32) of the turbine case. As such, the exhaust bearing body (24) remains centered, thereby preventing a tighter blade tip clearance at the top (28) of the turbine assembly (18) than at the bottom (28) of the assembly (18).
摘要翻译：公开了一种燃气涡轮发动机（10），其具有用于冷却排气扩散器（16）内的支柱（14）的转子定心冷却系统（12）和涡轮壳体，以减少在热重启期间的尖端摩擦。特别地，转子定心冷却系统（12）可以位于涡轮机组件（18）下游的排气扩散器（16）的支柱（14）内，用于限制顶部和底部支柱（20）之间的热梯度，以防止排气由于顶部支柱（20）变得比底部支柱变热，所以在稳态操作期间，轴承体（24）变得偏心。转子定心冷却系统（12）可以降低排气扩散器（16）和涡轮机壳体处的温度，从而减小顶部和底部支柱（20,22）之间的热梯度以及顶部和底部（28,32）之间的热梯度。涡轮箱。这样，排气支承体24保持居中，从而防止在涡轮机组件18的顶部28处与组件18的底部28处的更紧密的叶片顶端间隙。

5. 发明申请

WO2015050657A1 TURBINE BLADE-MOUNTED SENSOR FIXTURE FOR TIP GAP MEASUREMENT 审中-公开
标题翻译：涡轮叶片安装传感器固定器，用于提前测量
公开(公告)号：WO2015050657A1
公开(公告)日：2015-04-09
申请号：PCT/US2014/053635
申请日：2014-09-02
申请人： SIEMENS ENERGY, INC.
发明人： SILIETI, Mahmood K. , HINES, Kevin L. , CHEHAB, Abdullatif M.
IPC分类号： G01B11/14 , G01B5/14
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叶片上来测量涡轮叶片顶端间隙，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夹具上，传感器夹具包括夹持机构和传感器保持机构，其通过传感器相对于保持机构的选择性运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。该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。

6. 发明申请

WO2019040171A1 SEAL PLATE ASSEMBLY 审中-公开
公开(公告)号：WO2019040171A1
公开(公告)日：2019-02-28
申请号：PCT/US2018/038675
申请日：2018-06-21
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： SCHRÖDER, Peter , ROSS, Christopher W. , GLOSS, Daniel , CHEHAB, Abdullatif M. , ARRELL, Douglas J. , SHREEDHARA, Swaroop , BAKER, Jonathon , HALCHAK, William
IPC分类号： F01D5/30 , F01D11/00 , F16J15/08
CPC分类号： F01D5/3015 , F01D11/005 , F01D11/006 , F05D2240/11 , F05D2240/57 , F05D2250/182 , F05D2260/36 , F05D2260/961 , F16J15/0887
摘要： The present invention is related to a seal plate assembly (300) for a rotor disk assembly (100) of a gas turbine engine, wherein the seal plate assembly includes a plurality of adjacent seal plate segments (320, 340). Shiplaps (322,323,342,343) of the adjacent seal plate segments are overlapped with each other. The overlapped shiplaps of the adjacent seal plate segments are configured to have different stiffness. The less stiff shiplaps deflect toward to the overlapped stiffer shiplaps such that the overlapped shiplaps move toward to each other under pressure differences. Stiffness may be varied by providing stiffeners (324,344) of different heights, providing grooves (310), modifying thickness of the shiplaps or combining any of these. The seal plate assembly improves sealing and reduces leakage of cooling air between the adjacent seal plate segments and improves efficiency of the gas turbine engine.

7. 发明申请

WO2014074396A1 EXTERNAL COOLING FLUID INJECTION SYSTEM IN A GAS TURBINE ENGINE 审中-公开
标题翻译：气体涡轮发动机外部冷却流体注入系统
公开(公告)号：WO2014074396A1
公开(公告)日：2014-05-15
申请号：PCT/US2013/067950
申请日：2013-11-01
申请人： SIEMENS AKTIENGESELLSCHAFT , THAM, Kok-Mun , LEE, Ching-Pang , LAURELLO, Vincent P. , CHEHAB, Abdullatif M. , KEMP, David A. , FUSSNER, John A. , YIN, Yan , SULTANIAN, Bijay K. , CAI, Weidong
发明人： THAM, Kok-Mun , LEE, Ching-Pang , LAURELLO, Vincent P. , CHEHAB, Abdullatif M. , KEMP, David A. , FUSSNER, John A. , YIN, Yan , SULTANIAN, Bijay K. , CAI, Weidong
IPC分类号： F01D5/08 , F01D21/00 , F01D25/12 , F01D25/34
CPC分类号： F02C7/12 , F01D5/088 , F01D21/00 , F01D25/12 , F01D25/34 , F05D2270/3032
摘要： A cooling fluid air injection system (40) for use in a gas turbine engine (10) includes at an external cooling fluid source (42), at least one rotor cooling pipe (46), which is used to inject cooling fluid from the source into a rotor chamber (Rc), a piping system (44) that provides fluid communication between the source and the rotor cooling pipe(s), a blower system (50) for conveying the cooling fluid through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system (48). 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（10）的冷却流体空气喷射系统（40）包括在外部冷却流体源（42）处，至少一个转子冷却管（46），用于从源转子室（Rc），在源极和转子冷却管之间提供流体连通的管道系统（44），用于通过管道系统和转子冷却管道输送冷却流体的鼓风机系统（50）（s）进入转子室，以及阀系统（48）。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。

8. 发明申请

WO2014070436A2 TEMPERATURE CONTROL WITHIN A CAVITY OF A TURBINE ENGINE 审中-公开
标题翻译：在涡轮发动机的空气中的温度控制
公开(公告)号：WO2014070436A2
公开(公告)日：2014-05-08
申请号：PCT/US2013/064903
申请日：2013-10-15
申请人： SIEMENS AKTIENGESELLSCHAFT , RODRIGUEZ, Jose L. , LITTLE, David A. , ZHANG, Jiping , CHEHAB, Abdullatif M.
发明人： RODRIGUEZ, Jose L. , LITTLE, David A. , ZHANG, Jiping , CHEHAB, Abdullatif M.
IPC分类号： F01D9/06 , F01D25/16 , F02C7/18
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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