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1. 发明申请

WO2016064393A1 GAS TURBINE ENGINE WITH A TURBINE BLADE TIP CLEARANCE CONTROL SYSTEM 审中-公开
标题翻译：气动涡轮发动机带涡轮叶片间隙控制系统
公开(公告)号：WO2016064393A1
公开(公告)日：2016-04-28
申请号：PCT/US2014/061902
申请日：2014-10-23
申请人： SIEMENS ENERGY, INC.
发明人： ZHANG, Jiping , PEPPERMAN, Barton M.
IPC分类号： F01D11/18
CPC分类号： F01D11/18 , F01D9/042 , F01D11/025 , F01D11/08 , F01D11/16 , F05D2240/11 , F05D2260/36 , F05D2260/38 , F05D2300/50212
摘要： A gas turbine engine (10) having a turbine blade tip clearance control system (12) for increasing the efficiency of the engine (10) by reducing the gap (14) between turbine blade tips (16) and radially outward ring segments (18) is disclosed. The turbine blade tip clearance control system (12) may include one or more clearance control bands (20) positioned radially outward of inner surfaces (22) of ring segments (18) and bearing against at least one outer surface (24) of the ring segments (18) to limit radial movement of the ring segments (18). During operation, the clearance control band (20) limits radial movement of the ring segments (18), and the turbine blade tips (16) do not have a pinch point during start-up transient conditions. In addition, the smallest gap (14) during turbine engine operation may be found at steady state operation of the gas turbine engine (10). Thus, the clearance control system (12) can set the gap (14) between turbine blade tips (16) and ring segments (18) to be zero at steady state operation.
摘要翻译：一种具有涡轮叶片顶端间隙控制系统（12）的燃气涡轮发动机（10），用于通过减小涡轮叶片尖端（16）和径向向外的环形段（18）之间的间隙（14）来提高发动机（10）的效率，被披露。涡轮叶片顶端间隙控制系统（12）可以包括一个或多个位于环段（18）的内表面（22）径向外侧的间隙控制带（20），并且抵靠环的至少一个外表面（24）段（18）以限制环段（18）的径向移动。在操作期间，间隙控制带（20）限制环段（18）的径向移动，并且涡轮叶片尖端（16）在启动瞬态条件下不具有夹点。此外，在涡轮发动机运转中的最小间隙（14）可以在燃气轮机（10）的稳态运行中找到。因此，间隙控制系统（12）可以将稳定状态操作期间涡轮机叶片尖端（16）和环形段（18）之间的间隙（14）设定为零。

2. 发明申请

WO2015047478A3 RADIAL POSITION CONTROL OF CASE SUPPORT STRUCTURE WITH SPLINED CONNECTION 审中-公开
标题翻译：采用分层连接的箱体支撑结构的径向位置控制
公开(公告)号：WO2015047478A3
公开(公告)日：2015-06-11
申请号：PCT/US2014042840
申请日：2014-06-18
申请人： UNITED TECHNOLOGIES CORP
发明人： ROMANOV DMITRIY A , DUGUAY BRIAN
IPC分类号： F02C7/20 , F01D25/28
CPC分类号： F01D11/18 , F01D11/12 , F01D25/246 , F01D25/28 , F02C7/20 , F05D2240/14 , F05D2240/55 , F05D2240/80 , Y02T50/672
摘要： A radial position control assembly for a gas turbine engine includes a case structure. A support structure is operatively supported by the case structure respectively with first and second splines in engagement with one another. The support structure includes an annular recess, and a support ring is received in the recess. The support structure and the support ring having different coefficients of thermal expansion. An axial biasing member urges the first and second splines into engagement with one another.
摘要翻译：用于燃气涡轮发动机的径向位置控制组件包括壳体结构。支撑结构分别通过第一花键和第二花键彼此接合而被壳体结构可操作地支撑。支撑结构包括环形凹槽，并且支撑环容纳在凹槽中。支撑结构和支撑环具有不同的热膨胀系数。轴向偏置构件推动第一花键和第二花键彼此接合。

3. 发明申请

WO2015069338A2 GAS TURBINE ENGINE BLADE OUTER AIR SEAL THERMAL CONTROL SYSTEM 审中-公开
标题翻译：气体涡轮发动机叶片外密封热控制系统
公开(公告)号：WO2015069338A2
公开(公告)日：2015-05-14
申请号：PCT/US2014/049745
申请日：2014-08-05
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： BLANEY, Ken F. , LUTJEN, Paul M.
CPC分类号： F01D11/18 , F01D11/08 , F05D2220/32 , F05D2230/60 , F05D2240/55 , F05D2240/91 , F05D2260/30 , F05D2300/5021 , F16J15/445 , Y02T50/672
摘要： A clearance control system for a gas turbine engine is provided. The system includes an inner axial wall that extends between a forward wall and an aft wall. The system also includes an outer axial wall that extends parallel to the inner axial wall to pivotally receive a full hoop thermal control ring.
摘要翻译：提供了一种用于燃气涡轮发动机的间隙控制系统。该系统包括在前壁和后壁之间延伸的内轴向壁。该系统还包括外轴向壁，其平行于内轴向壁延伸以枢转地接收全环热控制环。

4. 发明申请

WO2014189590A2 HYBRID PASSIVE AND ACTIVE TIP CLEARANCE SYSTEM 审中-公开
标题翻译：混合被动和主动提示清除系统
公开(公告)号：WO2014189590A2
公开(公告)日：2014-11-27
申请号：PCT/US2014/020468
申请日：2014-03-05
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： MCCAFFREY, Michael G. , BORJA, Mark , ROUSE, Brandon T. , FARRIS, John R. , PELLETIER, Brian R. , ALMY, Thomas , GARCIA, Igor S.
IPC分类号： F01D11/14 , F01D11/18 , F01D11/20 , F01D11/22
CPC分类号： F01D11/18 , F01D5/02 , F01D11/22 , F01D11/24 , F01D25/24 , F05D2220/32 , F05D2240/55 , F05D2270/52 , F05D2270/62
摘要： A control ring extends circumferentially about a central axis. A plurality of circumferentially spaced carrier portions have a cavity receiving the control ring. There are circumferential gaps between the carrier portions. A blade outer air seal is mounted on the carrier portions radially inwardly of the control ring. The control ring maintains the carrier portions at a radially outwardly expanded position when heated by an electric heater.
摘要翻译：控制环围绕中心轴线周向延伸。多个周向间隔的载体部分具有容纳控制环的空腔。载体部分之间有圆周间隙。叶片外部空气密封件安装在控制环径向向内的托架部分上。当通过电加热器加热时，控制环将承载部分保持在径向向外扩展的位置。

5. 发明申请

WO2014014598A1 RADIAL POSITION CONTROL OF CASE SUPPORTED STRUCTURE 审中-公开
标题翻译：案例支持结构的径向位置控制
公开(公告)号：WO2014014598A1
公开(公告)日：2014-01-23
申请号：PCT/US2013/046270
申请日：2013-06-18
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： MCCAFFREY, Michael G.
IPC分类号： F02C7/00 , F02C7/20 , F02C7/32
CPC分类号： F01D11/16 , F01D11/18 , Y02T50/672
摘要： A radial position control assembly for a gas turbine engine stage includes a case structure. A supported structure is operatively supported by the case structure. The supported structure includes a hook providing an annular recess. A support ring is received in the recess. The supported structure and the support ring have different coefficients of thermal expansion. A sealing structure is adjacent to the supported structure. The support ring maintains the supported structure relative to the sealing structure at a clearance during thermal transients based upon a circumferential gap between adjacent supported structure and based upon a radial gap between the support ring and the supported structure.
摘要翻译：用于燃气涡轮发动机级的径向位置控制组件包括壳体结构。支撑结构由壳体结构可操作地支撑。支撑结构包括提供环形凹部的钩。一个支撑环被容纳在凹槽中。支撑结构和支撑环具有不同的热膨胀系数。密封结构与支撑结构相邻。基于相邻的支撑结构之间的周向间隙，并且基于支撑环和支撑结构之间的径向间隙，支撑环在热瞬变期间的间隙处相对于密封结构保持支撑结构。

6. 发明申请

WO2013101873A1 HOT GAS EXPANDER INLET CASING ASSEMBLY AND METHOD 审中-公开
标题翻译：热气体扩散器入口组件和方法
公开(公告)号：WO2013101873A1
公开(公告)日：2013-07-04
申请号：PCT/US2012/071716
申请日：2012-12-27
申请人： ELLIOTT COMPANY
发明人： JOSEFCZYK, Ronald, John , SCHUSTER, Carl, John
IPC分类号： F02C7/20
CPC分类号： F02C7/20 , F01D11/18 , F01D25/246 , F05D2220/62 , F05D2230/642 , F05D2240/12 , Y10T29/49323
摘要： A gas turbine device includes an inlet casing and a stator diaphragm provided inside the inlet casing. The stator diaphragm has an integral inner stator shroud and an outer stator shroud and a plurality of stator vanes provided in a circumferential arrangement between the inner stator shroud and the outer stator shroud. A plurality of key slots is provided in a circumferential arrangement on the stator diaphragm and a corresponding plurality of key slots is provided in a circumferential arrangement on the inlet casing. The key slots provided on the stator diaphragm are aligned with the plurality of key slots provided on the inlet casing. A key is inserted into each of the plurality of key slots provided to prevent rotation of the stator diaphragm with respect to the inlet casing. The stator diaphragm is secured in an axial direction by a stator shear ring.
摘要翻译：燃气轮机装置包括入口壳体和设置在入口壳体内部的定子膜片。定子膜片具有整体的内部定子护罩和外部定子护罩以及设置在内部定子护罩和外部定子护罩之间的周向布置的多个定子叶片。多个键槽设置在定子隔膜上的周向布置中，并且相应的多个键槽以周向布置设置在入口壳体上。设置在定子膜片上的键槽与设置在入口壳体上的多个键槽对准。将多个键槽中的每一个插入钥匙以防止定子隔膜相对于入口壳体旋转。定子隔膜通过定子剪切环沿轴向固定。

7. 发明申请

WO2012025358A1 A TURBOMACHINE CASING ASSEMBLY 审中-公开
标题翻译：涡轮机壳组件
公开(公告)号：WO2012025358A1
公开(公告)日：2012-03-01
申请号：PCT/EP2011/063429
申请日：2011-08-04
申请人： ROLLS-ROYCE PLC , WEBSTER, John Richard
发明人： WEBSTER, John Richard
IPC分类号： F01D11/12 , F01D11/18 , F01D25/06
CPC分类号： F01D25/24 , F01D11/12 , F01D11/18 , F01D25/06 , F04D29/324 , F04D29/666 , F04D29/668 , F05D2260/96
摘要： A turbomachine casing assembly comprising a casing (30) adapted to encase an aerofoil structure (26), the aerofoil structure having a tip (48), a leading edge (44) and a trailing edge (46), the casing substantially surrounding the tip of the aerofoil structure, wherein the casing has a set-back portion (54) extending from a position in the region of the leading edge (44) or the trailing edge (46) of the aerofoil structure (26) part way towards a position in the region of the respective other edge (46; 44) and set back from the remainder of the casing away from the aerofoil structure, such that the set-back portion permits a flow over a corresponding portion of the tip of the aerofoil structure.
摘要翻译：一种涡轮机壳体组件，包括适于包围机翼结构（26）的壳体（30），所述机翼结构具有尖端（48），前缘（44）和后缘（46），所述壳体基本上围绕所述尖端其中所述壳体具有从所述机翼结构（26）的前缘（44）或所述后缘（46）的区域中的位置部分地延伸到所述机翼部分（54）的位置在相应的另一边缘（46; 44）的区域中，并且从壳体的其余部分离开机翼结构退回，使得止回部分允许流过机翼结构的尖端的相应部分。

8. 发明申请

WO2005024186A1 EXPANDING SEALING STRIPS FOR STEAM TURBINES 审中-公开
标题翻译：扩大蒸汽轮胎密封条
公开(公告)号：WO2005024186A1
公开(公告)日：2005-03-17
申请号：PCT/US2004/028773
申请日：2004-09-03
申请人： GENERAL ELECTRIC COMPANY , PARRY, William, Thomas
发明人： PARRY, William, Thomas
IPC分类号： F01D11/02
CPC分类号： F01D11/025 , F01D11/18 , F05D2220/31 , F05D2240/56 , F05D2300/50212
摘要： A turbine (10) includes, in an exemplary embodiment, an outer housing (22), a turbine shaft (12) rotatably supported in the outer housing, and a plurality of turbine stages located along the turbine shaft. Each turbine stage includes a diaphragm (20) attached to the casing, a rotor (46) having a plurality of buckets (16) and a bucket cover (52) fixedly attached to the turbine shaft, and a packing ring (54) mounted in a first circumferentially extending groove (56) in said diaphragm. The packing ring includes a seal shroud (58) and a sealing means (60) and is positioned adjacent the turbine shaft. The seal shroud is fabricated from a first material having a first coefficient of expansion, and the is diaphragm fabricated from a second material having a second coefficient of expansion. The first and second materials are selected so that at a first temperature a gap between the turbine shaft and the diaphragm is larger than at a second higher temperature.
摘要翻译：涡轮（10）在一个示例性实施例中包括外壳（22），可旋转地支撑在外壳中的涡轮轴（12）和沿涡轮轴定位的多个涡轮级。每个涡轮级包括附接到壳体的隔膜（20），具有多个铲斗（16）的转子（46）和固定地连接到涡轮轴的铲斗盖（52），以及安装在所述隔膜中的第一周向延伸槽（56）。密封环包括密封罩（58）和密封装置（60）并且邻近涡轮机轴定位。密封罩由具有第一膨胀系数的第一材料制成，并且是由具有第二膨胀系数的第二材料制成的隔膜。选择第一和第二材料使得在第一温度下，涡轮轴和隔膜之间的间隙大于在第二较高温度下的间隙。

9. 发明申请

WO2017058745A1 GAS TURBINE COMPRESSOR WITH ADAPTIVE BLADE TIP SEAL ASSEMBLY 审中-公开
标题翻译：具有自适应叶片密封组件的气体涡轮压缩机
公开(公告)号：WO2017058745A1
公开(公告)日：2017-04-06
申请号：PCT/US2016/053877
申请日：2016-09-27
申请人： SIEMENS AKTIENGESELLSCHAFT , SIEMENS ENERGY, INC.
发明人： ZHANG, Jiping , PEPPERMAN, Barton M.
IPC分类号： F01D11/18 , F01D25/24
CPC分类号： F04D29/164 , F01D11/18 , F01D25/246 , F04D29/526 , F04D29/541 , F05B2220/302 , F05B2260/502 , F05B2280/1071 , F05B2280/50032 , F05D2240/11 , F05D2260/38 , F05D2300/171 , F05D2300/5024
摘要： A high-efficiency compressor section (10) for a gas turbine engine is disciosed. The compressor section includes a vane carrier (12) adapted to hold ring segment assemblies (16) that provide optimized blade tip gaps (28,29) during a variety of operating conditions. The ring segment assemblies include backing elements (30) and tip- facing elements (32) urged into a preferred orientation by biasing elements (40) that maintain contact along engagement surfaces (44,46). The backing and tip-facing elements have thermal properties sufficiently different to allow relative growth that strategically forms an interface gap (42,43) therebetween, resulting in blade tip gaps that are dynamically adjusted during operation.
摘要翻译：描述了一种用于燃气涡轮发动机的高效率压缩机部分（10）。压缩机部分包括适于在各种操作条件下保持提供优化的叶片尖端间隙（28,29）的环形段组件（16）的叶片承载件（12）。环段组件包括通过沿着接合表面（44,46）保持接触的偏压元件（40）而推动成优选取向的背衬元件（30）和朝向顶端的元件（32）。背衬和顶端元件具有足够不同的热性能，以允许在其间策略性地形成界面间隙（42,43）的相对生长，导致在操作期间动态调节的叶片尖端间隙。

10. 发明申请

WO2015130355A3 BLADE TIP CLEARANCE SYSTEMS 审中-公开
标题翻译：刀尖间隙系统
公开(公告)号：WO2015130355A3
公开(公告)日：2015-10-22
申请号：PCT/US2014066304
申请日：2014-11-19
申请人： UNITED TECHNOLOGIES CORP
发明人： DAVIS TIMOTHY M , PAULINO JOSE R , DUGUAY BRIAN
IPC分类号： F01D11/08 , F01D11/18
CPC分类号： F01D11/18 , F01D5/02 , F01D5/12 , F01D11/24 , F05D2220/32 , F05D2260/22141 , F05D2300/5021 , F05D2300/50212 , Y02T50/676
摘要： A blade tip clearance system includes first and second control rings. The first control ring has a first coefficient of thermal expansion (CTE) and a first thermal response rate. The second control ring is located radially outward of and operatively connected to the first control ring and has a second CTE that is different from the first CTE and a second thermal response rate that is different from the first thermal response rate. Thermal expansion and contraction of the first and the second control rings controls a radial position of the blade tip clearance system relative to a rotating blade component.
摘要翻译：叶片顶端间隙系统包括第一和第二控制环。第一控制环具有第一热膨胀系数（CTE）和第一热响应速率。第二控制环位于第一控制环的径向外部并且可操作地连接到第一控制环，并且具有不同于第一CTE的第二CTE和与第一热响应速率不同的第二热响应速率。第一和第二控制环的热膨胀和收缩控制叶片顶端间隙系统相对于旋转叶片部件的径向位置。

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