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61. 发明公开

EP3090139A4 BLADE TIP CLEARANCE SYSTEMS 有权转让
标题翻译： SCHAUFELSPITZENSPALTSYSTEME
公开(公告)号：EP3090139A4
公开(公告)日：2017-09-06
申请号：EP14883657
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

62. 发明公开

EP3209865A1 GAS TURBINE ENGINE WITH A TURBINE BLADE TIP CLEARANCE CONTROL SYSTEM 有权
标题翻译：燃气轮机发动机与涡轮叶片头间隙控制系统
公开(公告)号：EP3209865A1
公开(公告)日：2017-08-30
申请号：EP14795740.1
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：一种燃气涡轮发动机（10），具有通过减小涡轮叶片尖端（16）和径向外环段（18）之间的间隙（14）来增加发动机（10）的效率的涡轮叶片尖端间隙控制系统（12）被披露。涡轮机叶片顶端间隙控制系统（12）可以包括一个或多个间隙控制带（20），所述一个或多个间隙控制带（20）定位在环形段（18）的内表面（22）的径向外侧并抵靠环的至少一个外表面（24）（18），以限制环形部分（18）的径向运动。在操作期间，间隙控制带（20）限制环段（18）的径向运动，并且涡轮叶片尖端（16）在启动瞬态条件期间不具有夹点。另外，在涡轮发动机运行期间的最小间隙（14）可以在燃气涡轮发动机（10）的稳态运行中找到。因此，间隙控制系统（12）可以在稳态运行时将涡轮机叶片尖端（16）和环形部分（18）之间的间隙（14）设定为零。

63. 发明公开

EP3187694A1 PASSIVE FLOW MODULATION DEVICE AND GAS TURBINE COOLING SYSTEM COMPRISING SUCH A DEVICE 有权
标题翻译：被动流量调节装置和包括这种装置的燃气轮机冷却系统
公开(公告)号：EP3187694A1
公开(公告)日：2017-07-05
申请号：EP16205153.6
申请日：2016-12-19
申请人： General Electric Company
发明人： MIRANDA, Carlos Miguel , WIDENER, Stanley Kevin
IPC分类号： F01D11/18 , F01D17/08 , F01D17/14 , F01D25/12 , F16K31/00 , G05D23/02
CPC分类号： F01D17/145 , F01D5/02 , F01D9/00 , F01D17/085 , F01D17/141 , F01D25/12 , F05D2220/30 , F05D2260/2212 , F05D2300/5021 , F16K31/002 , G05D23/02 , Y02T50/675
摘要： A passive flow modulation device (36) according to an embodiment includes: a temperature sensitive element (54) disposed within a first area (30); a piston (60) coupled to the temperature sensitive element (54), the piston (60) extending through a wall to a second area (44), wherein the first area (30) is at a higher temperature than the second area (44); and a valve arrangement (42) disposed in the second area (44) and actuated by a distal end portion of the piston (60), the valve arrangement (42) tangentially injecting a supply of cooling air (32) through an angled orifice (34) from the second area (44) into the first area (30) in response an increase in temperature in the first area (44). A passive flow modulation device (38) according to another embodiment comprises: a temperature sensitive element (78); a piston (86) coupled to the temperature sensitive element (78), the piston (86) including a head section (90), wherein the temperature sensitive element (78) and the piston (86) are disposed in a first area (30); and
an orifice (34), extending from a second area into the first area (30), for supplying a flow of cooling air (32) from the second area to the first area (30), wherein the first area (30) is at a higher temperature than the second area; wherein the temperature sensitive element (78) enlarges or contracts to selectively position the head (90) of the piston (86) over a portion of the aperture (34) to control the flow of cooling air (32) from the second area into the first area (30). A corresponding turbine cooling system comprising a passive flow modulation device is also provided.
摘要翻译：根据一个实施例的无源流动调节装置（36）包括：设置在第一区域（30）内的温度敏感元件（54）与温度敏感元件（54）连接的活塞（60），活塞（60）穿过壁延伸到第二区域（44），其中第一区域（30）的温度高于第二区域（44））; 和布置在所述第二区域（44）中并由所述活塞（60）的远端部分致动的阀装置（42），所述阀装置（42）切向地注入冷却空气（32）供应通过成角度的孔口响应于第一区域（44）中的温度升高，从第二区域（44）进入第一区域（30）。根据另一实施例的无源流量调节装置（38）包括：温度敏感元件（78）; （78）连接的活塞（86），所述活塞（86）包括头部（90），其中所述温度敏感元件（78）和所述活塞（86）设置在第一区域）; 和从第二区域延伸到所述第一区域（30）中的用于从所述第二区域向所述第一区域（30）供应冷却空气流（32）的孔（34），其中所述第一区域（30）是在比第二区域更高的温度下; 其中所述温度敏感元件（78）扩大或收缩以选择性地将所述活塞（86）的所述头部（90）定位在所述孔（34）的一部分上方以控制冷却空气（32）从所述第二区域流入所述第二区域第一区域（30）。还提供了包括无源流量调节装置的对应的涡轮机冷却系统。

64. 发明公开

EP3121388A3 CONTROL RINGS FOR USE IN A GAS TURBINE 有权转让
标题翻译：用于燃气轮机的控制环
公开(公告)号：EP3121388A3
公开(公告)日：2017-04-19
申请号：EP16157952.9
申请日：2016-02-29
申请人： United Technologies Corporation
发明人： BORJA, Mark
IPC分类号： F01D11/18
CPC分类号： F01D11/18 , F05D2240/11 , F05D2300/5023 , F05D2300/5024
摘要： The present disclosure concerns three different types of control rings with adapted thermal response for gas turbines. A first control ring (101) for use in a gas turbine engine (20) includes a control ring segment (107) defining a centerline axis. The control ring segment includes an inner diameter surface (111) and an outer diameter surface (113). A thermally isolating contact (115) is operatively connected to at least one of the inner diameter surface and the outer diameter surface. The thermally isolating contact has lower thermal conductivity than the control ring. Furthermore, another control ring for use in a gas turbine engine comprises a control ring segment defining a centerline axis, wherein the control ring segment includes an inner diameter surface and an outer diameter surface, and an internal cavity defined between the inner and outer diameter surfaces, wherein the internal cavity is configured to contain a material having a higher heat capacitance than the control ring. An even further control ring for use in a gas turbine engine comprises a plurality of radially stacked rings, wherein each radially stacked ring includes a plurality of arcuate segments.
摘要翻译：本公开涉及三种不同类型的对燃气轮机具有适应的热响应的控制环。用于燃气涡轮发动机（20）的第一控制环（101）包括限定中心线轴线的控制环段（107）。控制环段包括内径表面（111）和外径表面（113）。隔热接触件（115）可操作地连接到内径表面和外径表面中的至少一个。隔热接触件的热导率低于控制环。此外，用于燃气涡轮发动机的另一控制环包括限定中心线轴线的控制环段，其中控制环段包括内径表面和外径表面以及限定在内径表面和外径表面之间的内腔其中，所述内腔构造成容纳具有比所述控制环更高的热容量的材料。用于燃气涡轮发动机的更进一步的控制环包括多个径向堆叠的环，其中每个径向堆叠的环包括多个弧形段。

65. 发明公开

EP3022398A4 TURBINE CLEARANCE CONTROL UTILIZING LOW ALPHA MATERIAL 审中-公开
标题翻译： TURBINENSPIELRAUMSTEUERUNG MIT NIEDRIGEM ALPHAMATERIALANTEIL
公开(公告)号：EP3022398A4
公开(公告)日：2017-03-01
申请号：EP14825893
申请日：2014-07-02
申请人： UNITED TECHNOLOGIES CORP
发明人： SUCIU GABRIEL L , ALVANOS IOANNIS
IPC分类号： F01D11/18 , F01D5/28 , F01D5/34 , F01D11/12
CPC分类号： F01D5/28 , F01D5/34 , F01D11/122 , F01D11/18 , F02C3/04 , F05D2300/174 , Y02T50/671

66. 发明公开

EP3090139A2 BLADE TIP CLEARANCE SYSTEMS 有权转让
标题翻译： SCOOP TOP分体式系统
公开(公告)号：EP3090139A2
公开(公告)日：2016-11-09
申请号：EP14883657.0
申请日：2014-11-19
申请人： United Technologies Corporation
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.

67. 发明公开

EP2518274A3 Blade clearance control using high-CTE and low-CTE ring members 有权转让
标题翻译：使用高CTE和低CTE环成员叶片桨距控制
公开(公告)号：EP2518274A3
公开(公告)日：2016-11-09
申请号：EP12165804.1
申请日：2012-04-26
申请人： United Technologies Corporation
发明人： McCaffrey, Michael G. , Hudson, Eric A.
IPC分类号： F01D11/18
摘要： An engine has a blade stage (10) and a circumferential array of blade outer air seal segments (66). A support ring (70) carries the blade outer air seal segments (66). The support ring (70) has a low-CTE member (72) and a high-CTE member (90) intervening between the blade outer air seal segments (66) and the low-CTE member (72).

68. 发明公开

EP2852734A4 PASSIVE THERMOSTATIC VALVE 有权转让
标题翻译：骗取温哥华
公开(公告)号：EP2852734A4
公开(公告)日：2016-04-27
申请号：EP13793384
申请日：2013-05-03
申请人： UNITED TECHNOLOGIES CORP
发明人： THORTON LANE , SLAVENS THOMAS N
IPC分类号： F01D5/18 , F01D11/18 , F01D17/00 , F01D17/08 , F01D25/12 , F02C7/14 , F02C9/00 , F02K3/00
CPC分类号： F01D5/187 , F01D5/18 , F01D5/188 , F01D11/18 , F01D17/00 , F01D17/085 , F02C6/08 , F02C7/185 , F05D2270/303 , F05D2270/3062 , F05D2270/42 , G05D23/1921
摘要： An airfoil includes an airfoil body having an internal cavity. A thermostatic valve is located at least partially within the internal cavity. The thermostatic valve is configured to passively control fluid flow into the internal cavity in response to a temperature within the internal cavity.
摘要翻译：翼型件包括具有内部空腔的翼型件本体。恒温阀至少部分位于内腔内。恒温阀被配置为响应于内腔内的温度而被动地控制流入内腔的流体。

69. 发明公开

EP3008295A1 CLEARANCE CONTROL RING ASSEMBLY 有权
标题翻译：远程控制系统RING
公开(公告)号：EP3008295A1
公开(公告)日：2016-04-20
申请号：EP14737076.1
申请日：2014-06-04
申请人： General Electric Company
发明人： MONDAL, Bhaskar, Nanda , RAHAIM, John, Joseph , MONIZ, Thomas , ROSS, Steven, A. , KIRK, Joel , HUNTER, Scott , FUSINATO, Daniel
IPC分类号： F01D11/02 , F01D11/18 , F01D25/00
CPC分类号： F01D11/18 , F01D11/025 , F01D25/005 , F05D2240/11 , F05D2240/55 , F05D2260/30 , F05D2300/5021 , F05D2300/6033 , Y02T50/672
摘要： A passive clearance control limits thermal expansion between stator components relative to rotor components. A control ring 40 controls clearance in a passive manner and is located on or adjacent to stationary components which thermally expand during engine operation. The control ring is formed of material having low coefficient of thermal expansion such as CMCs (Ceramic Matrix Composites) and therefore limits, inhibits or restrains expansion of the adjacent stator components 32 as temperatures increase. Limiting expansion of the stator component reduces rotor/stator clearances and limits parasitic leakage of fluid along the flowpath through the engine core.

70. 发明公开

EP2609297A1 METHOD OF DAMPING AEROFOIL STRUCTURE VIBRATIONS AND CORRESPONDING AEROFOIL STRUCTURE 审中-公开
标题翻译：方法阻尼VIBRATIONS WINGS结构及相关WINGS结构
公开(公告)号：EP2609297A1
公开(公告)日：2013-07-03
申请号：EP11743504.0
申请日：2011-08-04
申请人： Rolls-Royce PLC
发明人： WEBSTER, John Richard
IPC分类号： F01D25/06 , F01D5/26 , F01D11/18 , F02K3/06
CPC分类号： F04D29/66 , F01D5/145 , F01D5/26 , F01D11/18 , F01D25/06 , F02K3/06 , F04D29/60 , F05D2250/71 , F05D2260/96 , Y10T29/4932
摘要： A method of damping aerofoil structure vibrations, the method comprising: providing an aerofoil structure (26) having a root portion (36) and an aerofoil portion (38), wherein the aerofoil portion has a tip (48) remote from the root portion, the tip of the aerofoil structure being substantially surrounded by a casing (30) with a clearance gap (60) between the tip and the casing; disposing the aerofoil structure (26) relative to the casing (30) such that an oscillation of the aerofoil structure from an unperturbed position in a first direction reduces the clearance gap (60) and that an oscillation from the unperturbed position in a second direction increases the clearance gap; further disposing the aerofoil structure (26) such that the frequency of the clearance gap variation is equivalent to the frequency of the aerofoil structure vibration; and permitting a flow through the clearance gap (60), the flow tending to damp the aerofoil structure vibrations.

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