公开(公告)号：EP2554797A2

公开(公告)日：2013-02-06

申请号：EP12177897.1

申请日：2012-07-25

申请人： General Electric Company

发明人： Adaickalasamy, James ,  Sundaram, Hariharan

IPC分类号： F01D11/18

CPC分类号： F01D11/18 ,  F05D2300/505

摘要： A system for passively controlling clearance in a turbine engine (100) comprises a static assembly (160) arranged circumferentially about an engine rotor assembly (170) and defining a gap (150) between a tip end (112) of the rotor assembly (170) and an adjacent inner surface (132) of the static assembly (160). The static assembly includes a gap control member (130) that defines the inner surface (132), is exposed to the engine working fluid, and comprises a shape memory material selected and preconditioned to deform in a preselected manner in response to a temperature of the engine working fluid. Alternatively, airfoil blades of the rotor assembly include the gap control member (230). A method for passively controlling clearance in a turbine engine (100) comprises assembling the engine so as to define an initial set of build clearances, operating the engine to observe running clearances, configuring a gap control member (130) comprising a shape memory material and re-assembling the engine with the gap control member (130).

摘要翻译： 一种用于在涡轮发动机（100）被动地控制间隙系统包括周向布置即将发动机转子组件（170）的静态组件（160）和限定在转子组件的前端（112）之间的间隙（150）（170 ）和（毗邻内表面（132）的静态组件160）的。 静态组件包括（130）做了间隙控制构件限定所述内表面（132）被暴露于发动机的工作流体，以及包括形状记忆材料中选择和预处理在预先选定的方式变形以响应的一个温度 发动机的工作流体。 可替代地，转子的翼型叶片组件包括间隙控制构件（230）。 一种用于在涡轮发动机（100）被动地控制间隙的方法包括组装发动机，使得在初始设定构造间隙的定义，操作所述引擎来观察的运行间隙，配置包括形状记忆材料的间隙控制构件（130）和 重新组装具有间隙控制构件（130）的发动机。

公开(公告)号：EP2520678B1

公开(公告)日：2019-03-20

申请号：EP12166469.2

申请日：2012-05-02

申请人： General Electric Company

发明人： Feng, Ganjiang ,  Schaeffer, Jon Conrad ,  Balsone, Stephen Joseph ,  Sundaram, Hariharan ,  Amancherla, Sundar ,  Mukira, Gitahi Charles

IPC分类号： C22C19/05

公开(公告)号：EP2549065A1

公开(公告)日：2013-01-23

申请号：EP12176533.3

申请日：2012-07-16

申请人： General Electric Company

发明人： Nanakuttan, Biju ,  Adoor, Rakesh ,  Sundaram, Hariharan ,  Adalckalasamy, James ,  Punna, Prasad

IPC分类号： F01D11/22

CPC分类号： F01D11/22 ,  F05B2280/5006 ,  F05D2300/505 ,  Y10S277/931 ,  Y10S277/932

摘要： A system for operating a turbine includes a rotating component (18) and a non-rotating component (16) separated from the rotating component (18) by a clearance (30). A first actuator (42) is connected to the non-rotating component (16), and the first actuator (42) comprises a shape-memory alloy (44). A method for operating a turbine includes sensing a parameter reflective of a clearance (30) between a non-rotating component (16) and a rotating component (18) and generating a parameter signal reflective of the clearance (30). The method further includes generating a control signal to at least one actuator (42) based on the parameter signal and moving at least a portion of the non-rotating component (16) relative to the rotating component (18) to change the clearance (30).

摘要翻译： 用于操作涡轮机的系统包括旋转部件（18）和与旋转部件（18）间隔开间隙（30）分离的非旋转部件（16）。 第一致动器（42）连接到非旋转部件（16），并且第一致动器（42）包括形状记忆合金（44）。 用于操作涡轮机的方法包括感测反映在非旋转部件（16）和旋转部件（18）之间的间隙（30）的参数并产生反映间隙（30）的参数信号。 该方法还包括基于参数信号向至少一个致动器（42）生成控制信号，并且相对于旋转部件（18）移动至少一部分非旋转部件（16）以改变间隙（30） ）。

公开(公告)号：EP2520678A3

公开(公告)日：2016-12-14

申请号：EP12166469.2

申请日：2012-05-02

申请人： General Electric Company

发明人： Feng, Ganjiang ,  Schaeffer, Jon Conrad ,  Balsone, Stephen Joseph ,  Sundaram, Hariharan ,  Amancherla, Sundar ,  Mukira, Gitahi Charles

IPC分类号： C22C19/05

CPC分类号： C22C19/056 ,  C22C19/05 ,  F01D5/28 ,  F05D2300/607

摘要： The invention is a class of nickel-base alloys for gas turbine applications, comprising, by weight, about 13.7 to about 14.3 percent chromium, about 5.0 to about 10.0 percent cobalt, about 3.5 to about 5.2 percent tungsten, about 2.8 to about 5.2 percent titanium, about 2.8 to about 4.6 percent aluminum, about 0.0 to about 3.5 percent tantalum, about 1.0 to about 1.7 percent molybdenum, about 0.08 to about 0.13 percent carbon, about 0.005 to about 0.02 percent boron, about 0.0 to about 1.5 percent niobium, about 0.0 to about 2.5 percent hafnium, about 0.0 to about 0.04 percent zirconium, and the balance substantially nickel. The nickel-base alloys may be provided in the form of useful articles of manufacture, and which possess a unique combination of mechanical properties, microstructural stability, resistance to localized pitting and hot corrosion in high temperature corrosive environments, and high yields during the initial forming process as well as post-forming manufacturing and repair processes.

公开(公告)号：EP2623715A3

公开(公告)日：2014-06-11

申请号：EP12198399.3

申请日：2012-12-20

申请人： General Electric Company

发明人： Keny, Mayur Abhay ,  Subbareddyar, Thangaraj ,  Sundaram, Hariharan

IPC分类号： F01D5/14 ,  F01D5/28

CPC分类号： F01D5/148 ,  F01D5/28 ,  F05D2300/505

摘要： An exhaust strut (20) is provided and includes a body (30) having an airfoil-shaped cross-section (31) defining a lead edge portion (32) and a trailing edge portion (33) opposite the lead edge portion (32), the lead edge portion (32) and the trailing edge portion (33) being connected by a pressure side (34) and a suction side (35) opposite the pressure side (34), at least the lead edge portion (32) and respective sections of the pressure side (34) and the suction side (35) proximate to the lead edge portion (32) being formed of shape memory alloy, and a temperature control system (40) operably disposed at the lead edge portion (32) and the respective sections of the pressure side (34) and the suction side (35) proximate to the lead edge portion (32) to modify a temperature of the shape memory alloy.

公开(公告)号：EP2631452A2

公开(公告)日：2013-08-28

申请号：EP13155681.3

申请日：2013-02-18

申请人： General Electric Company

发明人： Ganti, Sanyaswara Rao ,  Keny, Mayur Abhay ,  Ramesh, Anantha ,  Sundaram, Hariharan ,  Nandagopal, Pugalenthi

IPC分类号： F02C7/224

CPC分类号： F02C7/224 ,  Y02T10/166

摘要： A gas turbine inlet system (20) includes a first passage (22) that delivers inlet air to a compressor (12), a second passage (28) that delivers fuel to a combustor (14), and a heat pump (26) that transfers heat from the inlet air to the fuel by consuming electric power. The heat transfer causes the turbine inlet air temperature to drop and fuel temperature to increase with favorable effects on both turbine output and heat rate.

摘要翻译： 燃气轮机入口系统（20）包括将入口空气输送到压缩机（12）的第一通道（22），将燃料输送到燃烧器（14）的第二通道（28）和热泵（26） 通过消耗电力将热量从入口空气传递到燃料。 传热会导致涡轮机入口空气温度下降，燃料温度升高，同时对涡轮机输出功率和热量均有好的影响。

公开(公告)号：EP2623715A2

公开(公告)日：2013-08-07

申请号：EP12198399.3

申请日：2012-12-20

申请人： General Electric Company

发明人： Keny, Mayur Abhay ,  Subbareddyar, Thangaraj ,  Sundaram, Hariharan

IPC分类号： F01D5/14 ,  F01D5/28

CPC分类号： F01D5/148 ,  F01D5/28 ,  F05D2300/505

摘要： An exhaust strut (20) is provided and includes a body (30) having an airfoil-shaped cross-section (31) defining a lead edge portion (32) and a trailing edge portion (33) opposite the lead edge portion (32), the lead edge portion (32) and the trailing edge portion (33) being connected by a pressure side (34) and a suction side (35) opposite the pressure side (34), at least the lead edge portion (32) and respective sections of the pressure side (34) and the suction side (35) proximate to the lead edge portion (32) being formed of shape memory alloy, and a temperature control system (40) operably disposed at the lead edge portion (32) and the respective sections of the pressure side (34) and the suction side (35) proximate to the lead edge portion (32) to modify a temperature of the shape memory alloy.

摘要翻译： 提供排气支柱（20），并且包括具有限定引线边缘部分（32）的机翼形横截面（31）和与引线边缘部分（32）相对的后缘部分（33）的主体（30） 所述前缘部分（32）和所述后缘部分（33）通过压力侧（34）和与所述压力侧（34）相对的吸力侧（35）连接，至少所述引导边缘部分（32）和 靠近引线边缘部分（32）的压力侧（34）和吸力侧（35）的各个部分由形状记忆合金形成，以及温度控制系统（40），其可操作地设置在引导边缘部分（32）处， 以及靠近引线边缘部分（32）的压力侧（34）和吸力侧（35）的各个部分，以改变形状记忆合金的温度。

公开(公告)号：EP2520678A2

公开(公告)日：2012-11-07

申请号：EP12166469.2

申请日：2012-05-02

申请人： General Electric Company

发明人： Feng, Ganjiang ,  Schaeffer, Jon Conrad ,  Balsone, Stephen Joseph ,  Sundaram, Hariharan ,  Amancherla, Sundar ,  Mukira, Gitahi Charles

IPC分类号： C22C19/05

CPC分类号： C22C19/056 ,  C22C19/05 ,  F01D5/28 ,  F05D2300/607

摘要： The invention is a class of nickel-base alloys for gas turbine applications, comprising, by weight, about 13.7 to about 14.3 percent chromium, about 5.0 to about 10.0 percent cobalt, about 3.5 to about 5.2 percent tungsten, about 2.8 to about 5.2 percent titanium, about 2.8 to about 4.6 percent aluminum, about 0.0 to about 3.5 percent tantalum, about 1.0 to about 1.7 percent molybdenum, about 0.08 to about 0.13 percent carbon, about 0.005 to about 0.02 percent boron, about 0.0 to about 1.5 percent niobium, about 0.0 to about 2.5 percent hafnium, about 0.0 to about 0.04 percent zirconium, and the balance substantially nickel. The nickel-base alloys may be provided in the form of useful articles of manufacture, and which possess a unique combination of mechanical properties, microstructural stability, resistance to localized pitting and hot corrosion in high temperature corrosive environments, and high yields during the initial forming process as well as post-forming manufacturing and repair processes.

摘要翻译： 本发明是一类用于燃气轮机应用的镍基合金，其重量包括约13.7至约14.3％的铬，约5.0至约10.0％的钴，约3.5至约5.2％的钨，约2.8至约5.2％ 钛，约2.8至约4.6％的铝，约0.0至约3.5％的钽，约1.0至约1.7％的钼，约0.08至约0.13％的碳，约0.005至约0.02％的硼，约0.0至约1.5％的铌， 约0.0至约2.5％的铪，约0.0至约0.04％的锆，余量基本上为镍。 镍基合金可以以有用的制品形式提供，并且具有机械性能，微结构稳定性，耐高温腐蚀环境中的局部点蚀和热腐蚀的独特组合，以及在初始成型期间的高产率 过程以及后成型制造和维修过程。