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91. 发明公开

EP1933007A2 Gas turbine guide vanes with tandem airfoils and fuel injection and method of use 审中-公开
标题翻译： GasturbinenführungsschaufelnmitTandemflächenund Brennstoffeinspritzung sowie Verwendungsverfahrendafür
公开(公告)号：EP1933007A2
公开(公告)日：2008-06-18
申请号：EP07121734.3
申请日：2007-11-28
申请人： General Electric Company
发明人： Bunker, Ronald Scott , Evulet, Andrei Tristan
IPC分类号： F01D5/14 , F01D9/04 , F02K3/08
CPC分类号： F01D5/146 , F01D9/041 , F01D9/065 , F02K3/08 , F23C2900/07001 , F23R3/20 , Y02T50/673
摘要： Gas turbine engine guide vanes (12) that include a first flange (26) connected with a casing (18) of a gas turbine engine, a second flange (28) connected with the casing, a first airfoil (22) disposed between the first and second flanges and connected thereto, and a second airfoil (24) disposed between the first and second flanges and connected thereto so as to form a gap (34) extending radially between a first trailing portion of the first airfoil and a second leading portion of the second airfoil, the hollow portion being in flow communication with the gap so as to allow a gaseous fuel (26) to flow from the hollow portion through the gap and into a fluid flowing over the guide vane. Gas turbines that use the guide vanes and methods for injecting a gaseous fuel for combustion in a gas turbine engine are also disclosed.
摘要翻译：包括与燃气涡轮发动机的壳体（18）连接的第一凸缘（26）的燃气涡轮发动机导向叶片（12），与壳体连接的第二凸缘（28），设置在第一和第二凸缘并连接到其上，第二翼型件（24）设置在第一和第二凸缘之间并与之连接，以形成在第一翼型件的第一尾部之间径向延伸的间隙（34）所述第二翼型件，所述中空部分与所述间隙流动连通，以允许气体燃料（26）从所述中空部分流过所述间隙并流入流过所述导向叶片的流体。还公开了使用引导叶片的燃气轮机和用于在燃气涡轮发动机中燃烧气体燃料的方法。

92. 发明授权

EP1211385B1 Making cooling channels in turbine components 有权
标题翻译：在涡轮机部件的冷却通路的安装
公开(公告)号：EP1211385B1
公开(公告)日：2007-08-08
申请号：EP01310021.9
申请日：2001-11-29
申请人： GENERAL ELECTRIC COMPANY
发明人： Bunker, Ronald Scott
IPC分类号： F01D5/18 , B23P15/02
CPC分类号： F01D9/02 , B23P2700/06 , F05D2230/10 , F05D2230/21 , F05D2240/81 , Y10T29/49318 , Y10T29/49336 , Y10T29/49341 , Y10T29/49716

93. 发明公开

EP1416558A3 Method and apparatus for fuel cell thermal management 审中-公开
标题翻译：一种用于燃料电池的热管理的方法和装置
公开(公告)号：EP1416558A3
公开(公告)日：2006-12-27
申请号：EP03254891.9
申请日：2003-08-06
申请人： GENERAL ELECTRIC COMPANY
发明人： Bunker, Ronald Scott
IPC分类号： H01M8/02
CPC分类号： H01M8/04067 , H01M8/0267 , H01M8/04014 , H01M8/04029 , H01M8/04089 , H01M8/2465
摘要： A fuel cell assembly (100) comprising: a first fuel cell unit (110) adapted for generating electrical power from a fuel flow and an oxidant flow; and a fluid heat exchanger (120) adapted for transferring heat between the fuel cell unit (110) and a heat exchanging fluid flow.

94. 发明公开

EP1734228A2 Turbine bucket tip cap 审中-公开
标题翻译： Turbinenlaufschaufelspitze
公开(公告)号：EP1734228A2
公开(公告)日：2006-12-20
申请号：EP06252966.4
申请日：2006-06-08
申请人： GENERAL ELECTRIC COMPANY
发明人： Bunker, Ronald Scott , Itzel, Gary Michael
IPC分类号： F01D5/20
CPC分类号： F01D5/20 , F05C2201/0463 , F05C2201/0466 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141
摘要： A tip cap piece for use in a turbine bucket is [provided which may include a cold side and a number of pins positioned on the cold side.
摘要翻译：用于涡轮机叶片的顶盖部件[被设置成可以包括冷侧和位于冷侧的多个销。

95. 发明公开

EP1681438A2 Turbine stage with scalloped surface platform 有权转让
标题翻译： Turbinenstufe mitbogenförmigerPlattformoberfläche
公开(公告)号：EP1681438A2
公开(公告)日：2006-07-19
申请号：EP05257850.7
申请日：2005-12-20
申请人： The General Electric Company
发明人： Tam, Anna , Lee, Ching-Pang , Kirtley, Kevin Richard , Bunker, Ronald Scott , Lamson, Scott Henry , Carson, Scott Michael
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , F05D2240/80 , F05D2250/70 , F05D2250/711 , F05D2250/712 , Y02T50/673
摘要： A turbine stage includes a row of airfoils (14) joined to corresponding platforms (16) to define flow passages (36) therebetween. Each airfoil (14) includes opposite pressure and suction sides (20, 22) and extends in chord between opposite leading and trailing edges (24, 26). Each platform (16) has a scalloped flow surface including a bulge (38) adjoining the pressure side (20) adjacent the leading edge (24), and a bowl (40) adjoining the suction side (22) aft of the leading edge (24).
摘要翻译：涡轮级包括连接到相应的平台（16）的一排翼型件（14），以在它们之间限定流动通道（36）。每个翼片（14）包括相对的压力和吸力侧（20,22），并且在相对的前缘和后缘（24,26）之间以和弦延伸。每个平台（16）具有扇形流动表面，该扇形流动表面包括邻近前缘（24）的压力侧（20）的凸起（38）和邻接前缘边缘的吸力侧（22） 24）。

96. 发明公开

EP1533475A2 Hot gas path component with mesh and dimpled cooling 审中-公开
标题翻译：带有网状和凹坑冷却的热气路径组件
公开(公告)号：EP1533475A2
公开(公告)日：2005-05-25
申请号：EP04255631.6
申请日：2004-09-16
申请人： GENERAL ELECTRIC COMPANY
发明人： Bunker, Ronald Scott , Bailey, Jeremy Clyde , Lee, Ching-Pang
IPC分类号： F01D5/18 , F01D25/12
CPC分类号： F28F13/12 , F01D5/187 , F05D2230/90 , F05D2250/28 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , F28F3/022 , F28F3/044 , Y02T50/67 , Y02T50/671 , Y02T50/676 , Y10T29/4932
摘要： A component (10) includes at least one wall (12) having an inner portion (14) and an outer portion (16). A number of pins (18) extend between the inner and outer portions of the wall. The pins define a mesh cooling arrangement (20) having a number of flow channels (22). A number of dimples (24) are located in at least one of the inner and outer portions of the wall. The component may also include a number of turbulators disposed on at least one of the inner and outer portions of the wall.
摘要翻译：部件（10）包括具有内部部分（14）和外部部分（16）的至少一个壁（12）。多个销（18）在壁的内部和外部之间延伸。这些销限定了具有许多流动通道（22）的网状冷却装置（20）。多个凹坑（24）位于壁的内部和外部中的至少一个中。部件还可以包括设置在壁的内部和外部中的至少一个上的多个湍流器。

97. 发明公开

EP1413829A2 Combustor liner with inverted turbulators 有权
标题翻译： Brennkammerwand mit umgekehrten Wirbelelementen
公开(公告)号：EP1413829A2
公开(公告)日：2004-04-28
申请号：EP03256700.0
申请日：2003-10-23
申请人： GENERAL ELECTRIC COMPANY
发明人： Bunker, Ronald Scott
IPC分类号： F23R3/00 , F23M5/00
CPC分类号： F23M5/00 , F05B2240/122 , F05B2260/222 , F23M5/085 , F23R3/002 , F23R3/005
摘要： A combustor liner (46) for a gas turbine, the combustor liner having a substantially cylindrical shape; and a plurality of axially spaced circumferential grooves (48) formed in an outside surface of the combustor liner.
摘要翻译：在具有圆筒形状的燃烧器衬套（46）的外表面上形成轴向间隔开的周向槽（48）。

98. 发明公开

EP1211385A2 Making cooling channels in turbine components 有权
标题翻译： Anbringung vonKühlkanälen在Turbinenteilen
公开(公告)号：EP1211385A2
公开(公告)日：2002-06-05
申请号：EP01310021.9
申请日：2001-11-29
申请人： General Electric Company
发明人： Bunker, Ronald Scott
IPC分类号： F01D5/18
CPC分类号： F01D9/02 , B23P2700/06 , F05D2230/10 , F05D2230/21 , F05D2240/81 , Y10T29/49318 , Y10T29/49336 , Y10T29/49341 , Y10T29/49716
摘要： The cooling scheme of a gas turbine engine component is modified to improve local cooling without redesigning the investment casting. The modification includes forming at least one channel (28) in the component such that the channel (28) is in fluid communication with a cooling medium source associated with the component. The channel (28) is then partially filled with a removable material (36), and the removable material (36) is covered with a patch material (38) so as to completely fill the channel (28). Lastly, the removable material (36) is removed from the channel (28) so as to create an internal cooling passage (40) in the component that is in fluid communication with the cooling medium source.
摘要翻译：修改燃气涡轮发动机部件的冷却方案以改进局部冷却，而不需要重新设计熔模铸造。修改包括在部件中形成至少一个通道（28），使得通道（28）与与部件相关联的冷却介质源流体连通。然后，通道（28）部分地被可移除材料（36）填充，并且可移除材料（36）被补片材料（38）覆盖，以便完全填充通道（28）。最后，可拆卸材料（36）从通道（28）移除，以在与冷却介质源流体连通的部件中形成内部冷却通道（40）。

99. 发明授权

EP0815995B1 Method for making cylindrical structures with cooling channels 失效
标题翻译：一种用于生产圆柱状结构的具有冷却通道处理
公开(公告)号：EP0815995B1
公开(公告)日：2002-06-05
申请号：EP97304420.9
申请日：1997-06-24
申请人： GENERAL ELECTRIC COMPANY
发明人： Ritter, Ann Melinda , Hughes, John Raymond , Jackson, Melvin Robert , Kirkpatrick, Francis Lawrence , Cunha, Francisco Jose Tenreiro , Abuaf, Nesim , Bunker, Ronald Scott
IPC分类号： B22F3/14 , B22F3/15 , B22F5/10 , B23P15/00
CPC分类号： F23R3/005 , B22F5/10 , B22F2005/103 , B23P15/00 , B23P2700/13 , F05B2250/231 , Y02T50/675 , Y10T29/49346 , Y10T29/49353

100. 发明公开

EP0816010A2 Method of making double-walled turbine components from pre-consolidated assemblies 失效
标题翻译：维尔法赫恩·赫斯特伦·冯·多普尔万德根
公开(公告)号：EP0816010A2
公开(公告)日：1998-01-07
申请号：EP97304424.1
申请日：1997-06-24
申请人： GENERAL ELECTRIC COMPANY
发明人： Ritter, Ann Melinda , Jackson, Melvin Robert , Abuaf, Nesim , Campbell, Robert Patrick , Bunker, Ronald Scott
IPC分类号： B23P15/00 , B21H1/06 , F01D9/02 , F23R3/00 , F01D25/12
CPC分类号： F01D9/023 , B21H1/06 , B23P15/00 , B23P2700/13 , F23R3/002 , Y02T50/67 , Y02T50/672 , Y02T50/675
摘要： Methods of making gas turbine structures with cooling channels, such as, for example, combustor/transition pieces for gas turbines having a double wall with a plurality of cooling channels, having axially and/or circumferential cross-flow passages positioned between the structure's inner member and the outer member to provide cooling air thereto, are disclosed. A representative method of producing such annular structures having a hot and a cold wall, and joining ribs, for the inner and the outer components of an annulus, such as for jet engine turbine combustors, to net shape as an annular pre-form includes: forming a pre-form assembly including materials for the hot wall, cold wall, and ribs and sacrificial segments for maintaining cooling channels during forming of the pre-assembly and later processing; rolling the pre-form to a required thickness and length as a flat pre-form; hoop-rolling the preform to a required thickness and a required length; welding the assembly; ring rolling to the pre-form to a desired inner diameter, ring-rolling or metal spinning the pre-form to produce the proper wall contour and removing the sacrificial material to open the cooling channels.
摘要翻译：制造具有冷却通道的燃气轮机结构的方法，例如具有带有多个冷却通道的双壁的燃气轮机的燃烧器/过渡件，具有位于结构的内部构件之间的轴向和/或周向的横向流动通道和外部构件以提供冷却空气。用于制造具有热壁和冷壁的环形结构的代表性方法，以及用于环形的内部和外部部件（例如用于喷气发动机涡轮机燃烧器）的连接肋，作为环形预成型件的净形状包括：形成预成型组件，其包括用于热壁，冷壁和肋的材料和牺牲段，用于在预组装和后续处理的形成期间保持冷却通道; 将预制件滚压成所需的厚度和长度作为平坦的预制件; 将预成型件卷绕成所需的厚度和所需的长度; 焊接组件; 环形轧制成预成形为期望的内径，环轧或金属纺丝预成型件以产生适当的壁轮廓并且去除牺牲材料以打开冷却通道。

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