公开(公告)号：US20150017007A1

公开(公告)日：2015-01-15

申请号：US14499386

申请日：2014-09-29

申请人： ALSTOM Technology Ltd

发明人： Herbert BRANDL

IPC分类号： F01D5/22

CPC分类号： F01D5/22 ,  F01D5/147 ,  F01D5/3007 ,  F01D5/326 ,  F01D11/008 ,  F05B2240/57 ,  F05D2230/50 ,  F05D2230/51 ,  F05D2240/55 ,  F05D2240/57 ,  F05D2240/80 ,  F05D2260/30 ,  F05D2260/31 ,  F05D2260/36 ,  F05D2260/96

摘要： The invention relates to a turbine blade, including a blade having a front edge and a rear edge, which blade transitions by means of a shaft into a blade root designed for fastening the turbine blade, and including a platform, which is arranged at the lower end of the blade in order to bound a flow channel. The platform is designed as a separate component and can be connected to the blade in a form-fit manner. Flexible application is achieved in that the platform is composed of several individual platform elements, which enclose the blade in the assembled state.

摘要翻译： 本发明涉及一种涡轮叶片，其包括具有前边缘和后边缘的叶片，该叶片借助于轴转变成设计成用于紧固涡轮叶片的叶根，并且包括布置在下部的平台 以便结合流动通道。 该平台设计为单独的部件，并且可以以适合形式的方式连接到刀片。 实现灵活的应用是，平台由几个单独的平台元件组成，其将叶片包围在组装状态。

公开(公告)号：US20150010393A1

公开(公告)日：2015-01-08

申请号：US13937109

申请日：2013-07-08

申请人： General Electric Company

发明人： Matthew Troy Hafner

IPC分类号： F01D11/00

CPC分类号： F01D11/001 ,  F01D5/3015 ,  F01D11/003 ,  F01D11/005 ,  F01D11/006 ,  F01D11/008 ,  Y10T29/49245

摘要： A system includes a multi-stage turbine that includes a first turbine stage having a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel. The turbine also includes a second turbine stage having a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel. The turbine also includes a seal assembly extending axially between the first and second turbine stages. The seal assembly includes a first coverplate coupled to the first turbine stage. The first coverplate includes a first air director. The seal assembly also includes a second coverplate coupled to the second turbine stage. The second coverplate comprises a second air director. The seal assembly also includes an interstage seal. The first coverplate, the second coverplate, or both are configured to support the interstage seal.

摘要翻译： 一种系统包括多级涡轮机，该多级涡轮机包括具有第一轮的第一涡轮级，该第一轮具有围绕第一车轮周向间隔开的多个第一叶片段。 涡轮机还包括具有第二轮的第二涡轮级，该第二轮具有围绕第二轮围绕圆周间隔开的多个第二叶片段。 涡轮机还包括在第一和第二涡轮级之间轴向延伸的密封组件。 密封组件包括联接到第一涡轮级的第一盖板。 第一盖板包括第一空气导向器。 密封组件还包括联接到第二涡轮级的第二盖板。 第二盖板包括第二空气导向器。 密封组件还包括级间密封。 第一盖板，第二盖板或两者被构造成支撑级间密封。

公开(公告)号：US20140271143A1

公开(公告)日：2014-09-18

申请号：US13833162

申请日：2013-03-15

申请人： GKN AEROSPACE SERVICES STRUCTURES, CORP.

发明人： Christopher J. Feeney

IPC分类号： F01D11/00 ,  B29C45/14 ,  B29C70/68

CPC分类号： F01D11/008 ,  B29C45/14 ,  B29C70/68 ,  F05D2220/36 ,  F05D2250/11 ,  F05D2300/603 ,  Y02T50/672

摘要： A fan spacer for placement between a pair of adjacent blades in a fan assembly and a related method of making. The fan spacer has a spacer body including an airflow surface shaped to direct air between the pair of adjacent blades in which the airflow surface is shaped on opposing sides to correspond to the pair of adjacent blades. An over molded feature is molded onto the airflow surface of the spacer body in which the over molded feature both includes an erosion coating on the airflow surface and, on the two opposing sides, seals configured to seal against the pair of adjacent blades on the opposing sides of the airflow surface.

摘要翻译： 用于放置在风扇组件中的一对相邻叶片之间的风扇间隔件和相关的制造方法。 风扇间隔件具有间隔件主体，其包括气流表面，该气流表面成形为在一对相邻的叶片之间引导空气，其中气流表面在相对侧成形，以对应于该对相邻的叶片。 模制成型的特征模制在隔离物体的气流表面上，其中过度模制的特征在气流表面上均包括侵蚀涂层，并且在两个相对的两侧上，密封构造成密封在相对的一对相邻刀片上 气流表面的两侧。

公开(公告)号：US08740556B2

公开(公告)日：2014-06-03

申请号：US13031893

申请日：2011-02-22

申请人： Thierry Georges Paul Papin ,  Alain Raffy ,  Dominique Raulin

发明人： Thierry Georges Paul Papin ,  Alain Raffy ,  Dominique Raulin

IPC分类号： F01D9/04

CPC分类号： F01D9/041 ,  F01D11/008 ,  F01D25/162 ,  F05B2260/301 ,  F05D2240/12 ,  F05D2300/603 ,  Y02T50/672 ,  Y02T50/673

摘要： A structural and aerodynamic module including two blades each extending along a longitudinal axis, in which each blade includes a leading edge, a trailing edge, a radially inner edge, and a radially outer edge, is provided. The module also includes a radially inner platform mechanically connecting the radially inner edges of the two blades, and a radially outer platform mechanically connecting the radially outer edges of the two blades such that the two blades and the radially outer and inner platforms delimit a flow stream. The two blades and the platforms are made from a composite material and the two blades are fixed on the radially outer and inner platforms using screw-nut assemblies.

摘要翻译： 包括两个叶片的结构和空气动力学模块，每个叶片沿着纵向轴线延伸，其中每个叶片包括前缘，后缘，径向内边缘和径向外边缘。 模块还包括机械连接两个叶片的径向内边缘的径向内部平台和径向外部平台，其机械地连接两个叶片的径向外边缘，使得两个叶片和径向外部和内部平台限定流动流 。 两个叶片和平台由复合材料制成，两个叶片使用螺母组件固定在径向外平台和内平台上。

公开(公告)号：US20140112792A1

公开(公告)日：2014-04-24

申请号：US14143828

申请日：2013-12-30

申请人： United Technologies Corporation

发明人： Seth J. Thomen ,  Christopher Corcoran

IPC分类号： F01D5/22 ,  F01D11/00

CPC分类号： F01D5/22 ,  F01D11/006 ,  F01D11/008 ,  F05D2250/25 ,  Y10S416/50

摘要： A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions.

摘要翻译： 用于联接相邻涡轮机叶片的平台的减震器销包括第一平坦纵向端部区域，第二平坦纵向端部区域和减小的横截面面积。 减小的横截面积由第一主体区域与第一平坦纵向端部区域分离，并且减小的横截面面积与第二平坦纵向端部区域通过第二主体区域分离。 横截面积减小的截面积小于第一和第二主体区域的横截面面积。

公开(公告)号：US20140003949A1

公开(公告)日：2014-01-02

申请号：US13926316

申请日：2013-06-25

申请人： SNECMA

发明人： Virginie ADAM ,  Guillaume Fribourg

IPC分类号： F01D11/00

CPC分类号： F01D11/008 ,  C22C21/00 ,  C22C21/10 ,  C22C21/12 ,  C22C21/18 ,  F01D5/02 ,  F01D5/28 ,  F01D5/30 ,  F01D5/3007 ,  F01D11/005 ,  Y02T50/671 ,  Y02T50/673 ,  Y10T29/49321

摘要： The invention concerns an interblade platform (3) of a turbomachine fan, characterized in that it is produced:in an aluminum alloy belonging to the 7xxx series that has undergone full-temper heat treatment of the T7x type, orin an aluminum alloy belonging to the 2xxx series that has undergone heat treatment of the T6x or T8x type.

摘要翻译： 本发明涉及一种涡轮机风扇的叶片间平台（3），其特征在于：在属于经过T7x型全温热处理的属于7xxx系列的铝合金中，或属于属于 经过T6x或T8x型热处理的2xxx系列。

公开(公告)号：US08596981B2

公开(公告)日：2013-12-03

申请号：US12817605

申请日：2010-06-17

申请人： Mathew Ashley Charles Hoyland ,  Dale Edward Evans

发明人： Mathew Ashley Charles Hoyland ,  Dale Edward Evans

IPC分类号： F01D5/22 ,  F01D11/00

CPC分类号： F01D5/22 ,  F01D11/008 ,  F05D2220/36 ,  F05D2230/60

摘要： An annulus filler for mounting to a rotor disc of a gas turbine engine is provided to bridge the gap between adjacent blades. A first part is connectable to the rotor disc between adjacent blades. There is a separate second part that engages with the first part after connecting the rotor blades to the rotor disc. When installed, the filler is spaced from each blade by a respective clearance gap (G), and an operational configuration in which it contacts each of said blades. Engagement of the second part with the first part is effective to urge the first part from said installation configuration to said operational configuration and thus into blade contact. The first part may have a mounting region for connection to the rotor disc and allow, in said first step of said procedure, the mounting region to remain visible from a radially outer viewpoint.

摘要翻译： 用于安装到燃气涡轮发动机的转子盘的环形填料被提供以桥接相邻叶片之间的间隙。 第一部分可连接到相邻叶片之间的转子盘。 在将转子叶片连接到转子盘之后，存在与第一部分接合的单独的第二部分。 当安装时，填料与每个叶片隔开相应的间隙（G），以及与其接触每个所述叶片的操作构型。 第二部分与第一部分的接合有效地将第一部分从所述安装构造推到所述操作构型，从而成为刀片接触。 第一部分可以具有用于连接到转子盘的安装区域，并且在所述过程的所述第一步骤中允许安装区域从径向外部视点保持可见。

公开(公告)号：US20130309073A1

公开(公告)日：2013-11-21

申请号：US13471718

申请日：2012-05-15

申请人： Charles W. Brown

发明人： Charles W. Brown

IPC分类号： F01D5/02 ,  F16J15/32 ,  B23P6/00

CPC分类号： F01D5/3053 ,  F01D5/3007 ,  F01D11/008 ,  F05D2230/80 ,  F05D2240/80 ,  Y10T29/49318

摘要： A fan section for a gas turbine engine includes a hub. A fan blade is secured to the hub. A platform is removably secured to the hub and is arranged adjacent to the fan blade. The platform has a body with lateral sides that each include a channel. A seal is removably received in each of the channels, with one of the seals abutting the fan blade. A method of repairing the fan blade platform includes the steps of removing a nose cone to provide access to a hub, detaching a platform from the hub, and pulling the seal from a groove in the platform.

摘要翻译： 用于燃气涡轮发动机的风扇部分包括轮毂。 风扇叶片固定在轮毂上。 平台可移除地固定到轮毂并且被布置成与风扇叶片相邻。 该平台具有侧面的主体，每个侧面均包括通道。 密封件可移除地容纳在每个通道中，其中一个密封件抵靠风扇叶片。 修理风扇叶片平台的方法包括以下步骤：去除鼻锥以提供对轮毂的接近，将平台与轮毂分离，以及从所述平台中的凹槽拉动密封件。

公开(公告)号：US08535013B2

公开(公告)日：2013-09-17

申请号：US12413615

申请日：2009-03-30

申请人： Ian Colin Deuchar Care ,  Dale Edward Evans

发明人： Ian Colin Deuchar Care ,  Dale Edward Evans

IPC分类号： F01D5/30

CPC分类号： F01D11/008 ,  F01D25/06 ,  F05D2260/96 ,  Y02T50/672

摘要： A fan assembly of a gas turbine engine, the fan assembly includes an array of radially extending blades defining gaps therebetween and an annulus filler located within at least one gap. The annulus filler includes at least two individual bodies arranged circumferentially adjacent one another with at least one adjacent a blade, one of the bodies includes a flexible wall arranged to centrifuge outwardly against the other body thereby urging both bodies against the blades and securing them during engine operation.

摘要翻译： 一种燃气涡轮发动机的风扇组件，所述风扇组件包括限定了间隙的径向延伸的叶片阵列和位于至少一个间隙内的环形填料。 环形填料包括至少两个单独的体，其彼此周向相邻地设置有至少一个相邻的叶片，其中一个主体包括布置成向外抵靠另一个体离心的柔性壁，从而将两个体抵靠在叶片上并将其固定在发动机 操作。

公开(公告)号：US08523189B2

公开(公告)日：2013-09-03

申请号：US12835163

申请日：2010-07-13

申请人： Cedric B. Harper

发明人： Cedric B. Harper

IPC分类号： F16J15/08

CPC分类号： F01D11/008 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2250/40 ,  F05D2260/30 ,  Y02T50/671 ,  Y10T156/10

摘要： A sealing assembly (100) for at least partially sealing a gap (102) leading to a void (104) between first and second members (110, 120), the first and second members forming part of a gas-washed surface of a jet engine, wherein the sealing assembly comprises: a bridging portion (130) couplable to one of the first and second members and movable to engage the other of the first and second members so as to block off the void between the first and second members from the gas-washed surface.

摘要翻译： 一种用于至少部分地密封通向第一和第二构件（110,120）之间的空隙（104）的间隙（102）的密封组件（100），所述第一和第二构件形成气体冲洗表面的一部分 发动机，其中所述密封组件包括：桥接部分（130），其可联接到所述第一和第二构件之一并且可移动以接合所述第一和第二构件中的另一个，以便阻挡所述第一构件和所述第二构件之间的空隙 气洗表面。