公开(公告)号：WO2011153393A3

公开(公告)日：2012-04-26

申请号：PCT/US2011038994

申请日：2011-06-03

Applicant: SIEMENS ENERGY INC ,  AFANASIEV GENNADIY ,  STRAIN JOHN N ,  SUNSHINE ROBERT W ,  BARKER ROBERT D

Inventor： AFANASIEV GENNADIY ,  STRAIN JOHN N ,  SUNSHINE ROBERT W ,  BARKER ROBERT D

IPC: F01D11/00

CPC classification number: F01D11/005 ,  F05D2230/642 ,  F05D2240/11 ,  F05D2250/192 ,  F05D2250/292 ,  F05D2250/314 ,  F05D2260/30

Abstract: A turbine section (16) having a plurality flow path components forming a plurality of guide vane rings (30 a-d) and ring segments (32 a-d) arranged in axial succession to define a boundary of a hot gas duct (28). A vane carrier (36) located around the gas duct, and sealing elements (40) extend radially between circumferentially extending grooves (50) in the vane carrier and respective grooves (54) in the flow path components. The sealing elements include radially inner and outer edges (58, 60), and at least one axially facing side (62, 64) defining a chamfered portion (66, 68) extending to one of the edges to accommodate axial movement of the sealing element about the one edge within a respective groove.

Abstract translation: 具有形成多个引导叶片环（30a-d）的多个流动路径部件和环形部分（32a-d）的涡轮机部分（16），所述多个流动路径部件轴向连续地布置以限定热气体管道（28）的边界。 位于气体管道周围的叶片载体（36）和密封元件（40）在叶片载体中的周向延伸的凹槽（50）和流动路径部件中的相应凹槽（54）之间径向延伸。 密封元件包括径向的内边缘和外边缘（58,60），并且至少一个轴向面对的侧面（62,64）限定了延伸到其中一个边缘的倒角部分（66,68），以适应密封元件 围绕相应凹槽内的一个边缘。

公开(公告)号：WO2012012330A1

公开(公告)日：2012-01-26

申请号：PCT/US2011/044355

申请日：2011-07-18

Applicant: SIEMENS ENERGY, INC. ,  KOWALSKI, Christian ,  ZHANG, Fan ,  LOHSE, Uwe ,  SUNSHINE, Robert W. ,  VOSS, Burkhard

Inventor： KOWALSKI, Christian ,  ZHANG, Fan ,  LOHSE, Uwe ,  SUNSHINE, Robert W. ,  VOSS, Burkhard

IPC: F01D9/02 ,  F01D11/18 ,  F01D11/02 ,  F01D11/00 ,  F01D25/28

CPC classification number: F01D9/023 ,  F01D11/006 ,  F01D11/025 ,  F01D11/18 ,  F05D2240/56 ,  F05D2300/502

Abstract: A seal assembly (50, 60) for a gas turbine engine for controlling air flow between a diffuser (48) and rotor disks comprising first and second annular flange ends (52, 54) and an annular seal mid-section (56) between and operatively connected to the flange ends (52, 54). The first and second annular flange ends (52, 54) abut respective outer frame members (46) of the diffuser, whereby a fluid flow path is formed between the seal assembly (50, 60) and the rotor disks (42). The first and second end flanges (52, 54) are composed of a material having a coefficient of thermal expansion that is substantially the same as a coefficient of thermal expansion of the material of the outer frame members (46). In addition, the material of the seal mid-section (56) has a coefficient of thermal expansion that is different than that of the materials of the annular flange ends (52, 54) and outer frame members (46)

Abstract translation: 一种用于燃气涡轮发动机的密封组件（50,60），用于控制扩散器（48）和转子盘之间的空气流，所述转子盘包括第一和第二环形凸缘端（52,54）和环形密封中段（56） 可操作地连接到凸缘端部（52,54）。 第一和第二环形凸缘端部（52,54）邻接扩散器的相应的外部框架构件（46），由此在密封组件（50,60）和转子盘（42）之间形成流体流动路径。 第一和第二端部凸缘（52,54）由具有与外框架构件（46）的材料的热膨胀系数基本相同的热膨胀系数的材料构成。 此外，密封中段（56）的材料具有与环形凸缘端（52,54）和外框架构件（46）的材料不同的热膨胀系数，

公开(公告)号：WO2011153393A2

公开(公告)日：2011-12-08

申请号：PCT/US2011/038994

申请日：2011-06-03

Applicant: SIEMENS ENERGY, INC. ,  AFANASIEV, Gennadiy ,  STRAIN, John, N. ,  SUNSHINE, Robert, W. ,  BARKER, Robert, D.

Inventor： AFANASIEV, Gennadiy ,  STRAIN, John, N. ,  SUNSHINE, Robert, W. ,  BARKER, Robert, D.

IPC: F01D11/00

CPC classification number: F01D11/005 ,  F05D2230/642 ,  F05D2240/11 ,  F05D2250/192 ,  F05D2250/292 ,  F05D2250/314 ,  F05D2260/30

Abstract: A turbine section having a plurality flow path components forming a plurality of guide vane rings and ring segments arranged in axial succession to define a boundary of a hot gas duct. A vane carrier located around the gas duct, and sealing elements extend radially between circumferentially extending grooves in the vane carrier and respective grooves in the flow path components. The sealing elements include radially inner and outer edges, and at least one axially facing side defining a chamfered portion extending to one of the edges to accommodate axial movement of the sealing element about the one edge within a respective groove.

Abstract translation: 涡轮部分具有多个流动路径部件，所述多个流动路径部件形成多个引导叶片环和环形部分，所述多个导向叶圈环和轴向连续地布置以限定热气体管道的边界。 位于气体管道周围的叶片载体和密封元件在叶片承载件中的周向延伸的凹槽和流动路径部件中的相应凹槽之间径向延伸。 密封元件包括径向内部和外部边缘，并且至少一个轴向相对侧限定延伸到边缘中的一个的倒角部分，以适应密封元件围绕相应凹槽中的一个边缘的轴向移动。