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1. 发明申请

US20110299978A1 GAS TURBINE ENGINE SEALING STRUCTURE 有权
标题翻译：气体涡轮发动机密封结构
公开(公告)号：US20110299978A1
公开(公告)日：2011-12-08
申请号：US13151355
申请日：2011-06-02
申请人： Gennadiy Afanasiev , John N. Strain , Robert W. Sunshine , Robert D. Barker
发明人： Gennadiy Afanasiev , John N. Strain , Robert W. Sunshine , Robert D. Barker
IPC分类号： F01D11/08
CPC分类号： F01D11/005 , F05D2230/642 , F05D2240/11 , F05D2250/192 , F05D2250/292 , F05D2250/314 , F05D2260/30
摘要： 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.
摘要翻译：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。

2. 发明授权

US5538393A Turbine shroud segment with serpentine cooling channels having a bend passage 失效
标题翻译：具有蛇形冷却通道的涡轮机护罩段具有弯曲通道
公开(公告)号：US5538393A
公开(公告)日：1996-07-23
申请号：US381173
申请日：1995-01-31
申请人： Ralph J. Thompson , Daniel E. Kane , Robert W. Sunshine
发明人： Ralph J. Thompson , Daniel E. Kane , Robert W. Sunshine
IPC分类号： F01D11/08 , F01D25/12
CPC分类号： F01D11/08 , F01D25/12
摘要： A turbine shroud segment for use in a gas turbine engine includes a serpentine channel along at least one axial edge of the segment. Various construction details are developed that disclose a channel for efficiently flowing cooling fluid through an axial edge of a shroud segment. In a particular embodiment, a turbine shroud segment includes a leading edge serpentine channel having a bend passage which includes a purge hole to avoid separating flow in the bend passage.
摘要翻译：用于燃气涡轮发动机的涡轮机护罩段包括沿着该段的至少一个轴向边缘的蛇形通道。开发了各种结构细节，其公开了用于使冷却流体有效地流过护罩段的轴向边缘的通道。在特定实施例中，涡轮机护罩段包括具有弯曲通道的前缘蛇形通道，该弯曲通道包括净化孔，以避免在弯曲通道中分离流动。

3. 发明授权

US09234431B2 Seal assembly for controlling fluid flow 有权
标题翻译：用于控制流体流动的密封组件
公开(公告)号：US09234431B2
公开(公告)日：2016-01-12
申请号：US13178784
申请日：2011-07-08
申请人： Christian Kowalski , Fan Zhang , Uwe Lohse , Robert W. Sunshine , Burkhard Voss
发明人： Christian Kowalski , Fan Zhang , Uwe Lohse , Robert W. Sunshine , Burkhard Voss
IPC分类号： F02C7/12 , F02K3/02 , F02C7/20 , F02C6/08 , F01D9/02 , F01D11/00 , F01D11/02 , F01D11/18
CPC分类号： F01D9/023 , F01D11/006 , F01D11/025 , F01D11/18 , F05D2240/56 , F05D2300/502
摘要： 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).
摘要翻译：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部（52,54）和环形密封中间部分（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部（52,54）和外框架构件（46）的材料不同的热膨胀系数。

4. 发明授权

US08821114B2 Gas turbine engine sealing structure 有权
标题翻译：燃气轮机发动机密封结构
公开(公告)号：US08821114B2
公开(公告)日：2014-09-02
申请号：US13151355
申请日：2011-06-02
申请人： Gennadiy Afanasiev , John N. Strain , Robert W. Sunshine , Robert D. Barker
发明人： Gennadiy Afanasiev , John N. Strain , Robert W. Sunshine , Robert D. Barker
IPC分类号： F01D11/00
CPC分类号： F01D11/005 , F05D2230/642 , F05D2240/11 , F05D2250/192 , F05D2250/292 , F05D2250/314 , F05D2260/30
摘要： 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.
摘要翻译：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。

5. 发明申请

US20120017594A1 SEAL ASSEMBLY FOR CONTROLLING FLUID FLOW 有权
标题翻译：密封组件控制流体流动
公开(公告)号：US20120017594A1
公开(公告)日：2012-01-26
申请号：US13178784
申请日：2011-07-08
申请人： Christian Kowalski , Fan Zhang , Uwe Lohse , Robert W. Sunshine , Burkhard Voss
发明人： Christian Kowalski , Fan Zhang , Uwe Lohse , Robert W. Sunshine , Burkhard Voss
IPC分类号： F02C7/28 , F16J15/447 , F16J15/44 , F16J15/16
CPC分类号： F01D9/023 , F01D11/006 , F01D11/025 , F01D11/18 , F05D2240/56 , F05D2300/502
摘要： 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).
摘要翻译：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部（52,54）和环形密封中间部分（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部（52,54）和外框架构件（46）的材料不同的热膨胀系数。

6. 发明授权

US07234918B2 Gap control system for turbine engines 有权
标题翻译：涡轮发动机间隙控制系统
公开(公告)号：US07234918B2
公开(公告)日：2007-06-26
申请号：US11014271
申请日：2004-12-16
申请人： Dieter Brillert , Wayne Giddens , Harald Hoell , Robert W. Sunshine , Juergen Hermeler , Hans-Thomas Bolms
发明人： Dieter Brillert , Wayne Giddens , Harald Hoell , Robert W. Sunshine , Juergen Hermeler , Hans-Thomas Bolms
IPC分类号： F01D11/08
CPC分类号： F01D11/001 , F01D11/025
摘要： Embodiments of the invention relate to a system and method for controlling the size of gaps in a turbine engine. In many instances, it is desirable to minimize the size of the gaps between neighboring rotating and stationary components in a turbine engine, such as between a disc cover plate and a proximate pre-swirler. According to embodiments of the invention, each component can be provided with a sealing surface. The sealing surfaces can be angled relative to the axis of rotation. The sealing surfaces are spaced from each other so as to form a gap therebetween. The sealing surfaces may or may not be substantially parallel. As a result of such configuration, the size of the gap can be controlled by axial and radial movement of the components. For example, the gap between the cover plate and the pre-swirler can be adjusted by axially movement of the rotor.
摘要翻译：本发明的实施例涉及一种用于控制涡轮发动机中的间隙尺寸的系统和方法。在许多情况下，期望使涡轮发动机中的相邻旋转和静止部件之间的间隙的尺寸最小化，例如在盘盖板和邻近预旋流器之间。根据本发明的实施例，每个部件可以设置有密封表面。密封表面可以相对于旋转轴线成角度。密封表面彼此间隔开，以便在它们之间形成间隙。密封表面可以或可以不基本上平行。作为这种构造的结果，可以通过部件的轴向和径向运动来控制间隙的尺寸。例如，盖板和预旋流器之间的间隙可以通过转子的轴向运动来调节。

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