专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US08845285B2 Gas turbine stator assembly 有权
标题翻译：燃气轮机定子总成
公开(公告)号：US08845285B2
公开(公告)日：2014-09-30
申请号：US13347269
申请日：2012-01-10
申请人： David Wayne Weber , Christopher Lee Golden
发明人： David Wayne Weber , Christopher Lee Golden
IPC分类号： F01D9/00
CPC分类号： F01D11/005 , F05D2240/11 , F05D2240/57 , F05D2240/81 , F05D2250/294
摘要： According to one aspect, a turbine assembly includes a second component circumferentially adjacent to a first component, wherein the first and second components each have a surface proximate a hot gas path and a first side surface of the first component to be joined to a second side surface of the second component. The assembly also includes a first slot formed longitudinally in the first component which extends from a first slot inner wall to the first side surface and a second slot formed longitudinally in the second component which extends from a second slot inner wall to the second side surface. The assembly also includes a first groove formed in a hot side surface of the first slot, the first groove extending from the first slot inner wall to the first side surface, wherein the first groove comprises a tapered cross-sectional geometry.
摘要翻译：根据一个方面，涡轮机组件包括与第一部件周向相邻的第二部件，其中第一和第二部件各自具有接近热气体路径的表面和要接合到第二部分的第一部件的第一侧表面第二部件的表面。组件还包括在第一部件中纵向形成的第一槽，其从第一槽内壁延伸到第一侧表面;以及第二槽，其在第二部件中纵向形成，其从第二槽内壁延伸到第二侧表面。组件还包括形成在第一槽的热侧表面中的第一凹槽，第一凹槽从第一槽内壁延伸到第一侧表面，其中第一凹槽包括锥形横截面几何形状。

2. 发明授权

US09151179B2 Turbine shroud segment cooling system and method 有权
标题翻译：涡轮护罩段冷却系统及方法
公开(公告)号：US09151179B2
公开(公告)日：2015-10-06
申请号：US13086279
申请日：2011-04-13
申请人： Benjamin Paul Lacy , Stephen William Tesh , David Wayne Weber
发明人： Benjamin Paul Lacy , Stephen William Tesh , David Wayne Weber
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F05D2230/90 , F05D2240/14 , F05D2250/185 , F05D2260/204 , Y02T50/676 , Y10T29/49229
摘要： The present embodiments are generally directed toward systems and methods for cooling one or more shroud segments of a gas turbine engine. For example, in a first embodiment, a shroud segment is provided that is configured to at least partially surround a turbine blade of a turbine engine. The shroud segment includes a body and a microchannel disposed in the body. The microchannel is configured to flow a cooling fluid through the body.
摘要翻译：本实施例通常涉及用于冷却燃气涡轮发动机的一个或多个护罩段的系统和方法。例如，在第一实施例中，提供了构造成至少部分地围绕涡轮发动机的涡轮叶片的护罩段。护罩区段包括主体和设置在身体中的微通道。微通道构造成使冷却流体流过身体。

3. 发明申请

US20130287546A1 TURBINE SHROUD COOLING ASSEMBLY FOR A GAS TURBINE SYSTEM 有权
标题翻译：用于气体涡轮机系统的涡轮风冷却组件
公开(公告)号：US20130287546A1
公开(公告)日：2013-10-31
申请号：US13456407
申请日：2012-04-26
申请人： Benjamin Paul Lacy , David Edward Schick , David Wayne Weber
发明人： Benjamin Paul Lacy , David Edward Schick , David Wayne Weber
IPC分类号： F01D25/26
CPC分类号： F01D5/00 , F01D5/08 , F01D5/084 , F01D5/225 , F01D25/12 , F01D25/14 , F01D25/26 , F05D2260/201 , F05D2260/204
摘要： A turbine shroud cooling assembly for a gas turbine system includes an outer shroud component disposed within a turbine section of the gas turbine system and proximate a turbine section casing, wherein the outer shroud component includes at least one airway for ingesting an airstream. Also included is an inner shroud component disposed radially inward of, and fixedly connected to, the outer shroud component, wherein the inner shroud component includes a plurality of microchannels extending in at least one of a circumferential direction and an axial direction for cooling the inner shroud component with the airstream from the at least one airway.
摘要翻译：用于燃气涡轮机系统的涡轮机罩冷却组件包括设置在燃气涡轮机系统的涡轮机部分内并且靠近涡轮部分壳体的外护罩部件，其中外护罩部件包括用于摄取气流的至少一个气道。还包括内护罩部件，其设置在外护罩部件的径向内侧并且固定地连接到外护罩部件上，其中内护罩部件包括沿圆周方向和轴向方向中的至少一个延伸的多个微通道，用于冷却内护罩具有来自至少一个气道的气流的部件。

4. 发明申请

US20130177411A1 SYSTEM AND METHOD FOR SEALING A GAS PATH IN A TURBINE 审中-公开
标题翻译：用于密封涡轮气体路径的系统和方法
公开(公告)号：US20130177411A1
公开(公告)日：2013-07-11
申请号：US13343935
申请日：2012-01-05
申请人： David Wayne Weber , Victor John Morgan
发明人： David Wayne Weber , Victor John Morgan
IPC分类号： F01D9/04 , B23P15/00
CPC分类号： F01D11/005 , F01D11/001 , F01D11/003 , F01D25/246 , F05D2300/211 , Y10T29/49323
摘要： A system for sealing a gas path in a turbine includes a stator ring segment, a shroud segment adjacent to the stator ring segment, and a first load-bearing surface between the stator ring segment and the shroud segment. A first non-metallic gasket is in contact with the first load-bearing surface between the stator ring segment and the shroud segment. A method for sealing a gas path in a turbine includes placing a non-metallic gasket between any two of a stator ring segment, a shroud segment, and a casing.
摘要翻译：用于密封涡轮机中的气体路径的系统包括定子环段，与定子环段相邻的护罩段，以及定子环段和护罩区段之间的第一承载表面。第一非金属垫圈与定子环段和护罩段之间的第一承载表面接触。用于密封涡轮机中的气体路径的方法包括将非金属垫圈放置在定子环段，护罩段和壳体中的任何两个之间。

5. 发明申请

US20120219404A1 TURBINE SHROUD AND A METHOD FOR MANUFACTURING THE TURBINE SHROUD 有权
标题翻译：涡轮风机和制造涡轮风机的方法
公开(公告)号：US20120219404A1
公开(公告)日：2012-08-30
申请号：US13034810
申请日：2011-02-25
申请人： David Wayne Weber , Gregory Thomas Foster
发明人： David Wayne Weber , Gregory Thomas Foster
IPC分类号： F01D11/08 , B23P11/00
CPC分类号： F01D11/08 , F01D9/04 , F01D11/122 , F01D25/12 , F01D25/246 , F05D2230/232 , F05D2230/237 , F05D2240/11 , F05D2260/20 , Y10T29/49297
摘要： A turbine shroud includes a body having a plurality of sides. A first inward facing groove is defined by a first side of the body, and a first seal covers the first inward facing groove to define a first fluid passage in the first inward facing groove along the first side of the body. A first inlet port through the first seal fluid communication through the first seal into the first fluid passage. A method for forming a turbine shroud includes forming an inner surface and forming an outer surface opposed to the inner surface, wherein the outer surface is configured for exposure to a hot gas path. The method further includes defining a first slot in the inner surface and extending a first seal across the first slot to define a first fluid passage in the first slot along the inner surface.
摘要翻译：涡轮机罩包括具有多个侧面的主体。第一向内的凹槽由本体的第一侧限定，第一密封件覆盖第一向内的凹槽，以沿着主体的第一侧在第一向内的凹槽中限定第一流体通道。通过第一密封件的第一入口端口通过第一密封件进入第一流体通道。形成涡轮机罩的方法包括形成内表面并形成与内表面相对的外表面，其中外表面构造成暴露于热气路径。该方法还包括在内表面中限定第一槽，并且跨越第一槽延伸第一密封件，以沿着内表面限定第一槽中的第一流体通道。

6. 发明申请

US20130177412A1 Gas Turbine Stator Assembly 有权
标题翻译：燃气轮机定子装配
公开(公告)号：US20130177412A1
公开(公告)日：2013-07-11
申请号：US13347269
申请日：2012-01-10
申请人： David Wayne Weber , Christopher Lee Golden
发明人： David Wayne Weber , Christopher Lee Golden
IPC分类号： F01D9/04
CPC分类号： F01D11/005 , F05D2240/11 , F05D2240/57 , F05D2240/81 , F05D2250/294
摘要： According to one aspect, a turbine assembly includes a second component circumferentially adjacent to a first component, wherein the first and second components each have a surface proximate a hot gas path and a first side surface of the first component to be joined to a second side surface of the second component. The assembly also includes a first slot formed longitudinally in the first component which extends from a first slot inner wall to the first side surface and a second slot formed longitudinally in the second component which extends from a second slot inner wall to the second side surface. The assembly also includes a first groove formed in a hot side surface of the first slot, the first groove extending from the first slot inner wall to the first side surface, wherein the first groove comprises a tapered cross-sectional geometry.
摘要翻译：根据一个方面，涡轮机组件包括与第一部件周向相邻的第二部件，其中第一和第二部件各自具有接近热气体路径的表面和要接合到第二部分的第一部件的第一侧表面第二部件的表面。组件还包括在第一部件中纵向形成的第一槽，其从第一槽内壁延伸到第一侧表面;以及第二槽，其在第二部件中纵向形成，其从第二槽内壁延伸到第二侧表面。组件还包括形成在第一槽的热侧表面中的第一凹槽，第一凹槽从第一槽内壁延伸到第一侧表面，其中第一凹槽包括锥形横截面几何形状。

7. 发明申请

US20130134678A1 SHIM SEAL ASSEMBLIES AND ASSEMBLY METHODS FOR STATIONARY COMPONENTS OF ROTARY MACHINES 审中-公开
标题翻译：旋转机械静态组件的SHIM密封组件和组装方法
公开(公告)号：US20130134678A1
公开(公告)日：2013-05-30
申请号：US13306090
申请日：2011-11-29
申请人： Neelesh Nandkumar Sarawate , Victor John Morgan , David Wayne Weber
发明人： Neelesh Nandkumar Sarawate , Victor John Morgan , David Wayne Weber
IPC分类号： F16J15/02
CPC分类号： F01D11/005 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F05D2250/12 , F05D2250/75 , F16J15/0812 , F16J15/0893 , F16J15/128
摘要： A seal assembly for a rotary machine is provided. The seal assembly includes a shim seal including multiple seal plates forming a C-shaped shim seal or a box shaped shim seal. The C-shaped shim seal includes a first side portion having a smaller width than that of an opposing second side portion, and the second side portion of the C-shaped shim seal includes a gap between at least two straight faces with an inward angle for allowing positioning within the slot between stator components. The box shaped seal includes a plurality of cuts at two opposing sides or corners for allowing high pressure fluid to occupy the cavity of the box-shaped shim seal. The seal may be inserted within one or more slots between adjacent stator components of the rotary machine.
摘要翻译：提供了一种用于旋转机器的密封组件。密封组件包括垫片密封件，其包括形成C形垫片密封件或盒形垫片密封件的多个密封板。 C形垫片密封件包括具有比相对的第二侧部的宽度小的第一侧部分，并且C形垫片密封件的第二侧部分包括在至少两个直角之间的间隙，允许定位在定子部件之间的槽内。箱形密封件包括在两个相对的侧面或拐角处的多个切口，用于允许高压流体占据箱形垫片密封件的空腔。密封件可以插入在旋转机器的相邻定子部件之间的一个或多个槽内。

8. 发明申请

US20120263576A1 TURBINE SHROUD SEGMENT COOLING SYSTEM AND METHOD 有权
标题翻译：涡轮风冷段冷却系统及方法
公开(公告)号：US20120263576A1
公开(公告)日：2012-10-18
申请号：US13086279
申请日：2011-04-13
申请人： Benjamin Paul Lacy , Stephen William Tesh , David Wayne Weber
发明人： Benjamin Paul Lacy , Stephen William Tesh , David Wayne Weber
IPC分类号： F01D25/12 , B23P17/00
CPC分类号： F01D25/12 , F05D2230/90 , F05D2240/14 , F05D2250/185 , F05D2260/204 , Y02T50/676 , Y10T29/49229
摘要： The present embodiments are generally directed toward systems and methods for cooling one or more shroud segments of a gas turbine engine. For example, in a first embodiment, a shroud segment is provided that is configured to at least partially surround a turbine blade of a turbine engine. The shroud segment includes a body and a microchannel disposed in the body. The microchannel is configured to flow a cooling fluid through the body.
摘要翻译：本实施例通常涉及用于冷却燃气涡轮发动机的一个或多个护罩段的系统和方法。例如，在第一实施例中，提供了构造成至少部分地围绕涡轮发动机的涡轮叶片的护罩段。护罩区段包括主体和设置在身体中的微通道。微通道构造成使冷却流体流过身体。

9. 发明授权

US10161523B2 Enhanced cloth seal 有权
公开(公告)号：US10161523B2
公开(公告)日：2018-12-25
申请号：US13336750
申请日：2011-12-23
申请人： Neelesh Nandkumar Sarawate , David Wayne Weber , Omprakash Samudrala , Victor John Morgan
发明人： Neelesh Nandkumar Sarawate , David Wayne Weber , Omprakash Samudrala , Victor John Morgan
IPC分类号： F16J15/02 , F16J15/08 , F01D11/00
摘要： The embodiments described herein provide a cloth seal for use with turbine components. The cloth seal includes first and second cloth layers. One or more central shims are positioned between the first and second cloth layers so as to block a leakage flow path. Another shim is positioned on and seals the opposite side of the first cloth layer from the one or more central shims positioned between the first and second cloth layers so as to block another leakage flow path. Yet another sealing shim may be positioned on the opposite side of the second cloth layer from the one or more central shims positioned between the first and second cloth layers to as to seal the opposite side of the second cloth layer and block another leakage flow path.

10. 发明授权

US09188228B2 Layered seal for turbomachinery 有权
标题翻译：涡轮机分层密封
公开(公告)号：US09188228B2
公开(公告)日：2015-11-17
申请号：US13560357
申请日：2012-07-27
申请人： Neelesh Nandkumar Sarawate , Victor John Morgan , David Wayne Weber
发明人： Neelesh Nandkumar Sarawate , Victor John Morgan , David Wayne Weber
IPC分类号： F16J15/12 , F01D11/00
CPC分类号： F16J15/128 , F01D11/005 , F05D2240/57
摘要： The present application provides seal assemblies for reducing leakages between adjacent components of turbomachinery. The seal assemblies may include outer shims, and at least a portion of the outer shims may be substantially impervious. At least one of the outer shims may be configured for sealing engagement with seal slots of the adjacent components. The seal assemblies may also include at least one of an inner shim and a filler layer positioned between the outer shims. The at least one inner shim may be substantially solid and the at least one filler layer may be relatively porous. The seal assemblies may be sufficiently flexible to account for misalignment between the adjacent components, sufficiently stiff to meet assembly requirements, and sufficiently robust to operating meet requirements associated with turbomachinery.
摘要翻译：本申请提供了用于减少涡轮机械的相邻部件之间的泄漏的密封组件。密封组件可以包括外垫片，并且外垫片的至少一部分可以是基本上不可渗透的。外部垫片中的至少一个可以构造成用于与相邻部件的密封槽密封接合。密封组件还可以包括位于外垫片之间的内垫片和填料层中的至少一个。至少一个内垫片可以是基本上固体的，并且至少一个填料层可以是相对多孔的。密封组件可以足够灵活以考虑相邻部件之间的不对准，足够坚硬以满足组装要求，并且足够坚固以满足与涡轮机械相关的要求。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式