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1. 发明授权

US08721291B2 Flow directing member for gas turbine engine 有权
标题翻译：燃气轮机发动机导流构件
公开(公告)号：US08721291B2
公开(公告)日：2014-05-13
申请号：US13180578
申请日：2011-07-12
申请人： Ching-Pang Lee , Kok-Mun Tham , Paul H. Vitt , Stephen R. Williamson , Matthew D. Montgomery , Chander Prakash , Melissa Harris
发明人： Ching-Pang Lee , Kok-Mun Tham , Paul H. Vitt , Stephen R. Williamson , Matthew D. Montgomery , Chander Prakash , Melissa Harris
IPC分类号： F01D5/14
CPC分类号： F01D5/081 , F01D5/141 , F05D2240/81 , F05D2270/17
摘要： In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall.
摘要翻译：在燃气涡轮发动机中，流动引导构件包括支撑在转子上的平台，并且包括径向面向的端壁和至少一个轴向面向轴向表面，该轴向表面从与所述端壁的连接处径向向内延伸。导流构件还包括从端壁径向向外延伸的翼型件和流体流动引导构件。流体流动导向特征包括轴向延伸到轴向表面的凹槽。凹槽具有径向内槽端部和径向外槽端部，其中外槽端部在轴向表面和端壁之间的连接处限定轴向延伸的凹口，并在端壁中形成开口，用于将冷却流体引导到端壁。

2. 发明申请

US20130017095A1 FLOW DIRECTING MEMBER FOR GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的流动导向构件
公开(公告)号：US20130017095A1
公开(公告)日：2013-01-17
申请号：US13180578
申请日：2011-07-12
申请人： Ching-Pang Lee , Kok-Mun Tham , Paul H. Vitt , Stephen R. Williamson , Matthew D. Montgomery , Chander Prakash , Melissa Harris
发明人： Ching-Pang Lee , Kok-Mun Tham , Paul H. Vitt , Stephen R. Williamson , Matthew D. Montgomery , Chander Prakash , Melissa Harris
IPC分类号： F01D5/14
CPC分类号： F01D5/081 , F01D5/141 , F05D2240/81 , F05D2270/17
摘要： In a gas turbine engine, a flow directing member includes a platform supported on a rotor and includes a radially facing endwall and at least one axially facing axial surface extending radially inwardly from a junction with the endwall. The flow directing member further includes an airfoil extending radially outwardly from the endwall and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface. The groove has a radially inner groove end and a radially outer groove end, wherein the outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall.
摘要翻译：在燃气涡轮发动机中，流动引导构件包括支撑在转子上的平台，并且包括径向面向的端壁和至少一个轴向面向轴向表面，该轴向表面从与所述端壁的连接处径向向内延伸。导流构件还包括从端壁径向向外延伸的翼型件和流体流动引导构件。流体流动导向特征包括轴向延伸到轴向表面的凹槽。凹槽具有径向内槽端部和径向外槽端部，其中外槽端部在轴向表面和端壁之间的连接处限定轴向延伸的凹口，并在端壁中形成开口，用于将冷却流体引导到端壁。

3. 发明授权

US08926283B2 Turbine blade angel wing with pumping features 有权
标题翻译：涡轮叶片天使翼具有抽水功能
公开(公告)号：US08926283B2
公开(公告)日：2015-01-06
申请号：US13688411
申请日：2012-11-29
申请人： Ching-Pang Lee , Kok-Mun Tham , Paul H. Vitt , Eric Schroeder
发明人： Ching-Pang Lee , Kok-Mun Tham , Paul H. Vitt , Eric Schroeder
IPC分类号： F01D11/00 , F01D5/14 , F01D11/02
CPC分类号： F01D5/141 , F01D5/145 , F01D11/001 , F01D11/02
摘要： A gas turbine engine, including: a plurality of blades (60) assembled into an annular row of blades and partly defining a hot gas path (26) and a cooling fluid path (24), wherein the cooling fluid path extends from a rotor cavity (22) to the hot gas path; an angel wing assembly (99) disposed on a side (74) of a base (76) of the row of blades; and pumping features (130) distributed about the angel wing assembly configured to impart, at a narrowest gap (42) of the cooling fluid path, motion to a flow of cooling fluid flowing there through. The plurality of pumping features, the angel wing assembly, and the base of the row of blades are effective to produce a helical motion to the flow of cooling fluid as it enters the hot gas path.
摘要翻译：一种燃气涡轮发动机，包括：多个叶片（60），其组装成环形叶片的叶片并且部分地限定热气体路径（26）和冷却流体路径（24），其中冷却流体路径从转子腔（22）到热气路径; 设置在所述一排叶片的基部（76）的侧面（74）上的天使翼组件（99）以及围绕天使翼组件分布的泵送特征（130），其被配置为在冷却流体路径的最窄间隙（42）处施加对流过其的冷却流体流的运动。多个泵送特征，天使翼组件和叶片排的基部有效地在冷却流体进入热气体路径时产生螺旋运动。

4. 发明申请

US20140147250A1 TURBINE BLADE ANGEL WING WITH PUMPING FEATURES 有权
标题翻译：涡轮叶片天鹅绒与抽水功能
公开(公告)号：US20140147250A1
公开(公告)日：2014-05-29
申请号：US13688411
申请日：2012-11-29
申请人： Ching-Pang Lee , Kok-Mun Tham , Paul H. Vitt , Eric Schroeder
发明人： Ching-Pang Lee , Kok-Mun Tham , Paul H. Vitt , Eric Schroeder
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/145 , F01D11/001 , F01D11/02
摘要： A gas turbine engine, including: a plurality of blades (60) assembled into an annular row of blades and partly defining a hot gas path (26) and a cooling fluid path (24), wherein the cooling fluid path extends from a rotor cavity (22) to the hot gas path; an angel wing assembly (99) disposed on a side (74) of a base (76) of the row of blades; and pumping features (130) distributed about the angel wing assembly configured to impart, at a narrowest gap (42) of the cooling fluid path, motion to a flow of cooling fluid flowing there through. The plurality of pumping features, the angel wing assembly, and the base of the row of blades are effective to produce a helical motion to the flow of cooling fluid as it enters the hot gas path.
摘要翻译：一种燃气涡轮发动机，包括：多个叶片（60），其组装成环形叶片的叶片并且部分地限定热气体路径（26）和冷却流体路径（24），其中冷却流体路径从转子腔（22）到热气路径; 设置在所述一排叶片的基部（76）的侧面（74）上的天使翼组件（99）以及围绕天使翼组件分布的泵送特征（130），其被配置为在冷却流体路径的最窄间隙（42）处施加对流过其的冷却流体流的运动。多个泵送特征，天使翼组件和叶片排的基部有效地在冷却流体进入热气体路径时产生螺旋运动。

5. 发明授权

US09206904B2 Seal including flexible seal strips 有权
标题翻译：密封包括柔性密封条
公开(公告)号：US09206904B2
公开(公告)日：2015-12-08
申请号：US12832141
申请日：2010-07-08
申请人： Ching-Pang Lee , Vincent P. Laurello , Chander Prakash , Kok-Mun Tham
发明人： Ching-Pang Lee , Vincent P. Laurello , Chander Prakash , Kok-Mun Tham
IPC分类号： F16J15/32 , F01D11/02
CPC分类号： F16J15/3292 , F01D11/02 , F05D2240/57
摘要： A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion.
摘要翻译：一种用于实现密封的密封件，其防止流体沿轴向流动通过形成在包括可旋转轴和定子结构的两个相对移动部件之间的环形空间。密封构件包括多个柔性密封条。每个密封条包括平面板，该平面板径向地延伸穿过环形空间并且具有支撑到定子结构的径向外端，以及限定沿轴向方向沿宽度方向延伸的尖端部分的径向内端，该尖端部分与可旋转的轴。密封条中的至少一个包括延伸穿过密封条并且位于密封条的前缘和后缘之间的多个穿孔，用于实现与尖端部分相邻的密封条的增加的柔性。

6. 发明申请

US20120007318A1 SEAL INCLUDING FLEXIBLE SEAL STRIPS 有权
标题翻译：密封包括柔性密封条
公开(公告)号：US20120007318A1
公开(公告)日：2012-01-12
申请号：US12832141
申请日：2010-07-08
申请人： Ching-Pang Lee , Vincent P. Laurello , Chander Prakash , Kok-Mun Tham
发明人： Ching-Pang Lee , Vincent P. Laurello , Chander Prakash , Kok-Mun Tham
IPC分类号： F02F11/00 , F16J15/44
CPC分类号： F16J15/3292 , F01D11/02 , F05D2240/57
摘要： A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion.
摘要翻译：一种用于实现密封的密封件，其防止流体沿轴向流动通过形成在包括可旋转轴和定子结构的两个相对移动部件之间的环形空间。密封构件包括多个柔性密封条。每个密封条包括平面板，该平面板径向地延伸穿过环形空间并且具有支撑到定子结构的径向外端，以及限定沿轴向方向沿宽度方向延伸的尖端部分的径向内端，该尖端部分与可旋转的轴。密封条中的至少一个包括延伸穿过密封条并且位于密封条的前缘和后缘之间的多个穿孔，用于实现与尖端部分相邻的密封条的增加的柔性。

7. 发明申请

US20110150653A1 Plasma Induced Flow Control of Boundary Layer at Airfoil Endwall 失效
标题翻译：翼型端壁边界层等离子体诱导流量控制
公开(公告)号：US20110150653A1
公开(公告)日：2011-06-23
申请号：US12640242
申请日：2009-12-17
申请人： Matthew D. Montgomery , Ching-Pang Lee , Chander Prakash
发明人： Matthew D. Montgomery , Ching-Pang Lee , Chander Prakash
IPC分类号： F01D5/14 , F01D9/02
CPC分类号： F01D5/145 , F05D2270/172 , Y02T50/67 , Y02T50/673
摘要： Plasma generators (48, 49, 70, 71) in an endwall (25) of an airfoil (22) induce aerodynamic flows in directions (50) that modify streamlines (47) of the endwall boundary layer toward a streamline geometry (46) of a midspan region of the airfoil. This reduces vortices (42) generated by the momentum deficit of the boundary layer, increasing aerodynamic efficiency. The plasma generators may be arrayed around the leading edge as well as between two airfoils (22) in a gas turbine nozzle structure, and may be positioned at correction points (68) in streamlines caused by surface contouring (66) of the endwall. The plasma generators may be oriented to generate flow vectors (74) that combine with boundary layer flow vectors (72) to produce resultant flow vectors (76) in directions that reduce turbulence.
摘要翻译：翼型件（22）的端壁（25）中的等离子体发生器（48,49,70,71）在方向（50）上引起空气动力学流动，所述方向（50）将端壁边界层的流线（47）改变为流线几何形状（46）翼型的跨跨区域。这减少了由边界层的动量缺失产生的旋涡（42），从而提高了空气动力学效率。等离子体发生器可以围绕前缘以及在燃气涡轮喷嘴结构中的两个翼型件（22）之间排列，并且可以位于由端壁的表面轮廓（66）引起的流线中的校正点（68）处。等离子体发生器可以被定向以产生与边界层流向量（72）组合的流向量（74），以在减少湍流的方向上产生合成流向量（76）。

8. 发明授权

US08435001B2 Plasma induced flow control of boundary layer at airfoil endwall 失效
标题翻译：翼型端壁边界层等离子体诱导流量控制
公开(公告)号：US08435001B2
公开(公告)日：2013-05-07
申请号：US12640242
申请日：2009-12-17
申请人： Matthew D. Montgomery , Ching-Pang Lee , Chander Prakash
发明人： Matthew D. Montgomery , Ching-Pang Lee , Chander Prakash
IPC分类号： F01D9/00
CPC分类号： F01D5/145 , F05D2270/172 , Y02T50/67 , Y02T50/673
摘要： Plasma generators (48, 49, 70, 71) in an endwall (25) of an airfoil (22) induce aerodynamic flows in directions (50) that modify streamlines (47) of the endwall boundary layer toward a streamline geometry (46) of a midspan region of the airfoil. This reduces vortices (42) generated by the momentum deficit of the boundary layer, increasing aerodynamic efficiency. The plasma generators may be arrayed around the leading edge as well as between two airfoils (22) in a gas turbine nozzle structure, and may be positioned at correction points (68) in streamlines caused by surface contouring (66) of the endwall. The plasma generators may be oriented to generate flow vectors (74) that combine with boundary layer flow vectors (72) to produce resultant flow vectors (76) in directions that reduce turbulence.
摘要翻译：翼型件（22）的端壁（25）中的等离子体发生器（48,49,70,71）在方向（50）上引起空气动力学流动，所述方向（50）将端壁边界层的流线（47）改变为流线几何形状（46）翼型的跨跨区域。这减少了由边界层的动量缺失产生的旋涡（42），从而提高了空气动力学效率。等离子体发生器可以围绕前缘以及在燃气涡轮喷嘴结构中的两个翼型件（22）之间排列，并且可以位于由端壁的表面轮廓（66）引起的流线中的校正点（68）处。等离子体发生器可以被定向以产生与边界层流向量（72）组合的流向量（74），以在减少湍流的方向上产生合成流向量（76）。

9. 发明授权

US09121298B2 Finned seal assembly for gas turbine engines 有权
标题翻译：燃气涡轮发动机的翅片密封组件
公开(公告)号：US09121298B2
公开(公告)日：2015-09-01
申请号：US13534060
申请日：2012-06-27
申请人： Ching-Pang Lee , Kok-Mun Tham , John M. Owen , Gary D. Lock , Carl M. Sangan , Vincent P. Laurello
发明人： Ching-Pang Lee , Kok-Mun Tham , John M. Owen , Gary D. Lock , Carl M. Sangan , Vincent P. Laurello
IPC分类号： F04D11/00 , F01D11/00
CPC分类号： F01D11/001
摘要： A seal assembly provided between a hot gas path and a disc cavity in a turbine engine includes an annular outer wing member extending from an axially facing side of a rotor structure toward an adjacent non-rotating vane assembly, and a plurality of fins extending radially inwardly from the outer wing member and extending toward the adjacent non-rotating vane assembly. The fins are arranged such that a space having a component in a circumferential direction is defined between adjacent fins. Rotation of the fins during operation of the engine effects a pumping of purge air from the disc cavity toward the hot gas path to assist in limiting hot working gas leakage from the hot gas path to the disc cavity by forcing the hot working gas away from the seal assembly.
摘要翻译：设置在涡轮发动机中的热气体路径和盘腔之间的密封组件包括从转子结构的轴向相对侧朝向相邻的非旋转叶片组件延伸的环形外翼构件，以及径向向内延伸的多个翅片从外翼构件延伸并且朝向相邻的非旋转叶片组件延伸。翅片被布置成使得在相邻翅片之间限定具有圆周方向的部件的空间。在发动机操作期间，翅片的旋转使得吹扫空气从盘腔朝向热气体路径泵送，以通过迫使热的工作气体远离热空气路径来帮助限制热的工作气体从热气体路径泄漏到盘腔中密封组装。

10. 发明申请

US20150003973A1 AFT OUTER RIM SEAL ARRANGEMENT 有权
标题翻译： AFT外部RIM密封安排
公开(公告)号：US20150003973A1
公开(公告)日：2015-01-01
申请号：US13930482
申请日：2013-06-28
申请人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
发明人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
IPC分类号： F01D11/02 , F01D5/18
CPC分类号： F01D11/02 , F01D5/082 , F01D5/18 , F01D5/187 , F01D11/04 , F05D2260/14
摘要： An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.
摘要翻译：外缘密封装置（10），包括：以转子盘（31）的纵向轴线（30）为中心的环形边缘（70），其在前面延伸并具有前端（72），面向外的表面（74）和面向内的表面（76）; 从天线叶片（22）的底部向后延伸的下部天使翼（62），并且具有设置在所述边缘向内相对表面的径向内侧的后端（64），以限定下部天使翼密封间隙（80）; 从所述涡轮叶片基部向后延伸的上天使翼（66），并且具有设置在所述轮缘朝外的表面的径向外侧的后端（68），以限定上天使翼密封间隙（80,82）; 以及设置在下天使翼密封间隙中的边缘向内表面上的导向叶片（100）。抽吸翼（102）可以设置在上天使翼密封间隙中的上天使翼密封后端。

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