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1. 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）。

2. 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）。

3. 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。

4. 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。

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

US20120006028A1 DAMPING RESONATOR WITH IMPINGEMENT COOLING 有权
标题翻译：阻尼谐振器与冲击冷却
公开(公告)号：US20120006028A1
公开(公告)日：2012-01-12
申请号：US12832116
申请日：2010-07-08
申请人： Ching-Pang Lee , Danning You , Reinhard Schilp , Chander Prakash
发明人： Ching-Pang Lee , Danning You , Reinhard Schilp , Chander Prakash
IPC分类号： F02C7/24 , F02C7/12
CPC分类号： F01D9/023 , F02C7/12 , F05D2260/96 , F23R3/06 , F23R2900/00014
摘要： A resonance chamber (42) has an outer wall (32) with coolant inlet holes (34A-C), an inner wall (36) with acoustic holes (38), and side walls (40A-C) between the inner and outer walls. A depression (33A-C) in the outer wall has a bottom portion (50) that is close to the inner wall compared to peaks (37A-C) of the outer wall. The coolant inlet holes may be positioned along the bottom portion of the depression and along a bottom portion of the side walls to direct coolant flows (44, 51) toward impingement locations (43) on the inner wall that are out of alignment with the acoustic holes. This improves impingement cooling efficiency. The peaks (37A-C) of the outer wall provide volume in the resonance chamber for a target resonance.
摘要翻译：共振室（42）具有外壁（32），其具有冷却剂入口孔（34A-C），具有声孔（38）的内壁（36）和内壁和外壁之间的侧壁（40A-C）。外壁上的凹部（33A-C）具有与外壁的顶部（37A-C）相比靠近内壁的底部部分（50）。冷却剂入口孔可以沿着凹陷的底部部分并且沿着侧壁的底部部分定位，以将冷却剂流（44,41）引向内壁上与声学不对准的冲击位置（43）孔。这提高了冲击冷却效率。外壁的峰（37A-C）在共振室中提供用于目标共振的体积。

7. 发明申请

US20110262695A1 Discreetly Defined Porous Wall Structure for Transpirational Cooling 有权
标题翻译：用于旋转冷却的谨慎定义的多孔壁结构
公开(公告)号：US20110262695A1
公开(公告)日：2011-10-27
申请号：US12765004
申请日：2010-04-22
申请人： Ching-Pang Lee , Chander Prakash , Gary B. Merrill , Andreas Heselhaus , Andrew J. Burns
发明人： Ching-Pang Lee , Chander Prakash , Gary B. Merrill , Andreas Heselhaus , Andrew J. Burns
IPC分类号： B32B3/10
CPC分类号： F01D5/182 , B33Y80/00 , F01D5/183 , F01D5/184 , F05D2230/22 , F05D2230/90 , F05D2250/18 , F05D2250/185 , F05D2250/28 , F05D2250/30 , F05D2260/203 , F05D2260/221 , Y10T428/24273
摘要： A wall structure (32, 42, 68, 70, 80) with layers (A, B, C, D, E) of non-random voids (26A, 26B, 28B, 30B) that interconnect to form discretely defined tortuous passages between an interior (21) and an exterior surface (23) of the wall for transpiration cooling of the wall. A coolant flow (38) through the wall may be metered by restrictions in coolant outlets (31) and/or within the passages to minimize the coolant requirement. Pockets (44) may be formed on the exterior surface of the wall for thermal Insulation (46). The layers may be formed by lamination, additive manufacturing, or casting. Layer geometries include alternating layers (A, B, C) with different overlapping void patterns (42), 3-D lattice structures (70), and offset waffle structures (80).
摘要翻译：具有非随机空隙（26A，26B，28B，30B）的层（A，B，C，D，E）的壁结构（32,42,68,70,80），其互连以在所述壁的内部（21）和外表面（23）用于所述壁的蒸发冷却。通过壁的冷却剂流（38）可以通过冷却剂出口（31）和/或通道内的限制来计量，以使冷却剂需求最小化。口袋（44）可以形成在隔热壁的外表面上（46）。层可以通过层压，添加剂制造或铸造形成。层几何形状包括具有不同重叠空白图案（42），3-D网格结构（70）和偏置华夫饼结构（80）的交替层（A，B，C）。

8. 发明授权

US07758306B2 Turbine assembly for a gas turbine engine and method of manufacturing the same 有权
标题翻译：用于燃气涡轮发动机的涡轮组件及其制造方法
公开(公告)号：US07758306B2
公开(公告)日：2010-07-20
申请号：US11615514
申请日：2006-12-22
申请人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
发明人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
IPC分类号： F01D1/02
CPC分类号： F01D9/041 , F01D5/141 , F01D5/145 , Y02T50/673 , Y10T29/49236
摘要： A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.
摘要翻译：一种用于燃气涡轮发动机的涡轮组件。涡轮机组件包括至少一个定子组件，其包括径向内部带和至少一个定子叶片，其从内部带径向向外延伸。定子叶片包括具有与内带相邻的根部部分和尖端部分的翼型件。翼型件还包括限定在根部部分和尖端部分之间的至少一个精简方向变化。涡轮组件还包括至少一个包括至少一个转子叶片的涡轮叶片组件。叶片组件与定子组件流体连通地联接，使得在它们之间限定轴向间隔。与所述至少一个瘦方向变化相邻限定的轴向间隔比邻近根部限定的轴向间隔宽。

9. 发明申请

US20080152505A1 GAS TURBINE ENGINES INCLUDING MULTI-CURVE STATOR VANES AND METHODS OF ASSEMBLING THE SAME 有权
标题翻译：气体涡轮发动机，其中包括多级定子风扇及其组装方法
公开(公告)号：US20080152505A1
公开(公告)日：2008-06-26
申请号：US11615556
申请日：2006-12-22
申请人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
发明人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Scott Michael Carson
IPC分类号： F01D9/00
CPC分类号： F01D5/141 , F01D5/145 , F01D9/041 , F05D2240/301 , F05D2250/611 , F05D2250/71 , Y02T50/673
摘要： A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.
摘要翻译：可用于发动机组件的定子叶片。定子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处联接到第一侧壁。翼型件从根部径向延伸到尖端部分。前缘和后缘中的每一个包括在根部部分和尖端部分之间限定的至少一个瘦方向改变和多个扫掠方向改变。

10. 发明申请

US20070059173A1 TURBINE AIRFOIL CURVED SQUEALER TIP WITH TIP SHELF 有权
标题翻译：涡轮机空气IL ED SQ SQ SQ。。。。。。。
公开(公告)号：US20070059173A1
公开(公告)日：2007-03-15
申请号：US11162434
申请日：2005-09-09
申请人： Ching-Pang Lee , Chander Prakash
发明人： Ching-Pang Lee , Chander Prakash
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F05D2250/712 , Y02T50/67
摘要： An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil. At least a portion of the pressure-side tip wall is recessed from the pressure sidewall to define an outwardly facing tip shelf, such that the pressure-side tip wall and the tip shelf define a trough therebetween.
摘要翻译：用于燃气涡轮发动机的翼型件包括根部，尖端，前缘，后缘以及大致沿径向轴线延伸的相对的压力和吸力侧壁。翼型件包括在压力侧和吸力侧壁之间延伸的顶盖; 并且间隔开的吸入侧和压力侧尖端壁从尖端帽径向向外延伸以在它们之间限定尖端腔。压力侧末端壁包括连续凹入的弯曲弧形部分，其至少一部分从翼型件的径向轴向向外延伸。压力侧顶端壁的至少一部分从压力侧壁凹入以限定向外的顶端架，使得压力侧顶端壁和尖端架在其间限定槽。

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