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11. 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）。

12. 发明申请

US20110268556A1 PLASMA ACTUATOR CONTROLLED FILM COOLING 失效
标题翻译：等离子体执行器控制膜冷却
公开(公告)号：US20110268556A1
公开(公告)日：2011-11-03
申请号：US12770932
申请日：2010-04-30
申请人： Matthew D. Montgomery , Chander Prakash
发明人： Matthew D. Montgomery , Chander Prakash
IPC分类号： F04D29/58
CPC分类号： F01D5/186 , F05D2260/202 , F05D2270/172
摘要： A film cooling apparatus with a cooling hole (46) in a component wall (40). A first surface (42) of the wall is subject to a hot gas flow (48). A second surface (44) receives a coolant gas (50). The coolant flows through the hole, then downstream over the first surface (42). One or more pairs of cooperating electrodes (60-61, 62-63, 80-81) generates and accelerates a plasma (70) that creates a body force acceleration (71, 82) in the coolant flow that urges the coolant flow to turn around the entry edge (57) and/or the exit edge (58) of the cooling hole without separating from the adjacent surface (47, 42). The electrodes may have a geometry that spreads the coolant into a fan shape over the hot surface (42) of the component wall (40).
摘要翻译：一种在组件壁（40）中具有冷却孔（46）的薄膜冷却装置。壁的第一表面（42）经受热气流（48）。第二表面（44）接收冷却剂气体（50）。冷却剂流过孔，然后流过第一表面（42）的下游。一对或多对配合电极（60-61,62-63,80-81）产生并加速等离子体（70），其产生在促使冷却剂流转向的冷却剂流中的体力加速度（71,82）围绕冷却孔的入口边缘（57）和/或出口边缘（58），而不与相邻表面（47,42）分离。电极可以具有将冷却剂扩散到组件壁（40）的热表面（42）上的扇形形状的几何形状。

13. 发明申请

US20140023483A1 AIRFOIL ASSEMBLY INCLUDING VORTEX REDUCING AT AN AIRFOIL LEADING EDGE 有权
标题翻译： AIRFOIL组件，包括VORTEX减少在AIRFOIL领先的边缘
公开(公告)号：US20140023483A1
公开(公告)日：2014-01-23
申请号：US13552708
申请日：2012-07-19
申请人： David J. Wiebe , Bruce L. Smith , Matthew D. Montgomery
发明人： David J. Wiebe , Bruce L. Smith , Matthew D. Montgomery
IPC分类号： F01D25/00 , F01D5/18 , F01D9/06
CPC分类号： F01D25/00 , F01D5/145 , F01D5/18 , F01D9/041 , F01D9/06 , F05D2240/80 , Y10T29/49234
摘要： An airfoil assembly including an endwall and an airfoil extending from the into a gas flow path. The endwall includes upstream and downstream edges, and is defined on a platform structure having a front surface extending radially in a direction of a thickness of the platform structure. At least one fluid injection passage extends through the platform structure in a direction from the upstream edge toward the downstream edge of the endwall. The fluid injection passage has an outlet opening defined at the endwall and an inlet opening in fluid communication with a pressurized fluid source. The fluid injection passage extends at a shallow angle relative to a plane of the endwall wherein the fluid injection passage defines a passage axis passing through the front surface and the endwall for effecting energization of a boundary layer between the outlet opening and the airfoil leading edge.
摘要翻译：一种翼型组件，其包括端壁和从所述气流通道延伸的翼型件。端壁包括上游和下游边缘，并且限定在具有在平台结构的厚度方向上径向延伸的前表面的平台结构上。至少一个流体喷射通道在从端壁的上游边缘向下游边缘的方向上延伸穿过平台结构。流体注入通道具有限定在端壁处的出口开口和与加压流体源流体连通的入口开口。流体喷射通道相对于端壁的平面以较小的角度延伸，其中流体喷射通道限定通过前表面和端壁的通道轴线，以实现出口和翼型前缘之间的边界层的通电。

14. 发明申请

US20110236182A1 Control of Blade Tip-To-Shroud Leakage in a Turbine Engine By Directed Plasma Flow 失效
标题翻译：通过定向等离子体流控制涡轮发动机中的叶片至罩的泄漏
公开(公告)号：US20110236182A1
公开(公告)日：2011-09-29
申请号：US12729380
申请日：2010-03-23
申请人： David J. Wiebe , Matthew D. Montgomery
发明人： David J. Wiebe , Matthew D. Montgomery
IPC分类号： F01D15/00 , F01D11/10
CPC分类号： F01D11/10 , F01D11/20 , F05D2270/172
摘要： An electrode (54) in the tip (31) of a turbine or compressor blade (30), and a series of electrodes (68) in a shroud (36, 64) that surrounds a rotation path (33) of the blade tip. As the blade tip reaches each shroud electrode, a controller (74) activates an electrical potential between them that generates a plasma-induced gas flow (76) directed toward the pressure side (PS) of the airfoil. The plasma creates a seal between the blade tip and the shroud, and induces a gas flow that opposes a leakage gas flow (52) from the pressure side to the suction side (SS) of the blade over the blade tip (31).
摘要翻译：涡轮或压缩机叶片（30）的尖端（31）中的电极（54）和围绕叶片尖端的旋转路径（33）的护罩（36,64）中的一系列电极（68）。当叶片尖端到达每个护罩电极时，控制器（74）激活它们之间的电位，其产生指向翼型的压力侧（PS）的等离子体引起的气流（76）。等离子体在叶片尖端和护罩之间产生密封，并且引起气体流动，该气流与来自叶片尖端（31）的叶片的压力侧到吸力侧（SS）的泄漏气体流（52）相对。

15. 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）。

16. 发明授权

US08550768B2 Method for improving the stall margin of an axial flow compressor using a casing treatment 有权
标题翻译：用于改善使用套管处理的轴流式压缩机的失速余量的方法
公开(公告)号：US08550768B2
公开(公告)日：2013-10-08
申请号：US12795781
申请日：2010-06-08
申请人： Matthew D. Montgomery
发明人： Matthew D. Montgomery
IPC分类号： F04D27/02
CPC分类号： F01D5/143 , F04D29/526 , F04D29/685 , F05D2240/11 , F05D2270/17
摘要： A method for determining a preferred circumferential groove arrangement for a casing treatment of an axial flow compressor is disclosed. The method includes using the results from a three dimensional steady state computational fluid dynamic analysis to generate a flow field between a blade tip of a rotating blade and a compressor casing to determine the preferred circumferential groove arrangement. A stall margin for the axial flow compressor will be increased with the method.
摘要翻译：公开了一种用于确定用于轴流式压缩机的套管处理的优选圆周槽布置的方法。该方法包括使用来自三维稳态计算流体动力学分析的结果来产生旋转叶片的叶片尖端和压缩机壳体之间的流场，以确定优选的周向槽布置。随着该方法，轴流式压缩机的失速余量将增加。

17. 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。

18. 发明申请

US20110299979A1 Method for Improving the Stall Margin of an Axial Flow Compressor Using a Casing Treatment 有权
标题翻译：使用壳体处理改善轴流压缩机失速裕度的方法
公开(公告)号：US20110299979A1
公开(公告)日：2011-12-08
申请号：US12795781
申请日：2010-06-08
申请人： Matthew D. Montgomery
发明人： Matthew D. Montgomery
IPC分类号： F01D1/00
CPC分类号： F01D5/143 , F04D29/526 , F04D29/685 , F05D2240/11 , F05D2270/17
摘要： A method for determining a preferred circumferential groove arrangement for a casing treatment of an axial flow compressor is disclosed. The method includes using the results from a three dimensional steady state computational fluid dynamic analysis to generate a flow field between a blade tip of a rotating blade and a compressor casing to determine the preferred circumferential groove arrangement. A stall margin for the axial flow compressor will be increased with the method.
摘要翻译：公开了一种用于确定用于轴流式压缩机的套管处理的优选圆周槽布置的方法。该方法包括使用来自三维稳态计算流体动力学分析的结果来产生旋转叶片的叶片尖端和压缩机壳体之间的流场，以确定优选的周向槽布置。随着该方法，轴流式压缩机的失速余量将增加。

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