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公开(公告)号：US08348592B2
公开(公告)日：2013-01-08
申请号：US11966473
申请日：2007-12-28
IPC分类号： F01D17/20
CPC分类号： F04D27/02 , F01D5/145 , F04D29/687 , F05D2270/172 , Y02T50/673
摘要： An instability mitigation system is disclosed, comprising a rotor having a row of blades arranged around a centerline axis, and a mitigation system comprising at least one plasma actuator mounted on a blade that facilitates the improvement of the stability of the rotor, and a control system for controlling the operation of the mitigation system. An instability mitigation system further comprising a detection system for detecting an onset of an instability in a rotor and a control system for controlling the detection system and the mitigation system are disclosed.
摘要翻译： 公开了一种不稳定性减轻系统，其包括具有围绕中心线轴线布置的一排叶片的转子，以及减轻系统，包括安装在叶片上的至少一个等离子体致动器，其有助于提高转子的稳定性;以及控制系统 用于控制缓解系统的运行。 公开了一种不稳定性缓解系统，还包括用于检测转子不稳定性的检测系统和用于控制检测系统和缓解系统的控制系统。
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公开(公告)号：US07819626B2
公开(公告)日：2010-10-26
申请号：US11580789
申请日：2006-10-13
CPC分类号： F01D11/20 , F05D2270/172 , Y02T50/671 , Y10S415/914
摘要： A gas turbine engine plasma blade tip clearance control system includes an annular shroud surrounding rotatable blade tips and an annular plasma generator spaced radially outwardly and apart from the blade tips. An exemplary embodiment of the annular plasma generator is mounted to the annular shroud and includes radially inner and outer electrodes separated by a dielectric material disposed within an annular groove in a radially inwardly facing surface of the annular shroud. The plasma generator is operable for producing an annular plasma between the annular shroud and blade tips and an effective clearance produced by the annular plasma between the annular shroud and blade tips that is smaller than a clearance between the annular shroud and blade tips.
摘要翻译： 燃气涡轮发动机等离子体叶片顶端间隙控制系统包括围绕可旋转叶片尖端的环形护罩和沿径向向外并与叶片尖端分开的环形等离子体发生器。 环形等离子体发生器的示例性实施例安装到环形护罩，并且包括径向内部和外部电极，该电极由设置在环形护罩的径向向内的表面中的环形槽内的电介质材料隔开。 等离子体发生器可操作用于在环形护罩和叶片尖端之间产生环形等离子体，以及由环形护罩和叶片尖端之间的环形等离子体产生的有效间隙小于环形罩和叶片尖端之间的间隙。
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公开(公告)号：US20090169367A1
公开(公告)日：2009-07-02
申请号：US11966532
申请日：2007-12-28
CPC分类号： F02K3/06 , F04D29/687 , F05D2270/172
摘要： An instability mitigation system is disclosed, comprising a stator stage located axially proximate to a rotor, the stator stage having a row of a plurality of stator vanes arranged around a centerline axis, and a mitigation system comprising at least one plasma actuator mounted on the stator vane that facilitates the improvement of the stability of the rotor, and a control system for controlling the operation of the mitigation system. An instability mitigation system further comprising a detection system for detecting an onset of an instability in a rotor and a control system for controlling the detection system and the mitigation system are disclosed.
摘要翻译： 公开了一种不稳定性缓解系统，其包括定位在轴向上靠近转子的台阶，定子台具有围绕中心线轴线布置的多排定子叶片的排，以及包括至少一个安装在定子上的等离子体致动器 有助于提高转子稳定性的叶片，以及用于控制缓解系统运行的控制系统。 公开了一种不稳定性缓解系统，还包括用于检测转子不稳定性的检测系统和用于控制检测系统和缓解系统的控制系统。
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公开(公告)号：US20090169363A1
公开(公告)日：2009-07-02
申请号：US11966503
申请日：2007-12-28
CPC分类号： F04D27/001 , F04D27/02 , F04D29/526 , F05D2270/101 , F05D2270/172
摘要： A compression system is disclosed, the compression system comprising a stator stage having a row of a plurality of stator vanes arranged around a centerline axis, each stator vane having a vane airfoil and at least one plasma actuator located on the stator stage. Exemplary embodiments of a detection system for detecting an instability in a compression system rotor and a mitigation system that facilitates the improvement of the stability of the rotor are disclosed.
摘要翻译： 公开了一种压缩系统，该压缩系统包括定子级，该定子级具有围绕中心线轴线布置的多列定子叶片的排，每个定子叶片具有叶片翼型件和位于定子平台上的至少一个等离子体致动器。 公开了一种用于检测压缩系统转子中的不稳定性的检测系统的示例性实施例和有助于提高转子稳定性的缓解系统。
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公开(公告)号：US20090155088A1
公开(公告)日：2009-06-18
申请号：US11494378
申请日：2006-07-27
申请人： Ching-Pang Lee , Tingfan Pang , Brian Alan Norton , Jan Christopher Schilling , Aspi Rustom Wadia
发明人： Ching-Pang Lee , Tingfan Pang , Brian Alan Norton , Jan Christopher Schilling , Aspi Rustom Wadia
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/20 , F05D2240/122 , F05D2240/304 , F05D2240/307 , F05D2250/185 , F05D2260/20 , F05D2260/202 , F05D2260/2212 , F05D2260/607 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A hollow turbine airfoil includes a tip cap bounding an internal cooling circuit between opposite pressure and suction sidewalls. The tip cap includes an internal dome surrounding a dust hole, and the dome is inclined inwardly toward the airfoil root both transversely between the opposite sidewalls and chordally between opposite leading and trailing edges of the airfoil.
摘要翻译： 中空涡轮机翼型件包括在相对的压力侧壁和抽吸侧壁之间限定内部冷却回路的顶盖。 顶盖包括围绕灰尘孔的内部圆顶，并且圆顶向外朝向翼型根部横向地在相对的侧壁之间向上倾斜，并且在翼型的相对的前缘和后缘之间弦向地倾斜。
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公开(公告)号：US20080145233A1
公开(公告)日：2008-06-19
申请号：US11639878
申请日：2006-12-15
CPC分类号： F01D5/147 , F01D5/145 , F01D9/041 , F05D2240/122 , F05D2240/304 , F05D2270/172 , Y02T50/673 , Y10S415/914
摘要： A trailing edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction, one or more spanwise extending plasma generators in a trailing edge region around a trailing edge of the airfoil. The plasma generators may be mounted on an outer wall of the airfoil with first and second pluralities of the plasma generators on pressure and suction sides of the airfoil respectively. The plasma generators may include inner and outer electrodes separated by a dielectric material disposed within a grooves in an outer hot surface of the outer wall of the airfoil. The plasma generators may be located at an aft end of the airfoil and the inner electrodes flush with the trailing edge base. A method for operating the system includes energizing one or more of plasma generators in steady state or unsteady modes.
摘要翻译： 后缘涡流减少系统包括在翼展方向上延伸的燃气涡轮发动机翼型件，在翼型件的后缘周围的后缘区域中的一个或多个翼展方向延伸的等离子体发生器。 等离子体发生器可以分别安装在机翼的外壁上，其中第一和第二多个等离子体发生器分别在翼型的压力和吸力侧。 等离子体发生器可以包括由设置在翼型件的外壁的外部热表面中的凹槽内的介电材料隔开的内部和外部电极。 等离子体发生器可以位于翼型的后端，并且内部电极与后缘基座齐平。 用于操作该系统的方法包括给稳态或不稳定模式中的一个或多个等离子体发生器通电。
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公开(公告)号：US20080145210A1
公开(公告)日：2008-06-19
申请号：US11639876
申请日：2006-12-15
IPC分类号： F01D5/18
CPC分类号： F01D5/145 , F01D5/143 , F01D5/186 , F01D5/187 , F01D9/041 , F01D9/065 , F04D29/681 , F05D2240/121 , F05D2240/303 , F05D2260/202 , F05D2270/17 , F05D2270/172 , Y02T50/673 , Y02T50/676 , Y10S415/914
摘要： A leading edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction away from an end wall, one or more plasma generators extending in the spanwise direction through a fillet between the airfoil and the end wall in a leading edge region near and around a leading edge of the airfoil and near the fillet. The plasma generators being operable for producing a plasma extending over a portion of the fillet in the leading edge region. The plasma generators may be mounted on an outer wall of the airfoil with a first portion of the plasma generators on a pressure side of the airfoil and a second portion of the plasma generators on a suction side of the airfoil. A method for operating the system includes energizing one or more plasma generators to form the plasma in steady state or unsteady modes.
摘要翻译： 前缘涡流减少系统包括沿翼展方向远离端壁延伸的燃气涡轮发动机翼型件，一个或多个等离子体发生器，其在翼展方向上延伸通过翼型件和端壁之间的圆角， 围绕机翼的前缘，靠近圆角。 等离子体发生器可操作用于产生在前缘区域中的圆角的一部分上延伸的等离子体。 等离子体发生器可以安装在翼型件的外壁上，其中等离子体发生器的第一部分在翼型的压力侧，等离子体发生器的第二部分在翼型的吸力侧。 用于操作该系统的方法包括激励一个或多个等离子体发生器以形成处于稳定状态或不稳定模式的等离子体。
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公开(公告)号：US07320575B2
公开(公告)日：2008-01-22
申请号：US10952184
申请日：2004-09-28
申请人： Aspi Rustom Wadia , Peter Nicholas Szucs , Syed Arif Khalid , Peter John Wood , Kevin R. Kirtley , Xiaoyue Liu
发明人： Aspi Rustom Wadia , Peter Nicholas Szucs , Syed Arif Khalid , Peter John Wood , Kevin R. Kirtley , Xiaoyue Liu
IPC分类号： B63H1/14
CPC分类号： F04D21/00 , F04D29/682 , F04D29/684
摘要： An airfoil having a root, a tip, and an outer surface for pressuring air flowable thereover. The outer surface includes one or more slots elongate in a direction selected to preclude or reduce circulation within the slots, and the one or more slots are configured to bleed a boundary layer from the outer surface to the tip utilizing one or more passageways within the airfoil.
摘要翻译： 具有根部，尖端和外表面的翼型件，用于对其中可流动的空气进行加压。 外表面包括一个或多个狭槽，所述狭槽在被选择为排除或减少槽内的循环的方向上延伸，并且所述一个或多个狭槽构造成利用翼型内的一个或多个通道将边界层从外表面流向尖端 。
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公开(公告)号：US07293961B2
公开(公告)日：2007-11-13
申请号：US11294218
申请日：2005-12-05
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/121 , F05D2240/303 , F05D2250/185 , F05D2260/201 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A turbine airfoil includes pressure and suction sidewalls spaced apart to define flow channels extending in span and separated by ribs. Side channels are disposed along one sidewall and spaced from the opposite sidewall by the ribs, and a mid channel bridges the sidewalls. The side and mid channels are arranged in a zigzag serpentine cooling circuit alternating therebetween for transferring heat from the sidewall into the mid channel.
摘要翻译： 涡轮机翼片包括间隔开的压力和抽吸侧壁，以限定在跨度中延伸并由肋分隔的流动通道。 侧通道沿着一个侧壁设置并且通过肋与相对侧壁间隔开，并且中间通道桥接侧壁。 侧通道和中间通道以锯齿形蛇形冷却回路布置，用于将热量从侧壁传送到中间通道。
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公开(公告)号：US08317457B2
公开(公告)日：2012-11-27
申请号：US11966348
申请日：2007-12-28
申请人： Aspi Rustom Wadia , David Scott Clark , Ching-Pang Lee , Andrew Breeze-Stringfellow , Gregory Scott McNulty
发明人： Aspi Rustom Wadia , David Scott Clark , Ching-Pang Lee , Andrew Breeze-Stringfellow , Gregory Scott McNulty
IPC分类号： F01D11/20
CPC分类号： F04D27/02 , F04D27/001 , F04D29/526 , F04D29/687 , F05D2270/101 , F05D2270/172
摘要： A method of operating a compressor having a row of blades for preventing a compressor stall is disclosed, the method comprising the steps of mounting a plasma generator in a casing or a shroud radially outwardly and apart from the blade tips wherein the plasma generator comprises a radially inner electrode and a radially outer electrode separated by a dielectric material; and supplying an AC potential to the radially inner electrode and the radially outer electrode.
摘要翻译： 公开了一种操作具有用于防止压缩机失速的一排叶片的压缩机的方法，所述方法包括以下步骤：将等离子体发生器沿径向向外并且与叶片尖端分开地安装在壳体或护罩中，其中等离子体发生器包括径向 内部电极和由电介质材料隔开的径向外部电极; 并向所述径向内部电极和所述径向外部电极提供AC电位。
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