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1. 发明授权

US08317457B2 Method of operating a compressor 失效
标题翻译：操作压缩机的方法
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。

2. 发明申请

US20100284795A1 Plasma Clearance Controlled Compressor 审中-公开
标题翻译：等离子体间隙控制压缩机
公开(公告)号：US20100284795A1
公开(公告)日：2010-11-11
申请号：US11966309
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： F01D11/08
CPC分类号： F01D11/20 , F05D2270/172
摘要： A plasma leakage flow control system for a compressor is disclosed, comprising a circumferential row of compressor blades, an annular casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one annular plasma generator located on the annular casing. The annular plasma generator comprises an inner electrode and an outer electrode separated by a dielectric material. A gas turbine engine having a plasma leakage flow control system further comprises an engine control system which controls the operation of the annular plasma generator such that the blade tip leakage flow can be changed.
摘要翻译：公开了一种用于压缩机的等离子体泄漏流量控制系统，包括圆周排的压缩机叶片，围绕叶片尖端的环形壳体，位于与叶片的尖端径向分开的位置以及至少一个环形等离子体发生器，其位于环形套管。环形等离子体发生器包括由电介质材料隔开的内电极和外电极。具有等离子体泄漏流量控制系统的燃气涡轮发动机还包括发动机控制系统，其控制环形等离子体发生器的操作，使得可以改变叶片尖端泄漏流。

3. 发明申请

US20100284780A1 Method of Operating a Compressor 失效
标题翻译：操作压缩机的方法
公开(公告)号：US20100284780A1
公开(公告)日：2010-11-11
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： F01D11/08
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。

4. 发明申请

US20100047060A1 Plasma Enhanced Compressor 审中-公开
标题翻译：等离子增压压缩机
公开(公告)号：US20100047060A1
公开(公告)日：2010-02-25
申请号：US11966275
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： F02C9/16
CPC分类号： F04D29/526 , F05D2270/101 , F05D2270/172 , F15D1/12
摘要： A gas turbine engine is disclosed, comprising a compressor having a circumferential row of blades, a casing surrounding the tips of the blades, located radially apart from the tips of the blades and at least one plasma generator located on the casing. The plasma generator comprises a first electrode and a second electrode separated by a dielectric material. The gas turbine engine further comprises an engine control system which controls the operation of the plasma generator such that the stable operating range of the compressor is increased.
摘要翻译：公开了一种燃气涡轮发动机，其包括具有周向排的叶片的压缩机，围绕叶片的尖端的壳体，位于与叶片的尖端径向分开的位置以及位于壳体上的至少一个等离子体发生器。等离子体发生器包括由电介质材料隔开的第一电极和第二电极。燃气涡轮发动机还包括发动机控制系统，其控制等离子体发生器的操作，使得压缩机的稳定工作范围增加。

5. 发明授权

US08702398B2 High camber compressor rotor blade 有权
标题翻译：高外倾压缩机转子叶片
公开(公告)号：US08702398B2
公开(公告)日：2014-04-22
申请号：US13072027
申请日：2011-03-25
申请人： Andrew Breeze-Stringfellow , David Scott Clark , Brent F. Beacher
发明人： Andrew Breeze-Stringfellow , David Scott Clark , Brent F. Beacher
IPC分类号： F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , Y02T50/673
摘要： A rotor blade having an airfoil for a compressor is described. The airfoil has an airfoil root, an airfoil tip located at a spanwise distance from the airfoil root, a leading edge extending from the airfoil root to the airfoil tip, an inner span region (“S1”) between the airfoil root and a first height location on the airfoil leading edge, a midspan region (“S2”) between the first height location and a second height location on the airfoil leading edge located radially outward from the first height location; an outer span region (“S3”) between the second height location and the airfoil tip, wherein the airfoil has a normalized camber profile such that the normalized camber increases in the outer span region in a spanwise direction towards the tip and is more than 2.2 in the outer span region.
摘要翻译：描述了具有用于压缩机的翼型的转子叶片。所述翼型件具有翼型根部，所述翼型端部位于与所述翼型根的翼展距离处，从所述翼型根延伸到所述翼型端部的前缘，所述翼型根部与所述翼型根部之间的内部跨度区域（“S1”）在翼型前缘上的位置，位于第一高度位置与位于第一高度位置径向向外的翼型件前缘上的第二高度位置之间的中跨区域（“S2”）; 在第二高度位置和翼型尖端之间的外跨距区域（“S3”），其中翼型件具有归一化的弧形轮廓，使得归一化的外倾角在翼跨方向上朝向顶端的外跨距区域增加，并且大于2.2 在外跨区域。

6. 发明授权

US08684698B2 Compressor airfoil with tip dihedral 有权
标题翻译：压缩机翼型具有尖端二面体
公开(公告)号：US08684698B2
公开(公告)日：2014-04-01
申请号：US13071996
申请日：2011-03-25
申请人： Andrew Breeze-Stringfellow , David Scott Clark , Brent F. Beacher
发明人： Andrew Breeze-Stringfellow , David Scott Clark , Brent F. Beacher
IPC分类号： F01D5/12
CPC分类号： F04D29/324 , F01D5/141 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2250/71 , Y02T50/673
摘要： An airfoil for a compressor is described. The airfoil has a root, an airfoil tip, a leading edge, a trailing edge, airfoil pressure and suction sides extending between the leading edge and the trailing edge. The airfoil has an inner span region and an outer span region and the trailing edge has a dihedral profile such that the trailing edge dihedral angle decreases in at least a portion of the inner span region and the outer span region.
摘要翻译：描述了用于压缩机的翼型件。翼型件具有根部，翼型端头，前缘，后缘，在前缘和后缘之间延伸的翼型压力和吸力侧。翼型件具有内跨区域和外跨距区域，并且后缘具有双面轮廓，使得后缘二面角在内跨距区域和外跨距区域的至少一部分中减小。

7. 发明申请

US20120244005A1 HIGH CAMBER COMPRESSOR ROTOR BLADE 有权
标题翻译：高档压缩机转子叶片
公开(公告)号：US20120244005A1
公开(公告)日：2012-09-27
申请号：US13072027
申请日：2011-03-25
申请人： Andrew BREEZE-STRINGFELLOW , David Scott Clark , Brent F. Beacher
发明人： Andrew BREEZE-STRINGFELLOW , David Scott Clark , Brent F. Beacher
IPC分类号： F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , Y02T50/673
摘要： A rotor blade having an airfoil for a compressor is described. The airfoil has an airfoil root, an airfoil tip located at a spanwise distance from the airfoil root, a leading edge extending from the airfoil root to the airfoil tip, an inner span region (“S1”) between the airfoil root and a first height location on the airfoil leading edge, a midspan region (“S2”) between the first height location and a second height location on the airfoil leading edge located radially outward from the first height location; an outer span region (“S3”) between the second height location and the airfoil tip, wherein the airfoil has a normalized camber profile such that the normalized camber increases in the outer span region in a spanwise direction towards the tip and is more than 2.2 in the outer span region.
摘要翻译：描述了具有用于压缩机的翼型的转子叶片。所述翼型件具有翼型根部，所述翼型端部位于与所述翼型根的翼展距离处，从所述翼型根延伸到所述翼型端部的前缘，所述翼型根部与所述翼型根部之间的第一高度在翼型前缘上的位置，位于第一高度位置与位于第一高度位置径向向外的翼型件前缘上的第二高度位置之间的中跨区域（“S2”）; 在第二高度位置和翼型尖端之间的外跨距区域（“S3”），其中翼型件具有归一化的弧形轮廓，使得归一化的外倾角在翼跨方向上朝向顶端的外跨距区域增加，并且大于2.2 在外跨区域。

8. 发明授权

US08123471B2 Variable stator vane contoured button 有权
标题翻译：可变定子叶片轮廓按钮
公开(公告)号：US08123471B2
公开(公告)日：2012-02-28
申请号：US12401960
申请日：2009-03-11
申请人： Mark Joseph Mielke , Andrew Breeze-Stringfellow , David Scott Clark , James Edwin Rhoda , Gary Robert Peters
发明人： Mark Joseph Mielke , Andrew Breeze-Stringfellow , David Scott Clark , James Edwin Rhoda , Gary Robert Peters
IPC分类号： F01D17/12
CPC分类号： F01D17/162 , F04D29/563 , F05D2240/80 , F05D2250/711
摘要： A variable stator vane airfoil is mounted on a button centered about a rotational axis and includes circular leading and trailing edges circumscribed about the rotational axis at a button radius. Contoured pressure and suction sides extend from the circular leading edge to the circular trailing edge and are recessed inwardly from a perimeter circumscribed about the rotational axis at the button radius. One of upstream and downstream pressure side portions of the contoured pressure side is straight and another of the upstream and downstream pressure side portions is convexly curved. One of the upstream and downstream suction side portions is straight and another of the upstream and downstream suction side portions is convexly curved. One of the upstream pressure side portion and upstream suction side portion is straight and another of the upstream pressure side portion and upstream suction side portion is convexly curved.
摘要翻译：可变的定子叶片翼型件安装在围绕旋转轴线居中的按钮上，并且包括在按钮半径处围绕旋转轴线包围的圆形前缘和后缘。轮廓压力和吸力侧面从圆形前缘延伸到圆形后缘，并从按钮半径处围绕旋转轴线围绕的周边向内凹入。成型压力侧的上游侧压力侧部分和下游侧压力侧部分之一是直的，并且上游和下游压力侧部分中的另一个是凸形弯曲的。上游侧和下游侧吸入侧部分之一是直的，并且上游和下游吸入侧部分中的另一个是凸形弯曲的。上游侧压力侧部分和上游侧吸入侧部分之一是直的，上游侧压力侧部分和上游侧吸力侧部分中的另一个是凸形弯曲的。

9. 发明授权

US09074483B2 High camber stator vane 有权
标题翻译：高弧度定子叶片
公开(公告)号：US09074483B2
公开(公告)日：2015-07-07
申请号：US13072091
申请日：2011-03-25
申请人： Andrew Breeze-Stringfellow , David Scott Clark , Brent F. Beacher
发明人： Andrew Breeze-Stringfellow , David Scott Clark , Brent F. Beacher
IPC分类号： F01D9/00 , F01D5/14 , F04D29/54
CPC分类号： F01D5/148 , F01D5/141 , F04D29/544 , F05D2240/121 , F05D2240/303 , F05D2250/71 , Y02T50/671 , Y02T50/673
摘要： A stator vane for a compressor is described. The stator vane has an airfoil root, an airfoil tip, a leading edge, a trailing edge, an inner span region, a midspan region and an outer span region, wherein the stator vane has a normalized camber profile that increases in the outer span region in a spanwise direction towards the tip and is more than 1.4 in the outer span region.
摘要翻译：描述了用于压缩机的定子叶片。定子叶片具有翼型根部，翼型端头，前缘，后缘，内跨距，中跨区域和外跨距区域，其中定子叶片具有在外跨距区域中增加的归一化的弧形轮廓在朝向尖端的翼展方向上，并且在外跨度区域中大于1.4。

10. 发明申请

US20120243975A1 COMPRESSOR AIRFOIL WITH TIP DIHEDRAL 有权
标题翻译：压缩机空气与提示DIHEDRAL
公开(公告)号：US20120243975A1
公开(公告)日：2012-09-27
申请号：US13071996
申请日：2011-03-25
申请人： Andrew BREEZE-STRINGFELLOW , David Scott Clark , Brent F. Beacher
发明人： Andrew BREEZE-STRINGFELLOW , David Scott Clark , Brent F. Beacher
IPC分类号： F01D11/08 , F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2250/71 , Y02T50/673
摘要： An airfoil for a compressor is described. The airfoil has a root, an airfoil tip, a leading edge, a trailing edge, airfoil pressure and suction sides extending between the leading edge and the trailing edge. The airfoil has an inner span region and an outer span region and the trailing edge has a dihedral profile such that the trailing edge dihedral angle decreases in at least a portion of the inner span region and the outer span region.
摘要翻译：描述了用于压缩机的翼型件。翼型件具有根部，翼型端头，前缘，后缘，在前缘和后缘之间延伸的翼型压力和吸力侧。翼型件具有内跨区域和外跨距区域，并且后缘具有双面轮廓，使得后缘二面角在内跨距区域和外跨距区域的至少一部分中减小。

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