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1.发明申请公开(公告)号：US20130312385A1
公开(公告)日：2013-11-28
申请号：US13480120
申请日：2012-05-24
CPC分类号： F01D9/041 , F02C7/04 , F05D2270/172
摘要： A gas turbine system having a plasma actuator flow control arrangement including a compressor section for compressing an airstream, wherein the compressor section includes at least one inlet guide vane for controlling the airstream proximate an inlet portion of the compressor section. Also included is a turbine inlet assembly for ingesting the airstream to be routed to the compressor section. Further included is a plasma actuator disposed within at least one of the inlet portion of the compressor section and the turbine inlet assembly for controllably producing an electric field to manipulate a portion of the airstream.
摘要翻译： 一种具有等离子体致动器流量控制装置的燃气涡轮机系统，其包括用于压缩空气流的压缩机部分，其中所述压缩机部分包括用于控制靠近所述压缩机部分的入口部分的所述气流的至少一个入口引导叶片。 还包括用于摄取要路由到压缩机部分的气流的涡轮机入口组件。 进一步包括设置在压缩机部分的入口部分和涡轮机入口组件中的至少一个中的等离子体致动器，用于可控地产生电场以操纵气流的一部分。
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2.发明申请Method And System For Providing A Splitter To Improve The Recovery Of Compressor Discharge Casing 有权提供分流器的方法和系统，以提高压缩机排气套管的回收率公开(公告)号：US20110252804A1
公开(公告)日：2011-10-20
申请号：US12761073
申请日：2010-04-15
CPC分类号： F01D9/023 , F01D25/24 , F02C3/14 , F02C3/145 , F05D2240/12 , F05D2240/126 , F05D2240/35 , F05D2250/33 , F05D2250/712 , F23R3/04 , F23R3/46
摘要： A splitter is provided for improving a pressure recovery of a compressor discharge casing (CDC) by substantially aligning a fluid vortex about a longitudinal axis of a gas turbine engine. The CDC includes an annular wall that extends generally axially along at least a portion of the CDC. The CDC is configured to house a first combustor and a second combustor. The splitter extends from the annular wall between the first and second combustors. The splitter includes a first surface that is configured to direct fluid towards the first combustor and a second surface that is configured to direct fluid towards the second combustor.
摘要翻译： 提供了一种分流器，用于通过围绕燃气涡轮发动机的纵向轴线大致对准流体涡流来改善压缩机排放壳体（CDC）的压力恢复。 CDC包括沿着CDC的至少一部分大致轴向延伸的环形壁。 CDC构造成容纳第一燃烧器和第二燃烧器。 分流器从第一和第二燃烧器之间的环形壁延伸。 分流器包括构造成将流体引向第一燃烧器的第一表面和被构造成将流体引向第二燃烧器的第二表面。
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公开(公告)号：US20090297339A1
公开(公告)日：2009-12-03
申请号：US12129280
申请日：2008-05-29
IPC分类号： F01D17/14
CPC分类号： F04D25/16 , F01D9/02 , F02C9/18 , F04D25/04 , F05D2220/3216
摘要： A turbomachine includes a compressor and an ejector. The ejector includes at least one nozzle having a first end portion that extends to a second end portion defining a flow region. The second end portion includes a variable outlet for controlling an airflow from the compressor.
摘要翻译： 涡轮机包括压缩机和喷射器。 喷射器包括至少一个喷嘴，其具有延伸到限定流动区域的第二端部的第一端部部分。 第二端部包括用于控制来自压缩机的气流的可变出口。
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公开(公告)号：US20100239418A1
公开(公告)日：2010-09-23
申请号：US12407525
申请日：2009-03-19
IPC分类号： F01D9/00
CPC分类号： F01D9/04 , F02C3/14 , F04D29/547 , F05D2240/12 , F05D2250/52 , F23R3/60
摘要： A diffuser for a turbine engine, including an annular casing to seal compressor discharge air and struts attached to the casing to delimit an annular array of intra-strut regions, is provided and includes a ring portion, including a ring shaped annular body with a forward face disposed on a forward side thereof, the ring portion being supportable by one or more of the struts, and a splitter portion, including a ring shaped annular body with an aft face disposed on an aft side thereof to mate with the forward face of the ring portion body, the splitter portion further including a lead edge, on a forward side of the splitter portion body, which is extendable into a flow path of the compressor discharge air to split the flow path into secondary flow paths defined radially outside of and inside of the splitter portion body.
摘要翻译： 一种用于涡轮发动机的扩散器，包括用于密封压缩机排出空气的环形壳体和附接到壳体的支柱以限定支柱内区域的环形阵列，并且包括环部分，其包括环形环形体，其具有向前 所述环形部分可由一个或多个所述支柱支撑，所述分隔部分包括环形环形体，所述环形环体具有设置在其后侧上的后表面， 环形部分主体，分离器部分还包括引导边缘，位于分离器部分主体的前侧，其可延伸到压缩机排出空气的流动路径中，以将流动路径分成径向地在外部和内部限定的二次流动路径 的分离器部分主体。
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公开(公告)号：US20100068045A1
公开(公告)日：2010-03-18
申请号：US12209416
申请日：2008-09-12
CPC分类号： F01D17/162 , F01D9/04 , F05D2250/74
摘要： An inlet guide vane having a nominal profile substantially in accordance with Cartesian coordinate values of x, y, and z set forth in TABLE 1 reduces vibration of engine components at various operating conditions. A scaling factor can be applied to the values to make the airfoil larger or smaller. The TABLE 1 x and y values are distances in inches within a tolerance which, when connected by smooth curves, define airfoil profile sections at each distance z in inches, the profile sections being joined smoothly to form a complete airfoil shape. The tolerance in an embodiment is up to about 0.16 inches.
摘要翻译： 具有基本上根据表1所示的x，y和z的笛卡尔坐标值的标称轮廓的入口导叶减少了各种操作条件下的发动机部件的振动。 可以对这些值应用比例因子以使翼型件变大或变小。 表1 x和y值是公差范围内的英寸间距，当通过平滑曲线连接时，以每英寸为单位定义每个距离z的翼型轮廓部分，轮廓部分平滑连接以形成完整的翼型形状。 实施例中的公差达到约0.16英寸。
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6.发明授权公开(公告)号：US08474270B2
公开(公告)日：2013-07-02
申请号：US13396930
申请日：2012-02-15
申请人： Carl Gerard Schott , Kevin W. Kinzie , John Joseph Lynch , David W. Ball , Gunnar Leif Siden , Kenneth Neil Whaling
发明人： Carl Gerard Schott , Kevin W. Kinzie , John Joseph Lynch , David W. Ball , Gunnar Leif Siden , Kenneth Neil Whaling
CPC分类号： F02K1/386 , B01J2208/00106 , B01J2208/00442 , B01J2219/00247 , F04F5/46 , F04F5/54 , Y10T29/494
摘要： A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.
摘要翻译： 提供了一种组装喷射器的方法，其中所述方法包括提供具有中心线轴线的动力喷嘴尖端，并且包括具有延伸穿过基本上垂直于中心线轴线的平面的至少一个突起的喷嘴尖端边缘。 该方法还包括将动力喷嘴尖端连接到喷射器。
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公开(公告)号：US08133017B2
公开(公告)日：2012-03-13
申请号：US12407525
申请日：2009-03-19
IPC分类号： F01D25/30
CPC分类号： F01D9/04 , F02C3/14 , F04D29/547 , F05D2240/12 , F05D2250/52 , F23R3/60
摘要： A diffuser for a turbine engine, including an annular casing to seal compressor discharge air and struts attached to the casing to delimit an annular array of intra-strut regions, is provided and includes a ring portion, including a ring shaped annular body with a forward face disposed on a forward side thereof, the ring portion being supportable by one or more of the struts, and a splitter portion, including a ring shaped annular body with an aft face disposed on an aft side thereof to mate with the forward face of the ring portion body, the splitter portion further including a lead edge, on a forward side of the splitter portion body, which is extendable into a flow path of the compressor discharge air to split the flow path into secondary flow paths defined radially outside of and inside of the splitter portion body.
摘要翻译： 一种用于涡轮发动机的扩散器，包括用于密封压缩机排出空气的环形壳体和附接到壳体的支柱以限定支柱内区域的环形阵列，并且包括环部分，其包括环形环形体，其具有向前 所述环形部分可由一个或多个所述支柱支撑，所述分隔部分包括环形环形体，所述环形环体具有设置在其后侧上的后表面， 环形部分主体，分离器部分还包括引导边缘，位于分离器部分主体的前侧，其可延伸到压缩机排出空气的流动路径中，以将流动路径分成径向地在外部和内部限定的二次流动路径 的分离器部分主体。
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公开(公告)号：US07985053B2
公开(公告)日：2011-07-26
申请号：US12209416
申请日：2008-09-12
IPC分类号： F01D9/02
CPC分类号： F01D17/162 , F01D9/04 , F05D2250/74
摘要： An inlet guide vane having a nominal profile substantially in accordance with Cartesian coordinate values of x, y, and z set forth in TABLE 1 reduces vibration of engine components at various operating conditions. A scaling factor can be applied to the values to make the airfoil larger or smaller. The TABLE 1 x and y values are distances in inches within a tolerance which, when connected by smooth curves, define airfoil profile sections at each distance z in inches, the profile sections being joined smoothly to form a complete airfoil shape. The tolerance in an embodiment is up to about 0.16 inches.
摘要翻译： 具有基本上根据表1所示的x，y和z的笛卡尔坐标值的标称轮廓的入口导叶减少了各种操作条件下的发动机部件的振动。 可以对这些值应用比例因子以使翼型件变大或变小。 表1 x和y值是公差范围内的英寸间距，当通过平滑曲线连接时，以每英寸为单位定义每个距离z的翼型轮廓部分，轮廓部分平滑连接以形成完整的翼型形状。 实施例中的公差达到约0.16英寸。
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9.发明授权Method and system for providing a splitter to improve the recovery of compressor discharge casing 有权提供分流器以提高压缩机排气套管回收率的方法和系统公开(公告)号：US08276390B2
公开(公告)日：2012-10-02
申请号：US12761073
申请日：2010-04-15
IPC分类号： F02C1/00
CPC分类号： F01D9/023 , F01D25/24 , F02C3/14 , F02C3/145 , F05D2240/12 , F05D2240/126 , F05D2240/35 , F05D2250/33 , F05D2250/712 , F23R3/04 , F23R3/46
摘要： A splitter is provided for improving a pressure recovery of a compressor discharge casing (CDC) by substantially aligning a fluid vortex about a longitudinal axis of a gas turbine engine. The CDC includes an annular wall that extends generally axially along at least a portion of the CDC. The CDC is configured to house a first combustor and a second combustor. The splitter extends from the annular wall between the first and second combustors. The splitter includes a first surface that is configured to direct fluid towards the first combustor and a second surface that is configured to direct fluid towards the second combustor.
摘要翻译： 提供了一种分流器，用于通过围绕燃气涡轮发动机的纵向轴线大致对准流体涡流来改善压缩机排放壳体（CDC）的压力恢复。 CDC包括沿着CDC的至少一部分大致轴向延伸的环形壁。 CDC构造成容纳第一燃烧器和第二燃烧器。 分流器从第一和第二燃烧器之间的环形壁延伸。 分流器包括构造成将流体引向第一燃烧器的第一表面和被构造成将流体引向第二燃烧器的第二表面。
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10.发明申请公开(公告)号：US20120137704A1
公开(公告)日：2012-06-07
申请号：US13396930
申请日：2012-02-15
申请人： Carl Gerard Schott , Kevin W. Kinzie , John Joseph Lynch , David W. Ball , Gunnar Leif Siden , Kenneth Neil Whaling
发明人： Carl Gerard Schott , Kevin W. Kinzie , John Joseph Lynch , David W. Ball , Gunnar Leif Siden , Kenneth Neil Whaling
CPC分类号： F02K1/386 , B01J2208/00106 , B01J2208/00442 , B01J2219/00247 , F04F5/46 , F04F5/54 , Y10T29/494
摘要： A method of assembling an ejector is provided, wherein the method includes providing a motive nozzle tip having a centerline axis and including a nozzle tip edge having at least one protrusion extending through a plane substantially normal to the centerline axis. The method also includes coupling the motive nozzle tip to the ejector.
摘要翻译： 提供了一种组装喷射器的方法，其中所述方法包括提供具有中心线轴线的动力喷嘴尖端，并且包括具有延伸穿过基本上垂直于中心线轴线的平面的至少一个突起的喷嘴尖端边缘。 该方法还包括将动力喷嘴尖端连接到喷射器。
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