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13 条记录 (耗时 0.034 秒)

    Air-cooled component
    1.
    发明授权
    Air-cooled component 有权
    风冷部件

    公开(公告)号：US08011890B2

    公开(公告)日：2011-09-06

    申请号：US11976296

    申请日：2007-10-23

    申请人： Sean A. Walters ,  Kevin P. Self ,  Brian G. Cooper

    发明人： Sean A. Walters ,  Kevin P. Self ,  Brian G. Cooper

    IPC分类号： F01D11/00

    CPC分类号： F01D5/186 ,  F05D2250/18 ,  F05D2250/33 ,  F05D2260/202

    摘要： An air-cooled component such as a turbine stator vane, has a row of cooling passages extending from the interior of the vane to the exterior. The passages are inclined to a plane perpendicular to the row. The angle of inclination of each passage varies with the position of the passage along the row. The arrangement assists in avoiding local overheating of the vane surface.

    摘要翻译： 诸如涡轮机定子叶片的风冷部件具有从叶片的内部延伸到外部的一排冷却通道。 通道倾斜于与行垂直的平面。 每个通道的倾斜角随着沿着行的通道的位置而变化。 该装置有助于避免叶片表面的局部过热。

    Air-cooled component
    2.
    发明申请
    Air-cooled component 有权
    风冷部件

    公开(公告)号：US20080131284A1

    公开(公告)日：2008-06-05

    申请号：US11976296

    申请日：2007-10-23

    申请人： Sean A. Walters ,  Kevin P. Self ,  Brian G. Cooper

    发明人： Sean A. Walters ,  Kevin P. Self ,  Brian G. Cooper

    IPC分类号： F01D5/18

    CPC分类号： F01D5/186 ,  F05D2250/18 ,  F05D2250/33 ,  F05D2260/202

    摘要： An air-cooled component such as a turbine stator vane, has a row of cooling passages 8 extending from the interior 4 of the vane to the exterior. The passages 8 are inclined to a plane perpendicular to the row. The angle of inclination of each passage 8 varies with the position of the passage 8 along the row. The arrangement assists in avoiding local overheating of the vane surface.

    摘要翻译： 诸如涡轮机定子叶片的风冷部件具有从叶片的内部4延伸到外部的一排冷却通道8。 通道8相对于垂直于该行的平面倾斜。 每个通道8的倾斜角随着通道8沿着排的位置而变化。 该装置有助于避免叶片表面的局部过热。

    Cooled aerofoil blade
    3.
    发明授权
    Cooled aerofoil blade 失效
    冷却的AEROFOIL叶片

    公开(公告)号：US5073086A

    公开(公告)日：1991-12-17

    申请号：US717502

    申请日：1991-06-19

    申请人： Brian G. Cooper

    发明人： Brian G. Cooper

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187

    摘要： A gas turbine engine turbine aerofoil blade includes an aerofoil portion having pressure and suction flanks. The flanks are internally interconnected by wall member which cooperates with the flanks to define first and second cooling passage portions which are interconnected by a bend portion. The wall member is locally thickened adjacent the bend portion. In the second cooling passage portion the locally thickened wall member portion progressively increases in thickness towards at least one of the flanks so as to eliminate any acute angle between the flanks and the thickened wall member portion adjacent thereto.

    摘要翻译： 燃气涡轮发动机涡轮机翼型叶片包括具有压力和吸力侧面的机翼部分。 侧壁通过壁构件内部互连，壁构件与侧面配合以限定通过弯曲部分互连的第一和第二冷却通道部分。 壁构件在弯曲部分附近局部加厚。 在第二冷却通道部分中，局部加厚的壁构件部分朝着至少一个侧面逐渐增加厚度，以消除侧面和与其相邻的加厚壁构件部分之间的任何锐角。

    Cooling air cooled gas turbine aerofoil
    4.
    发明授权
    Cooling air cooled gas turbine aerofoil 失效
    冷却风冷式燃气轮机机翼

    公开(公告)号：US5507621A

    公开(公告)日：1996-04-16

    申请号：US380715

    申请日：1995-01-30

    申请人： Brian G. Cooper

    发明人： Brian G. Cooper

    IPC分类号： F01D5/18

    CPC分类号： F01D5/187 ,  F05D2260/221

    摘要： A gas turbine engine is provided with turbine stators which have hollow aerofoils. The aerofoils are internally cooled by a flow of air the path of which is defined by walls. The wall has a curved deflector at its outer end which causes air to flow over the wall end and down the other side of the wall. An extension member ensures that the air does not break away from the surface of the wall and is preferably made from sheet metal so as to provide a light, easily made structure.

    摘要翻译： 燃气涡轮发动机设置有具有中空翼型的涡轮机定子。 机翼在内部被空气流冷却，其中路径由壁限定。 该壁在其外端具有弯曲的偏转器，这导致空气在壁的另一侧壁端部和下方流动。 延伸构件确保空气不会从壁的表面脱离，并且优选地由金属板制成，以便提供轻便且易于制造的结构。

    Vane apparatus for a gas turbine engine
    5.
    发明授权
    Vane apparatus for a gas turbine engine 有权
    燃气轮机的叶片装置

    公开(公告)号：US07179047B2

    公开(公告)日：2007-02-20

    申请号：US10919391

    申请日：2004-08-17

    申请人： Brian G Cooper

    发明人： Brian G Cooper

    IPC分类号： F01D9/06

    CPC分类号： F01D5/187 ,  F01D9/041 ,  F05D2260/607

    摘要： A vane assembly for a gas turbine engine, the vane assembly comprising an aerodynamic main body across which gas can flow in streamlines, the main body defining a chamber and a plurality of cooling apertures extending through the main body, the cooling apertures being arranged in a plurality of arrays, wherein the vane assembly is arrangeable so that each array is generally parallel to the streamlines, and the vane assembly further including a baffle arrangement provided in the chamber the baffle arrangement having a gas deflection surface which extends across a plurality of the arrays.

    摘要翻译： 一种用于燃气涡轮发动机的叶片组件，所述叶片组件包括空气动力学主体，气体可以流过其中流动，所述主体限定腔室和多个延伸穿过所述主体的冷却孔，所述冷却孔布置在 多个阵列，其中所述叶片组件可布置成使得每个阵列大致平行于所述流线，并且所述叶片组件还包括设置在所述腔室中的挡板装置，所述挡板装置具有气体偏转表面，所述气体偏转表面延伸跨越多个阵列 。

    Closely coupled exhaust aftertreatment system for a turbocharged engine
    6.
    发明授权
    Closely coupled exhaust aftertreatment system for a turbocharged engine 有权
    涡轮增压发动机紧密排气后处理系统

    公开(公告)号：US08312708B2

    公开(公告)日：2012-11-20

    申请号：US12750231

    申请日：2010-03-30

    申请人： David Bennet ,  Brian G. Cooper ,  Huntly W. Thomas ,  Nick Winder

    发明人： David Bennet ,  Brian G. Cooper ,  Huntly W. Thomas ,  Nick Winder

    IPC分类号： F01N5/04 ,  F01N3/00 ,  F01N3/02 ,  F01N3/10

    CPC分类号： F01N3/035 ,  F01N3/2066 ,  F01N13/0097 ,  F01N13/02 ,  Y02A50/2325 ,  Y02T10/16 ,  Y02T10/24

    摘要： A closely-coupled exhaust aftertreatment system includes a first exhaust conduit comprising a first valve operable between a first position promoting an exhaust flow within the first exhaust conduit to an inlet of a first oxidation catalyst and a second position promoting the exhaust gas flow within a second exhaust conduit. It also includes a third exhaust conduit fluidly coupled to an outlet of the OC and comprising a second valve operable between a first position promoting an exhaust flow within the third exhaust conduit to an inlet of a particulate filter (PF) and a second position promoting the exhaust gas flow through a fourth exhaust conduit to an inlet in the second exhaust conduit. It further includes a turbocharger fluidly coupled to the second exhaust conduit downstream of the inlet and a selective catalyst reduction (SCR) catalyst that is located downstream of the turbocharger and upstream of the PF.

    摘要翻译： 紧密耦合的排气后处理系统包括第一排气管道，其包括第一阀，其可在促使第一排气管道内的排气流与第一氧化催化剂的入口之间的第一位置和在第二排气管道的第二位置内促进废气流的第二位置 排气管。 它还包括流体地联接到OC的出口的第三排气管，并且包括第二阀，其可操作在第一位置和第二位置之间，该第一位置在第三排气管道内的排气流与微粒过滤器（PF）的入口之间， 排气通过第四排气管道流到第二排气管道中的入口。 它还包括流体耦合到入口下游的第二排气导管的涡轮增压器和位于涡轮增压器下游和PF上游的选择性催化剂还原（SCR）催化剂。

    CLOSELY COUPLED EXHAUST AFTERTREATMENT SYSTEM FOR A TURBOCHARGED ENGINE
    7.
    发明申请
    CLOSELY COUPLED EXHAUST AFTERTREATMENT SYSTEM FOR A TURBOCHARGED ENGINE 有权
    用于涡轮发动机的闭式联合排气后处理系统

    公开(公告)号：US20110239646A1

    公开(公告)日：2011-10-06

    申请号：US12750231

    申请日：2010-03-30

    申请人： David Bennet ,  Brian G. Cooper ,  Huntly W. Thomas ,  Nick Winder

    发明人： David Bennet ,  Brian G. Cooper ,  Huntly W. Thomas ,  Nick Winder

    IPC分类号： F02B33/44 ,  F01N9/00 ,  F01N3/035 ,  F01N3/10 ,  F01N5/04 ,  F01N5/02

    CPC分类号： F01N3/035 ,  F01N3/2066 ,  F01N13/0097 ,  F01N13/02 ,  Y02A50/2325 ,  Y02T10/16 ,  Y02T10/24

    摘要： A closely-coupled exhaust aftertreatment system includes a first exhaust conduit comprising a first valve operable between a first position promoting an exhaust flow within the first exhaust conduit to an inlet of a first oxidation catalyst and a second position promoting the exhaust gas flow within a second exhaust conduit. It also includes a third exhaust conduit fluidly coupled to an outlet of the OC and comprising a second valve operable between a first position promoting an exhaust flow within the third exhaust conduit to an inlet of a particulate filter (PF) and a second position promoting the exhaust gas flow through a fourth exhaust conduit to an inlet in the second exhaust conduit. It further includes a turbocharger fluidly coupled to the second exhaust conduit downstream of the inlet and a selective catalyst reduction (SCR) catalyst that is located downstream of the turbocharger and upstream of the PF.

    摘要翻译： 紧密耦合的排气后处理系统包括第一排气管道，其包括第一阀，其可在促使第一排气管道内的排气流与第一氧化催化剂的入口之间的第一位置和在第二排气管道的第二位置内促进废气流的第二位置 排气管。 它还包括流体地联接到OC的出口的第三排气管，并且包括第二阀，其可操作在第一位置和第二位置之间，该第一位置在第三排气管道内的排气流与微粒过滤器（PF）的入口之间， 排气通过第四排气管道流到第二排气管道中的入口。 它还包括流体耦合到入口下游的第二排气导管的涡轮增压器和位于涡轮增压器下游和PF上游的选择性催化剂还原（SCR）催化剂。

    Cooled gas turbine engine aerofoil
    8.
    发明授权
    Cooled gas turbine engine aerofoil 失效
    冷却气体涡轮发动机AEROFOIL

    公开(公告)号：US5193975A

    公开(公告)日：1993-03-16

    申请号：US650233

    申请日：1991-02-04

    申请人： Jonathan G. Bird ,  Brian G. Cooper

    发明人： Jonathan G. Bird ,  Brian G. Cooper

    IPC分类号： F01D5/18

    CPC分类号： F01D5/186 ,  F01D5/189

    摘要： The present invention relates to cooled gas turbine engine aerofoils particularly for turbine stator vanes or tubine rotor blades. The leading edge region of a hollow aerofoil is provided with rows of cooling air passages, which are arranged, in operation, to direct cooling air in the opposite direction to the local flow of the hot gas stream. The cooling air passages are substantially parallel, and have relatively large diameters to reduce the possibility of blockage of the cooling air passages by sand. An air guide tube in the hollow aerofoil is provided with large apertures at its leading edge to minimize the area for sand to adhere to.

    摘要翻译： 本发明涉及特别用于涡轮机定子叶片或者转子叶片的冷却燃气涡轮发动机翼型。 中空机翼的前缘区域设置有一排冷却空气通道，其在操作中被布置成沿与热气流的局部流动相反的方向引导冷却空气。 冷却空气通道基本平行，并且具有相对较大的直径以减少通过沙子堵塞冷却空气通道的可能性。 空心翼面中的空气引导管在其前缘设有大孔，以使沙子粘附的面积最小化。