公开(公告)号：US08172516B2

公开(公告)日：2012-05-08

申请号：US11999875

申请日：2007-12-07

申请人： John Frederick Parker ,  David Luck ,  David H. Brown

发明人： John Frederick Parker ,  David Luck ,  David H. Brown

IPC分类号： F01D17/14

CPC分类号： F01D17/143 ,  F01D17/167 ,  F05D2220/40

摘要： A variable geometry turbine comprises a turbine wheel (9) supported in a housing (1) for rotation about an axis. A nozzle ring (5) is moveably mounted within a cavity (19) provided within the housing for adjustment of the width of an annular inlet passageway (4) extending radially inwards towards the turbine wheel (9). An array of inlet guide vanes (8) extends between a radial face of the nozzle ring (5) and an opposing wall of the inlet (4) defining a radial vane passage. A first circumferential array of apertures (25) is provided through the radial face, each of which lies substantially within the vane passage. A second circumferential array of apertures (24) is also provided in said radial face, each of lies substantially upstream or downstream of the first array (25) of apertures. The inlet (4) and cavity (19) are in fluid communication via both the first and second sets of apertures (25,24).

摘要翻译： 可变几何涡轮机包括支撑在壳体（1）中以围绕轴线旋转的涡轮机叶轮（9）。 喷嘴环（5）可移动地安装在设置在壳体内的空腔（19）内，用于调节径向向内朝向涡轮机叶轮（9）延伸的环形入口通道（4）的宽度。 入口导向叶片（8）的阵列在喷嘴环（5）的径向面和入口（4）的相对的壁之间延伸，限定出径向叶片通道。 第一圆周阵列的孔（25）设置穿过径向面，每个基本上位于叶片通道内。 第二圆周阵列的孔（24）也设置在所述径向面中，每个位于基本上在第一阵列（25）孔的上游或下游。 入口（4）和空腔（19）经由第一和第二组孔（25,24）流体连通。

公开(公告)号：US20080089782A1

公开(公告)日：2008-04-17

申请号：US11999875

申请日：2007-12-07

申请人： John Parker ,  David Luck ,  David Brown

发明人： John Parker ,  David Luck ,  David Brown

IPC分类号： F04D29/56

CPC分类号： F01D17/143 ,  F01D17/167 ,  F05D2220/40

摘要： A variable geometry turbine comprises a turbine wheel (9) supported in a housing (1) for rotation about an axis. A nozzle ring (5) is moveably mounted within a cavity (19) provided within the housing for adjustment of the width of an annular inlet passageway (4) extending radially inwards towards the turbine wheel (9). An array of inlet guide vanes (8) extends between a radial face of the nozzle ring (5) and an opposing wall of the inlet (4) defining a radial vane passage. A first circumferential array of apertures (25) is provided through the radial face, each of which lies substantially within the vane passage. A second circumferential array of apertures (24) is also provided in said radial face, each of lies substantially upstream or downstream of the first array (25) of apertures. The inlet (4) and cavity (19) are in fluid communication via both the first and second sets of apertures (25,24).

摘要翻译： 可变几何涡轮机包括支撑在壳体（1）中以围绕轴线旋转的涡轮机叶轮（9）。 喷嘴环（5）可移动地安装在设置在壳体内的空腔（19）内，用于调节径向向内朝向涡轮机叶轮（9）延伸的环形入口通道（4）的宽度。 入口导向叶片（8）的阵列在喷嘴环（5）的径向面和入口（4）的相对的壁之间延伸，限定出径向叶片通道。 第一圆周阵列的孔（25）设置穿过径向面，每个基本上位于叶片通道内。 第二圆周阵列的孔（24）也设置在所述径向面中，每个位于基本上在第一阵列（25）孔的上游或下游。 入口（4）和空腔（19）经由第一和第二组孔（25,24）流体连通。