公开(公告)号：US20110189023A1

公开(公告)日：2011-08-04

申请号：US12919722

申请日：2009-02-27

申请人： Jean-Michel Guimbard ,  Olivier Kueny ,  Ludovic Pintat

发明人： Jean-Michel Guimbard ,  Olivier Kueny ,  Ludovic Pintat

IPC分类号： F01D5/14

CPC分类号： F01D5/145 ,  F01D5/143 ,  F05D2240/80 ,  F05D2250/70 ,  Y02T50/673

摘要： A blade for a turbomachine impeller including an airfoil, and at least one platform at one of the ends of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring around a ring axis. In the blade, a suction surface profile at the surface of the platform and along the suction surface has a first recessed part located axially in an upstream half of the airfoil and a first boss-like part located axially downstream of the first recessed part. Due to this configuration, efficiency of the blade is improved.

摘要翻译： 一种用于涡轮机叶轮的叶片，其包括翼型件，以及在所述翼型件的一端处的至少一个平台，所述叶片构造成布置有多个基本上相同的叶片，以便围绕环轴线形成环。 在叶片中，平台表面和抽吸表面处的吸力表面轮廓具有轴向位于翼型的上游半部中的第一凹部和位于第一凹部的轴向下游的第一凸起状部分。 由于这种结构，刀片的效率提高。

公开(公告)号：US08734113B2

公开(公告)日：2014-05-27

申请号：US13171561

申请日：2011-06-29

申请人： Patrick Girard ,  Olivier Kueny ,  Renaud Martet ,  Renaud Royan

发明人： Patrick Girard ,  Olivier Kueny ,  Renaud Martet ,  Renaud Royan

IPC分类号： F01D9/02 ,  F01D9/04

CPC分类号： F01D5/141 ,  F01D9/041 ,  F05D2220/321 ,  F05D2220/3215 ,  F05D2240/121 ,  F05D2240/303 ,  Y02T50/673

摘要： When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

摘要翻译： 当冷和处于非涂覆状态时，空气动力学特性与由表1中给出的笛卡尔坐标X，Y，Z'确定的标称轮廓基本相同，其中坐标Z'是商D / H，其中D 是从位于标称轮廓底部的第一参考平面P0考虑的点的距离，H是从第一参考平面测量到第二参考平面P1的所述剖面的高度。 测量D和H相对于涡轮机的轴线径向地获得，而X坐标是在涡轮的轴向方向上测量的。

公开(公告)号：US08757983B2

公开(公告)日：2014-06-24

申请号：US13171586

申请日：2011-06-29

申请人： Patrick Girard ,  Olivier Kueny ,  Pierre Marche ,  Ludovic Pintat

发明人： Patrick Girard ,  Olivier Kueny ,  Pierre Marche ,  Ludovic Pintat

IPC分类号： F01D5/14

CPC分类号： F01D5/142 ,  F01D5/141 ,  Y02T50/673

摘要： When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

摘要翻译： 当冷和处于非涂覆状态时，空气动力学特性与由表1中给出的笛卡尔坐标X，Y，Z'确定的标称轮廓基本相同，其中坐标Z'是商D / H，其中D 是从位于标称轮廓底部的第一参考平面P0考虑的点的距离，H是从第一参考平面测量到第二参考平面P1的所述剖面的高度。 测量D和H相对于涡轮机的轴线径向地获得，而X坐标是在涡轮的轴向方向上测量的。

公开(公告)号：US08647066B2

公开(公告)日：2014-02-11

申请号：US12919722

申请日：2009-02-27

申请人： Jean-Michel Guimbard ,  Olivier Kueny ,  Ludovic Pintat

发明人： Jean-Michel Guimbard ,  Olivier Kueny ,  Ludovic Pintat

IPC分类号： F01D5/14

CPC分类号： F01D5/145 ,  F01D5/143 ,  F05D2240/80 ,  F05D2250/70 ,  Y02T50/673

摘要： A blade for a turbomachine impeller including an airfoil, and at least one platform at one of the ends of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring around a ring axis. In the blade, a suction surface profile at the surface of the platform and along the suction surface has a first recessed part located axially in an upstream half of the airfoil and a first boss-like part located axially downstream of the first recessed part. Due to this configuration, efficiency of the blade is improved.

摘要翻译： 一种用于涡轮机叶轮的叶片，其包括翼型件，以及在所述翼型件的一端处的至少一个平台，所述叶片构造成布置有多个基本上相同的叶片，以便围绕环轴线形成环。 在叶片中，平台表面和抽吸表面处的吸力表面轮廓具有轴向位于翼型的上游半部中的第一凹部和位于第一凹部的轴向下游的第一凸起状部分。 由于这种结构，刀片的效率提高。

公开(公告)号：US20120051932A1

公开(公告)日：2012-03-01

申请号：US13171758

申请日：2011-06-29

申请人： Patrick GIRARD ,  Olivier Kueny ,  Ludovic Pintat ,  Pascal Routier

发明人： Patrick GIRARD ,  Olivier Kueny ,  Ludovic Pintat ,  Pascal Routier

IPC分类号： F01D5/14

CPC分类号： F01D5/141 ,  F01D5/225 ,  F05D2250/74 ,  Y02T50/673

摘要： When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

摘要翻译： 当冷和处于非涂覆状态时，空气动力学特性与由表1中给出的笛卡尔坐标X，Y，Z'确定的标称轮廓基本相同，其中坐标Z'是商D / H，其中D 是从位于标称轮廓底部的第一参考平面P0考虑的点的距离，H是从第一参考平面测量到第二参考平面P1的所述剖面的高度。 测量D和H相对于涡轮机的轴线径向地获得，而X坐标是在涡轮的轴向方向上测量的。

公开(公告)号：US20090155062A1

公开(公告)日：2009-06-18

申请号：US12329142

申请日：2008-12-05

申请人： Jean-Michel Bernard GUIMBARD ,  Olivier Kueny ,  Eric Schwartz

发明人： Jean-Michel Bernard GUIMBARD ,  Olivier Kueny ,  Eric Schwartz

IPC分类号： F01D1/02 ,  F01D9/04 ,  F01D5/14

CPC分类号： F01D5/142 ,  F01D5/141 ,  F01D9/041 ,  Y02T50/673

摘要： A method of designing a multistage turbine for a turbomachine in which each turbine stage comprises a stator row and a rotor row each made up of an annular row of airfoils, wherein, for all of the stator or rotor rows, it consists in simultaneously modifying the shapes of the airfoils of said rows to straighten out the wakes from the trailing edges of said airfoils, then in angularly positioning the rows in such a manner that the wakes from the airfoils of the stator (or rotor) airfoils impact against the leading edges of the stator (or rotor, respectively) airfoils of the rows situated downstream, in order to achieve multistage aerodynamic coupling simultaneously over the turbine as a whole.

摘要翻译： 一种设计用于涡轮机的多级涡轮机的方法，其中每个涡轮级包括定子排和转子排，每个涡轮机由一排环形翼片组成，其中，对于所有的定子或转子排，它同时修改 所述排的翼型的形状用于从所述翼型件的后缘拉平所述擦拭物，然后以这样的方式成角度地定位所述排，使得来自所述定子（或转子）翼型件的翼片的冲击抵靠所述翼型件的前缘 位于下游的行的定子（或转子，分别）翼型，以便在整个涡轮机上同时实现多级空气动力学耦合。

公开(公告)号：US20120070298A1

公开(公告)日：2012-03-22

申请号：US13171586

申请日：2011-06-29

申请人： Patrick GIRARD ,  Olivier Kueny ,  Pierre Marche ,  Ludovic Pintat

发明人： Patrick GIRARD ,  Olivier Kueny ,  Pierre Marche ,  Ludovic Pintat

IPC分类号： F01D5/14

CPC分类号： F01D5/142 ,  F01D5/141 ,  Y02T50/673

摘要： When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

摘要翻译： 当冷和处于非涂覆状态时，空气动力学特性与由表1中给出的笛卡尔坐标X，Y，Z'确定的标称轮廓基本相同，其中坐标Z'是商D / H，其中D 是从位于标称轮廓底部的第一参考平面P0考虑的点的距离，H是从第一参考平面测量到第二参考平面P1的所述剖面的高度。 测量D和H相对于涡轮机的轴线径向地获得，而X坐标是在涡轮的轴向方向上测量的。

公开(公告)号：US20110110788A1

公开(公告)日：2011-05-12

申请号：US12919781

申请日：2009-02-27

申请人： Jean-Michel Guimbard ,  Olivier Kueny ,  Ludovic Pintat

发明人： Jean-Michel Guimbard ,  Olivier Kueny ,  Ludovic Pintat

IPC分类号： F01D5/14

CPC分类号： F01D5/143 ,  F01D5/145 ,  F01D5/225 ,  F05D2240/80 ,  F05D2250/70 ,  Y02T50/673

摘要： A blade for a turbomachine impeller including an airfoil, and a platform extending at one of the ends of the airfoil in a direction globally perpendicular to a longitudinal direction of the airfoil, the blade configured, together with other identical blades, to form a ring around a ring axis, with the adjacent blade platforms joining in pairs so as to form an inter-airfoil surface linking the pressure surface of one airfoil to the suction surface of the neighboring airfoil. In this blade, the inter-airfoil surface includes, in an upstream half of the airfoil, a boss located closer to the pressure surface than to the suction surface, and a recessed passage located between the same and the suction surface.

摘要翻译： 一种用于涡轮机叶轮的叶片，其包括翼型件，以及在翼型件的一端处在与翼型件的纵向方向全局垂直的方向上延伸的平台，该叶片与其它相同的叶片一起形成围绕 环形轴线，其中相邻的叶片平台成对地接合，以便形成将一个翼型件的压力表面连接到相邻翼型件的吸力表面的翼间表面。 在该叶片中，翼型间表面在机翼的上游一半中包括位于比压力表面更接近压力表面的凸台，以及位于其与吸力表面之间的凹入通道。

公开(公告)号：US09004865B2

公开(公告)日：2015-04-14

申请号：US12919798

申请日：2009-02-27

申请人： Jean-Michel Guimbard ,  Olivier Kueny ,  Ludovic Pintat

发明人： Jean-Michel Guimbard ,  Olivier Kueny ,  Ludovic Pintat

IPC分类号： F01D5/18 ,  F04D29/38 ,  F01D5/14

CPC分类号： F01D5/143 ,  F01D5/145 ,  F05D2240/80 ,  F05D2250/70 ,  Y02T50/673 ,  Y10S416/02

摘要： A blade for a turbomachine impeller including an airfoil and at least one platform at one end of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring, the platform surface having a suction surface profile and a pressure surface profile respectively along the suction surface and the pressure surface. In the blade, the pressure surface profile including a pressure surface recessed part is located axially in an upstream half of the airfoil. Due to this configuration, efficiency of the blade is improved.

摘要翻译： 一种用于涡轮机叶轮的叶片，其包括翼型件和在翼型件的一端处的至少一个平台，所述叶片构造成布置有多个基本相同的叶片以形成环，所述平台表面具有吸力表面轮廓和 分别沿着吸力表面和压力表面的压力表面轮廓。 在叶片中，包括压力表面凹陷部分的压力表面轮廓轴向位于翼型的上游一半中。 由于这种结构，刀片的效率提高。

公开(公告)号：US08647069B2

公开(公告)日：2014-02-11

申请号：US13171758

申请日：2011-06-29

申请人： Patrick Girard ,  Olivier Kueny ,  Ludovic Pintat ,  Pascal Routier

发明人： Patrick Girard ,  Olivier Kueny ,  Ludovic Pintat ,  Pascal Routier

IPC分类号： F01D5/14 ,  B64C27/46

CPC分类号： F01D5/141 ,  F01D5/225 ,  F05D2250/74 ,  Y02T50/673

摘要： When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z′ given in Table 1, in which the coordinate Z′ is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.

摘要翻译： 当冷和处于非涂覆状态时，空气动力学特性与由表1中给出的笛卡尔坐标X，Y，Z'确定的标称轮廓基本相同，其中坐标Z'是商D / H，其中D 是从位于标称轮廓底部的第一参考平面P0考虑的点的距离，H是从第一参考平面测量到第二参考平面P1的所述剖面的高度。 测量D和H相对于涡轮机的轴线径向地获得，而X坐标是在涡轮的轴向方向上测量的。