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1.发明申请OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE VANE, IN PARTICULAR FOR A NOZZLE OF THE THIRD STAGE OF A TURBINE 有权用于涡轮风扇的优化航空配置文件，特别是用于涡轮机第三阶段的喷嘴公开(公告)号：US20120020800A1
公开(公告)日：2012-01-26
申请号：US13170239
申请日：2011-06-28
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , 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。
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2.发明申请OPTIMIZED AERODYNAMIC PROFILE FOR A TURBINE BLADE, IN PARTICULAR FOR A ROTARY WHEEL OF THE SECOND STAGE OF A TURBINE 有权用于涡轮叶片的优化航空轮廓，特别是用于涡轮机第二阶段的旋转轮公开(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。
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公开(公告)号：US20110110788A1
公开(公告)日：2011-05-12
申请号：US12919781
申请日：2009-02-27
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。
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公开(公告)号：US09004865B2
公开(公告)日：2015-04-14
申请号：US12919798
申请日：2009-02-27
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。
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5.发明授权Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the fourth stage of a turbine 有权优化用于涡轮机叶片的空气动力学特性，特别是用于涡轮机第四级的旋转轮公开(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
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。
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公开(公告)号：US20110014056A1
公开(公告)日：2011-01-20
申请号：US12919798
申请日：2009-02-27
IPC分类号： 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。
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7.发明授权Optimized aerodynamic profile for a turbine vane, in particular for a nozzle of the third stage of a turbine 有权用于涡轮叶片的优化的空气动力学特性，特别是用于涡轮机第三级的喷嘴公开(公告)号：US08757968B2
公开(公告)日：2014-06-24
申请号：US13170239
申请日：2011-06-28
IPC分类号： F01D9/04
CPC分类号： F01D5/141 , 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 the 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 是从位于标称轮廓的底部的第一参考平面P0考虑的点的距离，H是从第一参考平面到第二参考平面P1测量的轮廓的高度。 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。
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8.发明申请公开(公告)号：US20110189023A1
公开(公告)日：2011-08-04
申请号：US12919722
申请日：2009-02-27
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。
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9.发明授权Optimized aerodynamic profile for a turbine blade, in particular for a rotary wheel of the second stage of a turbine 有权涡轮机叶片的优化的空气动力学特性，特别是用于涡轮机第二级的转轮公开(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。
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10.发明授权公开(公告)号：US08647066B2
公开(公告)日：2014-02-11
申请号：US12919722
申请日：2009-02-27
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。
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