公开(公告)号：US20060257257A1

公开(公告)日：2006-11-16

申请号：US11382415

申请日：2006-05-09

申请人： Pascal Deschamps ,  Chantal Giot ,  Thomas Potier

发明人： Pascal Deschamps ,  Chantal Giot ,  Thomas Potier

IPC分类号： F01D5/18

CPC分类号： F01D5/20

摘要： The invention relates to a hollow blade having an internal cooling passage, an open cavity situated at the free end of the blade and defined by an end wall extending over the entire end of the blade and by a rim, and cooling channels connecting said internal cooling passage and the outside face of the pressure side wall. In characteristic manner, the pressure side wall presenting a projecting end portion whose outside face is inclined relative to the outside face of the pressure side wall, and said cooling channels being disposed in said end portion, being parallel to the outside face of said end portion so that they open out into the tip of said end portion towards the free end of the blade. The blade is applicable to a high pressure turbine without a heel.

摘要翻译： 叶片具有由端壁和沿着吸力侧壁在前缘和后缘之间延伸的边缘限定的空腔。 连接内部冷却通道和压力侧壁的外表面的冷却通道（32）相对于压力壁倾斜。 压壁具有相对于压壁外表面倾斜的突出端部。 端部的末端位于端壁的外表面（26b）中，使得通道向腔室前方的压力壁开口。

公开(公告)号：US07661930B2

公开(公告)日：2010-02-16

申请号：US11562726

申请日：2006-11-22

申请人： Pascal Deschamps ,  Patrice Eneau ,  Thomas Potier

发明人： Pascal Deschamps ,  Patrice Eneau ,  Thomas Potier

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/202 ,  F05D2260/22141

摘要： A moving blade for a turbomachine with a central portion that is geometrically subdivided into four adjacent pressure-side zones disposed on the pressure side of the blade, and into four adjacent suction-side zones disposed on the suction side of the blade, the pressure-side and suction-side zones being distributed on either side of the skeleton of the blade, and the blade including in its central portion a pressure-side cooling circuit and a suction-side cooling circuit, the pressure-side cooling circuit including three radial cavities occupying three adjacent pressure-side zones, and the suction-side cooling circuit including three radial cavities occupying the four suction-side zones and the remaining pressure-side zone.

摘要翻译： 一种用于涡轮机的移动叶片，其中心部分几何地分为设置在叶片的压力侧上的四个相邻的压力侧区域，并且设置在设置在叶片的吸力侧上的四个相邻的吸入侧区域中， 侧面和吸入侧分布在叶片的骨架的两侧，并且叶片在其中心部分包​​括压力侧冷却回路和吸入侧冷却回路，该压力侧冷却回路包括三个径向空腔 占据三个相邻的压力侧区域，吸入侧冷却回路包括占据四个吸入侧区域和剩余压力侧区域的三个径向空腔。

公开(公告)号：US20070122282A1

公开(公告)日：2007-05-31

申请号：US11562726

申请日：2006-11-22

申请人： Pascal Deschamps ,  Patrice Eneau ,  Thomas Potier

发明人： Pascal Deschamps ,  Patrice Eneau ,  Thomas Potier

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/202 ,  F05D2260/22141

摘要： The invention relates to moving blade for a turbomachine. The central portion of the blade is geometrically subdivided into four adjacent pressure-side zones disposed on the pressure side of the blade, and into four adjacent suction-side zones disposed on the suction side of the blade, the pressure-side and suction-side zones being distributed on either side of the skeleton of the blade, and the blade including in its central portion a pressure-side cooling circuit and a suction-side cooling circuit, the pressure-side cooling circuit comprising three radial cavities occupying three adjacent pressure-side zones, and the suction-side cooling circuit comprising three radial cavities occupying the four suction-side zones and the remaining pressure-side zone.

摘要翻译： 本发明涉及用于涡轮机的移动叶片。 叶片的中心部分几何地被分为设置在叶片的压力侧的四个相邻的压力侧区域，并且设置在设置在叶片的吸入侧上的四个相邻的吸入侧区域中，压力侧和吸入侧 区域分布在叶片的骨架的任一侧，并且叶片在其中心部分包​​括压力侧冷却回路和吸入侧冷却回路，该压力侧冷却回路包括三个径向空腔， 并且吸入侧冷却回路包括占据四个吸入侧区域和剩余压力侧区域的三个径向空腔。

公开(公告)号：US07351035B2

公开(公告)日：2008-04-01

申请号：US11382415

申请日：2006-05-09

申请人： Pascal Deschamps ,  Chantal Gisele Giot ,  Thomas Potier

发明人： Pascal Deschamps ,  Chantal Gisele Giot ,  Thomas Potier

IPC分类号： F01D5/20

CPC分类号： F01D5/20

摘要： A hollow blade has an internal cooling passage, an open cavity situated at the free end of the blade and defined by an end wall extending over the entire end of the blade and by a rim. The blade includes cooling channels connecting the internal cooling passage and the outside face of the pressure side wall. The pressure side wall presents a projecting end portion whose outside face is inclined relative to the outside face of the pressure side wall. The cooling channels are disposed in the end portion, being parallel to the outside face of the end portion so that they open out into the tip of the end portion towards the free end of the blade.

摘要翻译： 中空叶片具有内部冷却通道，位于叶片自由端的开放空腔，由在叶片的整个端部和边缘延伸的端壁限定。 叶片包括连接内部冷却通道和压力侧壁的外表面的冷却通道。 压力侧壁具有突出端部，其外表面相对于压力侧壁的外表面倾斜。 冷却通道设置在端部中，平行于端部的外表面，使得它们朝向叶片的自由端打开到端部的末端。

公开(公告)号：US20070212228A1

公开(公告)日：2007-09-13

申请号：US11682517

申请日：2007-03-06

申请人： Sebastien Digard Brou De Cuissart ,  Chantal Gisele Giot ,  Thomas Potier

发明人： Sebastien Digard Brou De Cuissart ,  Chantal Gisele Giot ,  Thomas Potier

IPC分类号： F01D5/18

CPC分类号： F01D5/082 ,  F01D5/187 ,  F01D5/3007

摘要： A moving blade for a turbomachine, the blade comprising an aerodynamic surface extending radially between a blade root and a blade tip, and at least one internal cooling circuit made up of at least one radial cavity, at least one air admission opening formed in the blade root and opening out into the cavity(ies), and a plurality of outlet orifices opening out from the cavity(ies) and leading to the outside of the blade, the blade root having lower swellings and upper swellings defining bearing surfaces for fastening the blade to a rotor disk. The air admission openings of the cooling circuit(s) open out into a common cavity that is formed in the blade root and that extends radially from the base of the blade root at least as far as the upper swelling of said root.

摘要翻译： 一种用于涡轮机的移动叶片，所述叶片包括在叶片根部和叶片尖端之间径向延伸的空气动力学表面，以及由至少一个径向空腔构成的至少一个内部冷却回路，形成在叶片中的至少一个进气口 根部并且打开到空腔中，以及从腔体开口并通向叶片外部的多个出口孔，叶片根部具有较小的膨胀和上部隆起，形成用于紧固叶片的支承表面 到转子盘。 冷却回路的进气口开口形成在叶片根部中的共同的空腔中，并且从叶片根部的基部径向延伸至少与所述根部的上部肿胀一致。

公开(公告)号：US07972115B2

公开(公告)日：2011-07-05

申请号：US11870614

申请日：2007-10-11

申请人： Thomas Potier

发明人： Thomas Potier

IPC分类号： F01D5/14

CPC分类号： F01D5/20 ,  F01D11/10 ,  F05D2240/55 ,  F05D2250/184 ,  F05D2250/611 ,  F05D2250/70

摘要： A turbomachine moving blade without a top platform, the blade including a fastener root (110) surmounted by an airfoil (112) that presents an end face (114), a pressure-side face (116), and a suction-side face, said fastener root and said end face being situated respectively at bottom and top ends of the blade that are spaced apart along the main axis (A) of the blade. The airfoil presents a projecting edge defined between a portion (124) of its end face and a top portion (122) of its pressure-side face, these portions forming between each other a mean edge angle that is strictly less than 90°. The top portion (122) of the pressure-side face is corrugated, and in a section plane perpendicular to the main axis of the blade, it follows an outline formed by an alternating succession of concave curves (129) and convex curves (131).

摘要翻译： 一种没有顶部平台的涡轮机械动叶片，该叶片包括一个紧固件根部110，该紧固件根部110由端面114，压力侧面116和吸力侧面114构成， 所述紧固件根部和所述端面分别位于叶片的沿着叶片的主轴线（A）间隔开的底部和顶端。 机翼具有限定在其端面的部分（124）和其压力侧面的顶部（122）之间的突出边缘，这些部分彼此之间形成严格小于90°的平均边缘角。 压力侧面的顶部部分（122）是波纹形的，并且在垂直于叶片主轴线的截面中，它遵循由交替连续的凹曲线（129）和凸曲线（131）形成的轮廓， 。