公开(公告)号：US07513737B2

公开(公告)日：2009-04-07

申请号：US11131200

申请日：2005-05-18

申请人： Stéphan Daux ,  Chantal Giot ,  Hugues Joubert ,  Benjamin Sauthier

发明人： Stéphan Daux ,  Chantal Giot ,  Hugues Joubert ,  Benjamin Sauthier

IPC分类号： B63H1/14

CPC分类号： F01D5/187 ,  F05D2260/2214

摘要： A blade for a turbomachine gas turbine, the blade having a cooling circuit comprising at least one cooling cavity with a high aspect ratio extending radially between a root and a tip of the blade, and at least one air admission opening at a radially inner end of the cavity to feed it with cooling air, at least one of the walls of the cooling cavity being provided with a plurality of indentations so as to disturb the flow of cooling air in said cavity and increase heat exchange.

摘要翻译： 一种用于涡轮机燃气轮机的叶片，所述叶片具有冷却回路，所述冷却回路包括至少一个冷却空腔，所述至少一个冷却腔具有在所述叶片的根部和所述尖端之间径向延伸的高纵横比，以及至少一个在所述叶片的径向内端的空气入口 所述腔体用冷却空气供给，所述冷却腔的壁中的至少一个设置有多个压痕，以便扰乱所述空腔中的冷却空气的流动并增加热交换。

公开(公告)号：US20050260076A1

公开(公告)日：2005-11-24

申请号：US11131200

申请日：2005-05-18

申请人： Stephan Daux ,  Chantal Giot ,  Hugues Joubert ,  Benjamin Sauthier

发明人： Stephan Daux ,  Chantal Giot ,  Hugues Joubert ,  Benjamin Sauthier

IPC分类号： F01D5/18 ,  F02C7/18 ,  B63H1/14

CPC分类号： F01D5/187 ,  F05D2260/2214

摘要： A blade for a turbomachine gas turbine, the blade having a cooling circuit comprising at least one cooling cavity with a high aspect ratio extending radially between a root and a tip of the blade, and at least one air admission opening at a radially inner end of the cavity to feed it with cooling air, at least one of the walls of the cooling cavity being provided with a plurality of indentations so as to disturb the flow of cooling air in said cavity and increase heat exchange.

摘要翻译： 一种用于涡轮机燃气轮机的叶片，所述叶片具有冷却回路，所述冷却回路包括至少一个冷却空腔，所述至少一个冷却腔具有在所述叶片的根部和所述尖端之间径向延伸的高纵横比，以及至少一个在所述叶片的径向内端的空气入口 所述腔体用冷却空气供给，所述冷却腔的壁中的至少一个设置有多个压痕，以便扰乱所述空腔中的冷却空气的流动并增加热交换。

公开(公告)号：US07214034B2

公开(公告)日：2007-05-08

申请号：US10514559

申请日：2003-05-28

申请人： Chantal Giot ,  Marc Marchi ,  Christian Gosselin ,  Eric Bil

发明人： Chantal Giot ,  Marc Marchi ,  Christian Gosselin ,  Eric Bil

IPC分类号： F01D11/00

CPC分类号： F01D5/3015 ,  F01D5/22 ,  F01D11/008 ,  F05D2240/55

摘要： A system for controlling a leakage zone under platforms of blades of a turbomachine blade-wheel by liners having edges that flare radially inwards, and that are disposed in inter-blade cavities defined by the platforms, by upstream and downstream radial walls of the blades and by the periphery of the wheel disk. One of the flared edges, upstream or downstream, presents an elastic zone bearing on an inclined surface of the adjacent radial wall relative to a radial plane, such that the liner tends to move axially towards the radial wall facing, under action of centrifugal forces, to improve sealing in the zone, and so that when the wheel stops, the elastic zone moves radially inwards, the liner pivoting around an axis distant from the elastic zone.

摘要翻译： 一种用于控制涡轮机叶片叶片平台下的泄漏区域的系统，其具有通过径向向内展开的边缘的边缘，并且由叶片的上游和下游径向壁设置在由平台限定的叶片间空腔内的叶片间空腔中， 通过轮盘的周边。 扩张边缘中的一个上游或下游具有相对于径向平面承载在相邻径向壁的倾斜表面上的弹性区域，使得在离心力的作用下，衬垫倾向于朝着径向壁轴向移动， 以改善区域中的密封，并且使得当轮停止时，弹性区域径向向内移动，衬套围绕远离弹性区域的轴线枢转。

公开(公告)号：US20070292271A1

公开(公告)日：2007-12-20

申请号：US11206156

申请日：2005-08-18

申请人： Eric Bil ,  Chantal Giot ,  Thomas Schlesinger

发明人： Eric Bil ,  Chantal Giot ,  Thomas Schlesinger

IPC分类号： F01D11/00

CPC分类号： F01D5/147 ,  F05D2240/80 ,  F05D2260/94 ,  F05D2260/941 ,  Y02T50/671

摘要： Rotor blade for a compressor or a gas turbine, in particular for a turbojet engine, comprising a suction side and a pressure side, which are joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases, a platform connecting the suction side and the pressure side to a blade root, and a stiffener formed beneath the downstream part of the platform and including at least one notch or a cut-away in line with the trailing edge, in order to reduce the stresses in the joint region between the aerofoil and the platform.

摘要翻译： 用于压缩机或燃气轮机的转子叶片，特别是用于涡轮喷气发动机的转子叶片，其包括吸入侧和压力侧，它们在其上游端由前缘并在其下游端由气体的后缘连接， 将吸入侧和压力侧连接到叶片根部的平台以及形成在平台的下游部分下方并且包括与后缘成一直线的至少一个切口或切口的加强件，以便减小应力 在机翼和平台之间的联合区域。

公开(公告)号：US20050175463A1

公开(公告)日：2005-08-11

申请号：US10514559

申请日：2003-05-28

申请人： Chantal Giot ,  Marc Marchi ,  Christian Gosselin ,  Eric Bil

发明人： Chantal Giot ,  Marc Marchi ,  Christian Gosselin ,  Eric Bil

IPC分类号： F01D1/00 ,  F01D5/22 ,  F01D11/00 ,  B63H1/26

CPC分类号： F01D5/3015 ,  F01D5/22 ,  F01D11/008 ,  F05D2240/55

摘要： A system for controlling a leakage zone under platforms of blades of a turbomachine blade-wheel by liners having edges that flare radially inwards, and that are disposed in inter-blade cavities defined by the platforms, by upstream and downstream radial walls of the blades and by the periphery of the wheel disk. One of the flared edges, upstream or downstream, presents an elastic zone bearing on an inclined surface of the adjacent radial wall relative to a radial plane, such that the liner tends to move axially towards the radial wall facing, under action of centrifugal forces, to improve sealing in the zone, and so that when the wheel stops, the elastic zone moves radially inwards, the liner pivoting around an axis distant from the elastic zone.

摘要翻译： 一种用于控制涡轮机叶片叶片平台下的泄漏区域的系统，其具有通过径向向内展开的边缘的边缘，并且由叶片的上游和下游径向壁设置在由平台限定的叶片间空腔内的叶片间空腔中， 通过轮盘的周边。 扩张边缘中的一个上游或下游具有相对于径向平面承载在相邻径向壁的倾斜表面上的弹性区域，使得在离心力的作用下，衬垫倾向于朝着径向壁轴向移动， 以改善区域中的密封，并且使得当轮停止时，弹性区域径向向内移动，衬套围绕远离弹性区域的轴线枢转。

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。