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1. 发明授权

US09827610B2 Method for producing a rotor vane for a turbomachine 有权
公开(公告)号：US09827610B2
公开(公告)日：2017-11-28
申请号：US14771785
申请日：2014-03-04
申请人： SNECMA
发明人： Guillaume Klein , Josserand Bassery , Sebastien Congratel , Raphael Dupeyre , David Mathieu , Ba-Phuc Tang
IPC分类号： B22D25/02 , B22C9/22 , F01D5/22 , F01D9/02 , F01D11/08 , B23P15/02
CPC分类号： B22D25/02 , B22C9/22 , B23P15/02 , F01D5/225 , F01D9/02 , F01D11/08 , F05D2240/12 , F05D2240/55
摘要： A method for producing a rotor vane (10) for a turbomachine, including producing a rough casting, the heel of which has a downstream lip (121) with a transverse increased thickness (130) such that the lip has an upstream surface (134) substantially parallel to an axis The method further includes machining said increased thickness so that the downstream lip has an upstream surface (138) inclined in relation to the axis.

2. 发明申请

US20160016227A1 METHOD FOR PRODUCING A ROTOR VANE FOR A TURBOMACHINE 有权
标题翻译：用于生产涡轮转子的转子叶片的方法
公开(公告)号：US20160016227A1
公开(公告)日：2016-01-21
申请号：US14771785
申请日：2014-03-04
申请人： SNECMA
发明人： Guillaume Klein , Josserand Bassery , Sebastien Congratel , Raphael Dupeyre , David Mathieu , Ba-Phuc Tang
IPC分类号： B22D25/02 , F01D11/08 , B22C9/22 , F01D9/02
CPC分类号： B22D25/02 , B22C9/22 , B23P15/02 , F01D5/225 , F01D9/02 , F01D11/08 , F05D2240/12 , F05D2240/55
摘要： The invention relates to a method for producing a rotor vane (10) for a turbomachine, comprising a step consisting in producing a rough casting, the heel of which has a downstream lip (121) with a transverse increased thickness (130) such that the lip has an upstream surface (134) substantially parallel to the above-mentioned axis, said method comprising an additional step of machining said increased thickness so that the downstream lip has an upstream surface (138) inclined in relation to the above-mentioned axis.
摘要翻译：本发明涉及一种用于制造用于涡轮机的转子叶片（10）的方法，包括一个步骤，该步骤包括制造粗铸件，其后端具有横向增加的厚度（130）的下游唇缘（121），使得唇部具有基本上平行于上述轴线的上游表面（134），所述方法包括加工所述增加的厚度以使下游唇缘具有相对于上述轴线倾斜的上游表面（138）的附加步骤。

3. 发明授权

US09833834B2 Turbine engine blade preform 有权
公开(公告)号：US09833834B2
公开(公告)日：2017-12-05
申请号：US14895777
申请日：2014-06-04
申请人： Snecma
发明人： Sébastien Serge Francis Congratel , Raphaël Jean Philippe Dupeyre , Guillaume Klein , David Mathieu , Ba-Phuc Tang
IPC分类号： B22C9/06 , B22C9/10 , B22C9/22 , B22D25/02 , F01D5/14
CPC分类号： B22C9/10 , B22C9/06 , B22C9/22 , B22D25/02 , F01D5/141 , F05D2230/21 , F05D2230/61
摘要： A blade preform includes a strut connecting a plat-form to a blade root portion extending longitudinally in an upstream-downstream direction, an upstream web and a downstream web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut. The upstream and downstream webs connect the upstream and downstream ends of the plat-form to the upstream and downstream ends of the blade root. The blade root extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that of the upstream and downstream webs and the side edges of each web are extended by walls that converge at the flanks of the blade root.

4. 发明授权

US09567861B2 Turbomachine vane cooperating with a vane retention disk 有权
标题翻译：涡轮机叶片与叶片保持盘配合
公开(公告)号：US09567861B2
公开(公告)日：2017-02-14
申请号：US14249851
申请日：2014-04-10
申请人： SNECMA
发明人： Sebastien Congratel , Raphael Dupeyre , Guillaume Klein , David Mathieu , Ba-Phuc Tang , Denis Gabriel Trahot
IPC分类号： F01D5/30 , F01D5/14 , F01D11/00
CPC分类号： F01D5/3015 , F01D5/147 , F01D5/3007 , F01D11/006 , F05D2240/30 , F05D2250/70 , Y02T50/671 , Y02T50/673
摘要： A turbomachine vane for cooperating with a vane retention disk including a plurality of peripheral teeth, the vane including a shank including a neck and a bulb for cooperating with a socket of the disk so as to radially hold the shank in the socket, the socket being a space bounded by two successive teeth of the disk, a pole on top of the neck, including two side walls facing the active surface side of the vane and two side walls facing the passive surface side of the vane, each wall having a rib at a lower end of the pole, the rib extending in the direction of the side wall facing the wall and providing a function of holding the vane when the vane is retained in the disk.
摘要翻译：一种用于与包括多个周缘齿的叶片保持盘配合的涡轮机叶片，所述叶片包括具有颈部的杆和用于与所述盘的插座配合的灯泡，以将所述柄径向地保持在所述插座中，所述插座为由盘的两个连续的齿限定的空间，颈部顶部的极，包括面对叶片的有效表面侧的两个侧壁和面向叶片的被动表面侧的两个侧壁，每个壁具有肋杆的下端，肋沿面向墙壁的侧壁的方向延伸，并且当叶片保持在盘中时提供保持叶片的功能。

5. 发明申请

US20150023793A1 TURBOMACHINE ROTOR BLADE 审中-公开
标题翻译：涡轮转子叶片
公开(公告)号：US20150023793A1
公开(公告)日：2015-01-22
申请号：US14372841
申请日：2013-01-16
申请人： SNECMA
发明人： Slim Bensalah , Arnaud Negri , Sebastien Digard Brou De Cuissart , Guillaume Klein , Ba-Phuc Tang , David Mathieu , Sibylle Doremus
IPC分类号： F01D5/22 , F01D5/30 , F01D5/28
CPC分类号： F01D5/225 , F01D5/28 , F01D5/288 , F01D5/30 , Y02T50/671 , Y02T50/673
摘要： A turbomachine rotor blade presenting an outer part (314) at its distal end (310B), the outer part comprising a platform (320) defining the outside surface of the passage for gas passing through the turbomachine and presenting first (351) and second opposite side edges; and upstream and downstream sealing wipers (331, 332) extending outwards from said platform (320), each wiper extending between two lateral faces (331L, 332L) situated respectively at the first (351) and second side edges. The lateral faces (331L, 332L) of the upstream and downstream wipers (331, 332) are covered at least in part in an anti-wear material (360).
摘要翻译：一种涡轮机转子叶片，其在其远端（310B）处具有外部部分（314），所述外部部分包括限定所述通道的外表面的平台（320），用于通过所述涡轮机的气体，并且呈现第一（351）和第二相对侧边缘以及从所述平台（320）向外延伸的上游和下游密封擦拭器（331,332），每个擦拭器在分别位于第一（351）和第二侧边缘处的两个侧面（331L，332L）之间延伸。上游和下游擦拭器（331,332）的侧面（331L，332L）至少部分地被覆盖在抗磨材料（360）中。

6. 发明授权

US09638049B2 Turbine engine blade 有权
公开(公告)号：US09638049B2
公开(公告)日：2017-05-02
申请号：US14228409
申请日：2014-03-28
申请人： SNECMA
发明人： Raphael Dupeyre , Damien Alquier , Sebastien Congratel , Guillaume Klein , David Mathieu , Ba-Phuc Tang , Denis Gabriel Trahot
IPC分类号： F01D5/30 , F01D11/00 , F01D5/14
CPC分类号： F01D5/30 , F01D5/147 , F01D5/3007 , F01D11/006 , F01D11/008
摘要： A turbine engine blade includes an airfoil connected by a platform to a middle radial wall extending axially and prolonged radially inwards by a blade root that is mountable in a slot of a disk, and the platform and the middle radial wall defining two lateral cavities situated on either side of the middle radial wall and opening out circumferentially to receive scaling members. The cavities are open downstream with two fins projecting on either side of the middle radial wall at downstream end of the middle radial wall, the fins coming to bear against two adjacent teeth of the disk between which the slot is formed. The downstream end of the middle radial wall includes a setback extending between at least one rib of the platform and the fins.

7. 发明申请

US20160129497A1 TURBINE ENGINE BLADE PREFORM 有权
标题翻译：涡轮发动机叶片预制
公开(公告)号：US20160129497A1
公开(公告)日：2016-05-12
申请号：US14895777
申请日：2014-06-04
申请人： SNECMA
发明人： Sébastien Serge Francis Congratel , Raphaël Jean Philippe Dupeyre , Guillaume Klein , David Mathieu , Ba-Phuc Tang
IPC分类号： B22C9/10 , B22D25/02 , B22C9/22
CPC分类号： B22C9/10 , B22C9/06 , B22C9/22 , B22D25/02 , F01D5/141 , F05D2230/21 , F05D2230/61
摘要： The invention relates to a blade preform (46) including a strut connecting a plat-form (16) to a blade root portion (14) extending longitudinally in an upstream-downstream direction, an upstream web (26) and a downstream (28) web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut. The upstream (26) and downstream (28) webs connect the upstream and downstream ends of the plat-form (16) to the upstream and downstream ends of the blade root (14). According to the invention, the blade root (14) extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that of the upstream and downstream webs (26, 28) and the side edges (40) of each web (26, 28) are extended by walls that converge (44) at the flanks of the blade root.
摘要翻译：本发明涉及一种刀片预制件（46），其包括将平板形式（16）连接到沿上游 - 下游方向纵向延伸的叶片根部（14）的支柱，上游腹板（26）和下游（28）腹板，其各自沿着与叶片根部的纵向方向基本垂直的方向延伸并形成在支柱的上游和下游端部。上游（26）和下游（28）腹板将平台形式（16）的上游和下游端连接到叶片根部（14）的上游和下游端。根据本发明，叶片根部（14）在与叶片根部的纵向方向垂直的方向上延伸的距离小于上游和下游腹板（26,28）的距离和每个侧缘（40）的侧边缘腹板（26,28）通过在叶片根部的侧面会聚（44）的壁延伸。

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