公开(公告)号：EP2598721B1

公开(公告)日：2014-04-23

申请号：EP11754709.1

申请日：2011-07-20

申请人： Snecma

发明人： ALQUIER, Damien ,  BOURY, Jacques, Auguste, Amédée ,  COURTIN, Pascal ,  TRAN, Huu-Thanh

IPC分类号： F01D11/00 ,  F01D5/22

CPC分类号： F01D5/12 ,  F01D5/22 ,  F01D5/24 ,  F01D11/006 ,  F05D2250/231 ,  Y02T50/672

公开(公告)号：EP2817114A1

公开(公告)日：2014-12-31

申请号：EP13704418.6

申请日：2013-02-12

申请人： SNECMA

发明人： TRAN, Huu-Thanh ,  HANSOM, Michael ,  BARIAUD, Christian ,  ENEAU, Patrice

IPC分类号： B22C9/10 ,  B22C9/04 ,  F01D5/18

CPC分类号： F01D5/147 ,  B22C7/02 ,  B22C9/04 ,  B22C9/103 ,  B22C21/14 ,  F01D5/187 ,  F05D2230/211

摘要： The invention relates to a foundry core (30) for manufacturing a blade (1) of a turbomachine (1) having a tip section offset, comprising a core element (31) for forming various internal cavities (19a-19e), said core element comprising a leading-edge cavity internal core (31a), central cavity internal cores (31b, 31c, 31d) and a trailing-edge cavity internal core (31e), characterized in that the internal core for the central cavity (31d) adjacent to the internal core (31e) for the trailing-edge cavity has a bulge (34) extending toward the core (31a) for the leading-edge cavity.

摘要翻译： 甲铸造芯用于制造涡轮机的包括尖端部的叶片的偏移，包括用于形成各种内部空腔的芯元件，所述芯元件包括一个前缘腔内芯，中心腔内部芯，和一个后缘腔内部 核心。 为中心腔毗邻的后缘腔内芯内芯包括一个凸起朝向芯的前缘空腔延伸。

公开(公告)号：EP2809887A1

公开(公告)日：2014-12-10

申请号：EP13704197.6

申请日：2013-01-24

申请人： SNECMA

发明人： HANSOM, Michael ,  TRAN, Huu-Thanh ,  BARIAUD, Christian

IPC分类号： F01D11/00 ,  B23H9/10 ,  B23Q3/06

CPC分类号： F01D5/14 ,  B23P15/02 ,  B23Q3/063 ,  F01D5/147 ,  F01D11/008 ,  F05D2230/10 ,  F05D2230/68 ,  F05D2240/306 ,  Y02T50/671 ,  Y02T50/673 ,  Y10T29/49336

摘要： A method for machining, in a three-dimensional machining centre, a vane (10) comprising an airfoil blade (18), a platform (12) beneath the upstream and downstream portions of which are formed, respectively, upstream and downstream supports (12A, 12B) for a sealing liner (20), a blade root (16) and a stilt (14) interposed between said platform and the blade root, method wherein the supports form two bearing points (22A, 22B) for a 6-point system for positioning the vane in the three-dimensional machining centre.

公开(公告)号：EP2809887B1

公开(公告)日：2016-09-28

申请号：EP13704197.6

申请日：2013-01-24

申请人： SNECMA

发明人： HANSOM, Michael ,  TRAN, Huu-Thanh ,  BARIAUD, Christian

IPC分类号： F01D11/00 ,  B23H9/10 ,  B23Q3/06

CPC分类号： F01D5/14 ,  B23P15/02 ,  B23Q3/063 ,  F01D5/147 ,  F01D11/008 ,  F05D2230/10 ,  F05D2230/68 ,  F05D2240/306 ,  Y02T50/671 ,  Y02T50/673 ,  Y10T29/49336

公开(公告)号：EP2598721A1

公开(公告)日：2013-06-05

申请号：EP11754709.1

申请日：2011-07-20

申请人： Snecma

发明人： ALQUIER, Damien ,  BOURY, Jacques, Auguste, Amédée ,  COURTIN, Pascal ,  TRAN, Huu-Thanh

IPC分类号： F01D11/00 ,  F01D5/22

CPC分类号： F01D5/12 ,  F01D5/22 ,  F01D5/24 ,  F01D11/006 ,  F05D2250/231 ,  Y02T50/672

摘要： The invention relates to an inter-vane seal for a wheel of a turbine or a turbomachine compressor, comprising inserts (38) engaged in longitudinal cavities (32) of the lateral edges of the platforms (18) of the vanes (14) and being supported in operation on the lateral edges facing the platforms of the adjacent vanes (12), each insert having a long cylindrical form and a comprising, on its outer cylindrical surface, at least one annular gap (44) for the passage of air for cooling the platforms and at least one annular groove (46) forming a wear control, the depth of said groove being less than the or each annular gap (44) for the passage of the cooling air.