公开(公告)号：EP2483565B1

公开(公告)日：2016-01-06

申请号：EP10768209.8

申请日：2010-10-01

申请人： Snecma ,  Cenaero

发明人： BOSTON, Eric, Jacques ,  CHARTOIRE, Alexandre, Franck, Arnaud ,  ILIOPOULOU, Vasiliki ,  LEPOT, Ingrid ,  OBRECHT, Thierry, Jean-Jacques

IPC分类号： F04D29/32 ,  F01D5/14 ,  F04D29/66

CPC分类号： F04D29/321 ,  F01D5/143 ,  F04D29/329 ,  F05D2240/80 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/673

公开(公告)号：EP2483565A2

公开(公告)日：2012-08-08

申请号：EP10768209.8

申请日：2010-10-01

申请人： Snecma ,  Cenaero

发明人： BOSTON, Eric, Jacques ,  CHARTOIRE, Alexandre, Franck, Arnaud ,  ILIOPOULOU, Vasiliki ,  LEPOT, Ingrid ,  OBRECHT, Thierry, Jean-Jacques

IPC分类号： F04D29/32 ,  F01D5/14 ,  F04D29/66

CPC分类号： F04D29/321 ,  F01D5/143 ,  F04D29/329 ,  F05D2240/80 ,  F05D2250/711 ,  F05D2250/712 ,  Y02T50/673

摘要： A rotor of a turbomachine compressor, including a bladed rotor disk fitted at its radially external end with a wall forming the inner end of an annual flow channel of a primary gas flow, and formed from multiple angular sectors, each of which is delimited between two blades of the disk which are consecutive in a circumferential direction and includes a bulging portion which is convex in the axial direction and in the circumferential direction, together with, upstream from the bulging portion, a troughed portion which is concave in the axial direction and in the circumferential direction and which has a base which is roughly punctiform.

公开(公告)号：EP2582985A1

公开(公告)日：2013-04-24

申请号：EP11735463.9

申请日：2011-06-09

申请人： Snecma

发明人： PERROT, Vincent, Paul, Gabriel ,  PESTEIL, Agnès ,  BAERT, Lieven ,  ILIOPOULOU, Vasiliki

IPC分类号： F04D29/52 ,  F04D29/68 ,  F01D5/14 ,  F01D5/20

摘要： Turbomachine compressor (10) comprising a casing (12) of which an inner wall defines an aerodynamic reference surface delimiting a gas flow duct, and in which there is mounted a bladed wheel (14) equipped with radial blades (18). A circumferential groove is formed in the inner wall of the casing. Its shape is defined from upstream to downstream by three substantially conical surfaces, an upstream surface, a central surface and a downstream surface, respectively. The upstream surface extends upstream of the leading edge of the blades. The central surface is substantially parallel to said aerodynamic reference surface. The downstream surface extends downstream at least as far as the trailing edge of the blades. The junction between the central and downstream surfaces is situated between 30% and 80%, preferably between 50 and 65%, of the axial length of the blades (18) starting from the leading edge.