公开(公告)号：EP3347147B1

公开(公告)日：2019-05-01

申请号：EP16775806.9

申请日：2016-09-08

申请人： Safran Aircraft Engines

发明人： ONFRAY, Rémi, Philippe, Guy ,  BRIEND, Maxime ,  PELLETIER, Didier

IPC分类号： B21D53/78 ,  F01D5/28 ,  B23P15/04

公开(公告)号：EP3347147A1

公开(公告)日：2018-07-18

申请号：EP16775806.9

申请日：2016-09-08

申请人： Safran Aircraft Engines

发明人： ONFRAY, Rémi, Philippe, Guy ,  BRIEND, Maxime ,  PELLETIER, Didier

IPC分类号： B21D53/78 ,  F01D5/28 ,  B23P15/04

CPC分类号： B23P15/04 ,  B21D53/78 ,  B23H5/04 ,  B23K26/0093 ,  B23K2101/001 ,  F01D5/147 ,  F01D5/28 ,  F04D29/289 ,  F04D29/324 ,  F05D2220/32 ,  F05D2230/20 ,  F05D2240/303

摘要： The invention proposes a method for producing a protective reinforcement for the leading edge (BA) or trailing edge of a blade (P), the leading edge (BA) or trailing edge being curved, the method comprising steps of flattening (102) a hollow tube (1) so as to form at least one fold line (6) extending along the tube (1), opening (104) the flattened tube (1) by cutting the tube (1) along a cutting line (8) opposite the fold line (6) with respect to the tube (1), so as to form two flanks (16, 18) linked at the fold line (6) and intended to be mounted on the pressure side and the suction side of the blade (P), the method being characterised by a preliminary step (100) of bending the hollow tube (1) carried out before the flattening (102) and adapted such that the fold line (6) after flattening (102) is curved and substantially matches the curved leading edge (BA) of the blade (P).