公开(公告)号：US12084779B2

公开(公告)日：2024-09-10

申请号：US15733743

申请日：2019-04-19

申请人： SAFRAN AIRCRAFT ENGINES ,  SAFRAN

发明人： Marc Soisson ,  Said Boukerma ,  Janusz Lisowski ,  Alexandre Gimel ,  Amar Saboundji

IPC分类号： C23F1/04 ,  B22C7/02 ,  B22C9/10 ,  B22C9/24 ,  B23P15/02 ,  F01D5/14

CPC分类号： C23F1/04 ,  B22C9/10 ,  B22C9/24 ,  B23P15/02 ,  F01D5/14 ,  B22C7/02 ,  F05D2220/323 ,  F05D2230/10 ,  F05D2230/21

摘要： The invention relates to a method for producing a metal bladed element for a turbomachine of an aircraft, said bladed element comprising at least one blade having a lower surface and an upper surface extending between a leading edge and a trailing edge of the blade, the trailing edge having to have a thickness X1, said method comprising the steps of: a) producing the bladed element by lost-wax casting, and b) finishing the bladed element, characterised in that step b) comprises the chemical milling at least of the trailing edge of the or each blade so as to obtain said thickness X1 which cannot be directly obtained by step a).

公开(公告)号：US11904420B2

公开(公告)日：2024-02-20

申请号：US18030425

申请日：2021-09-30

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Jérôme Salmon ,  Alexandre Gimel ,  Christophe Gleize ,  Axel Pereira ,  Jean François Richard

IPC分类号： B23P15/04 ,  B21D53/78 ,  B23K20/02 ,  F01D5/28

CPC分类号： B23P15/04 ,  B21D53/78 ,  B23K20/021 ,  B23K20/023 ,  F01D5/28 ,  F05D2230/64 ,  F05D2300/174

摘要： The invention relates to a method for producing a turbomachine compressor blade, comprising the following steps:—installing primary pins (26) comprising a material other than a titanium-based alloy in primary bores (20) of a core, the primary bores forming at least one polygon, and installing a secondary pin made of titanium-based alloy in a secondary bore of the core; —producing a stack (2) of a suction-face sheet (4), a core (14) and a pressure-face sheet (6); —compacting the stack; —removing the primary pins (26) from the primary bores (20); —removing the secondary pin from the secondary bore; and—taking the core (14) away from the stack.

公开(公告)号：US12060809B2

公开(公告)日：2024-08-13

申请号：US17617749

申请日：2020-06-12

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Maxime Paul Numa Givert ,  Christophe Damour ,  Alexandre Gimel ,  Elsa Maxime ,  Denis Gabriel Trahot

IPC分类号： F01D5/14 ,  F01D5/22

CPC分类号： F01D5/141 ,  F01D5/22 ,  F05D2220/323 ,  F05D2240/30 ,  F05D2260/96

摘要： A turbine engine has a blade with lower and upper surfaces. The blade has a root at a radially external end and includes a transverse head section in a plane perpendicular to a radial direction of the blade, taken at the radially external end with a first center of gravity. The root has a second center of gravity defined in a plane parallel to the transverse head section and transversely offset from the first center of gravity. The second center of gravity is defined in a predetermined zone at least partly demarcated by a V that is open towards the lower surface and includes a peak, the orthogonal projection of which on the transverse head section is located on the first center of gravity.