公开(公告)号：US20190240725A1

公开(公告)日：2019-08-08

申请号：US16314341

申请日：2017-06-07

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Coralie Cinthia Guerard ,  Vincent Marc Herb ,  Jun Ni ,  Joseph Toussaint Tami Lizuzu ,  Matthieu Jean Luc Vollebregt

IPC分类号： B22C9/10 ,  B22C9/04 ,  B22C9/24 ,  F01D5/18

CPC分类号： B22C9/10 ,  B22C9/04 ,  B22C9/24 ,  F01D5/187 ,  F05D2250/241

摘要： The present disclosure is generally directed to a core configured for the manufacturing of a turbine engine blade by lost-wax casting. The core includes a first convex curved outer face and a second concave curved outer face. The first and second faces have a plurality of recesses, each recess including a spherical portion.

公开(公告)号：US10682687B2

公开(公告)日：2020-06-16

申请号：US16314341

申请日：2017-06-07

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Coralie Cinthia Guerard ,  Vincent Marc Herb ,  Jun Ni ,  Joseph Toussaint Tami Lizuzu ,  Matthieu Jean Luc Vollebregt

IPC分类号： B22C9/10 ,  B22C9/24 ,  F01D5/18 ,  B22C9/04

摘要： The present disclosure is generally directed to a core configured for the manufacturing of a turbine engine blade by lost-wax casting. The core includes a first convex curved outer face and a second concave curved outer face. The first and second faces have a plurality of recesses, each recess including a spherical portion.