公开(公告)号：US11867065B2

公开(公告)日：2024-01-09

申请号：US17760369

申请日：2021-02-11

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Edouard Emmanuel Garreau ,  Josserand Jacques Andre Bassery ,  Lucas Geoffrey Desbois ,  Etienne Leon Francois ,  Samuel Laurent Noel Mathieu Juge ,  Elsa Maxime ,  Ba-Phuc Tang ,  Denis Gabriel Trahot ,  Thomas Tsassis

IPC分类号： F01D11/00

CPC分类号： F01D11/001 ,  F05D2220/323 ,  F05D2250/141 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2250/713

摘要： To increase the inertia of a sealing lip of a blade for an aircraft turbine engine, and thus improve the service life of such a sealing lip, the sealing lip is conformed so as to have a trough in the outer surface thereof and a corresponding boss in the inner surface thereof, the trough and the boss being defined based on a connection cross section of the sealing lip to a blade body, and being formed at a distance from a free axial end of the sealing lip.

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.