Invention Grant
- Patent Title: Turbomachine vane with integrated metal leading edge and method for obtaining it
-
Application No.: US16879171Application Date: 2020-05-20
-
Publication No.: US11333028B2Publication Date: 2022-05-17
- Inventor: Sébastien Serge Francis Congratel , Célia Iglesias Cano , Antoine Hubert Marie Jean Masson
- Applicant: SAFRAN AIRCRAFT ENGINES
- Applicant Address: FR Paris
- Assignee: SAFRAN AIRCRAFT ENGINES
- Current Assignee: SAFRAN AIRCRAFT ENGINES
- Current Assignee Address: FR Paris
- Agency: Pillsbury Winthrop Shaw Pittman LLP
- Priority: FR1905301 20190521
- Main IPC: F01D5/28
- IPC: F01D5/28 ; B29C33/12 ; F01D5/14 ; B29D99/00

Abstract:
A turbomachine vane includes a blading made of composite material with fibrous reinforcement densified by a matrix and an integrated metal leading edge, the blading extending in a longitudinal direction, the leading edge being formed by a metal foil overmolded onto the blading, the foil having a lower wing and an upper wing which extend respectively on the lower and upper faces of the blading while matching an aerodynamic profile of the vane. One of the lower wing and the upper wing has a positioning portion extending in the longitudinal direction, the portion having a flat inner face and an increasing thickness away from the leading edge, and being housed in a correspondingly shaped groove in the blading.
Public/Granted literature
- US20200370438A1 TURBOMACHINE VANE WITH INTEGRATED METAL LEADING EDGE AND METHOD FOR OBTAINING IT Public/Granted day:2020-11-26
Information query