摘要 |
A turbo engine includes a system for changing a pitch of blades of a propeller, the system including an annular fluid cylinder with a linear drive and a link mechanism linking the cylinder to the blades of the propeller to change an orientation of the propeller. The annular cylinder of the system can be rigidly mounted on a fixed housing supporting the propeller and internal to it, unlike the blades mounted in an external rotating hub of the propeller, and the link mechanism includes a displacement transfer bearing fixed, on one side, to the mobile part of the cylinder and cooperating, on the other side, with a mechanism linking to the blades of the rotating hub of the propeller. |
申请人 |
Safran Aircraft Engines;GE Aviation Systems Limited |
发明人 |
ESCURE, Didier, René, André;BOCQUET, Denis, Louis;CHARIER, Gilles, Alain;SZYMANDERA, Aleksander;MALITKA, Marek;SIKORSKI, Jan;CARRINGTON, Christopher |