| 摘要 |
<p>The blade (1) has a lower aerodynamic part (11) comprising a single aerodynamic profile (13), and an upper aerodynamic part (12) comprising two identical aerodynamic profiles (14). The aerodynamic parts are superimposed along a radial direction (Z), and a joint platform (10) separates the aerodynamic parts. The platform constitutes a flow separation nozzle for separating a main exhaust flow and a secondary exhaust flow in a turbojet engine.</p> |
