COMPRESSOR BLADE WITH REDUCED AERODYNAMIC BLADE EXCITATION

摘要

The compressor blades of an aircraft engine are, in at least one natural- vibration critical area, designed such at the blade leading edge (6) that the leading edge shock (14) attaches to the leading edge (6), as a result of which the laminar boundary layer flow (7) on the suction side (13) quickly transits into the turbulent boundary layer flow (9) which is kept constant and prevented from re- lamination by the further, continuous curvature of the suction side. Therefore, the transition, whose periodic movement is also suppressed, cannot communicate with the suction-side compression shock (10), preventing the compression shock from augmenting the natural vibrations of the blade occurring under certain flight conditions. The blade leading edge can, for example, be designed as ellipse with a semi-axis ratio equal to or smaller than 1 : 4.