Compressor blade with reduced aerodynamic blade excitation

Details Compressor blade with reduced aerodynamic blade excitation Compressor blade with reduced aerodynamic blade excitation

2004-06-18

2009-02-03

Nguyen, Ninh H (Department: 3745)

Fluid reaction surfaces (i.e., impellers)

Specific blade structure

Tined or irregular periphery

C416S235000, C416S243000

Reexamination Certificate

active

07484937

ABSTRACT:
The compressor blades of an aircraft engine are, in at least one natural-vibration critical area, designed such that at the blade leading edge (6), the leading edge shock wave (14) attaches to the leading edge (6), as a result of which a laminar boundary layer flow (7) on the suction side (13) quickly transitions into a 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 a 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 an ellipse with a semi-axis ratio equal to or smaller than 1:4.

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