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مکانیک::
لبه فرار
What may appear at first sight a relatively simple task of interpreting the modal characteristics of the blade is oftentimes hampered by the geometric configuration-the root structure is thick, with a complex fir tree form for attachment to the disk; the airfoil trailing edge is thin; the cross-section profiles are varying at different radial heights; and the blade is twisted and leaned.
Individual blades also need to be tested using modal analysis with impulse, white noise and sinusoidal excitation applied at the leading edge and at the trailing edge.
are passage vortex, trailing edge vortices, corner vortex, and horseshoe vortex.
The position of maximum loss and wake behind the trailing edge and its
One-stage designs in the transonic mode often experience dis- tinct trailing edge shocks on the blades (Ahmad and Mirzamoghadam, 1999).
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