T. Nishizawa et H. Takata, Numerical study on stall flutter of a compressor cascade - (1st report, numerical method and numerical example), JSME I J B, 43(3), 2000, pp. 351-360
Citations number
20
Categorie Soggetti
Mechanical Engineering
Journal title
JSME INTERNATIONAL JOURNAL SERIES B-FLUIDS AND THERMAL ENGINEERING
Stall flutter of a compressor cascade is studied by the numerical analysis
of the unsteady separated flow around the blades oscillating in a torsional
mode. A numerical method is developed for the present study, in which used
are a discrete vortex modeling to calculate the convection and the diffusi
on of vorticity in the separated flow and a grid system deforming together
with blade oscillation. The present method is applied to a compressor casca
de working at an inlet flow angle where the rotating stall is also liable t
o occur. The numerical result shows that the strong vortices shed from the
leading edge of stalled blades have dominant influences both on the flow be
havior and on the flutter excitation of blades, and that the occurrence of
stall flutter is closely connected with the propagation of rotating stall.