Abstract
After more than 30 years of research, flutter is still a major headache when developing jet engines. In modern transonic fans, requirements of high efficiency at high speed results in flat and thin blades which are especially vulnerable to a new type of flutter. The mechanism of this flutter was revealed by Isomura [1] and Isomura and Giles [2], that the shock instability at the point of unstarting is responsible. In their paper, numerical studies were performed assuming the blades are oscillating in pure bending mode. As an approximation to study the mechanism, this assumption is acceptable because the torsional component in the first flex mode, which is the typical oscillation mode in transonic fans, is small. But in reality, fans will seldom oscillate in pure bending mode in two dimensional section aligned to the flow direction, instead the blade oscillation mode usually contains torsional components. For designers of transonic fans, information on the effect of the torsional component on this shock-induced flutter will be important to push their designs to the limit of high efficiency. Flutter is often very costly to fix and can result in fatal accident when it occurs.
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