A THEORETICAL INVESTIGATION OF THE FLUTTER CHARACTERISTICS OF COMPRESSOR AND TURBINE BLADE SYSTEMS

摘要

The problem of blade-row flutter is attacked in four phases. In Part I, the equations of motion are formulated for a single rotating blade at the flutter condition with provision for centrifugal effects, blade twist, rotary inertia due to flexure, and racially varying section properties. In Fart II, a simple relation is proved to exist between the motions of all the blades of a blade row at flutter under any condi¬tions of flow as well as any form of interblade coupling, with the sole restriction that the phenomenon be satisfactorily represented by a linear analysis. This analysis is restricted at first to the condition of infinite rotor inertia and is then extended to allow for the possibility of oscillation of the entire rotor in the rotational direction.