Flutter in Started and Unstarted Transonic Linear Cascades: Simultaneous Measurements of Unsteady Loads and Shock Dynamics

Abstract

In the present work, we report on an experimental study of bending/flap mode flutter of a blade within a linear cascade at transonic conditions. Driven by the motivation to understand the contribution of shock location/dynamics to flutter characteristics, we have performed simultaneous measurements of shock dynamics using high-speed shadowgraphy combined with unsteady load measurements on an oscillating blade within the cascade. The flutter characteristics in terms of energy transfer from the fluid to the blade and shock dynamics have been mapped out over a range of blade oscillation frequencies and static pressure ratios (SPRs) across the cascade, the latter being important as they decide the mean location of the passage shocks. SPR values studied include both conditions where the shock is within the passage (started cascade) and where the passage shock is pushed ahead of the leading edge of the blades (unstarted cascade). These measurements show characteristically different flutter behavior for an unstarted cascade compared with a started cascade, the former having received very little attention in the literature. While both these cases show small excitation levels at low reduced frequencies, the unstarted cascade case exhibits an additional relative narrow region of excitation at higher reduced frequencies with approximately an order of magnitude higher excitation energies. Comparison of the shock dynamics between the two excitation regimes shows significant differences in the phase of the leading edge shock in addition to changes in the suction side shock phase indicating that the two excitation regimes are of different origin.

Flutter Measurement of a Linear Turbine Blade Cascade with an Angular Position Deviation of One Blade

“…Oscillating linear blade cascades are frequently used in experiments [19][20][21][22][23] and two methods are known for controlled flutter testing: a Travelling Wave Mode (TMW) and an Influence Coefficient Method (ICM). Flutter in uniform turbomachine blade rows can be realistically represented using the TWM approach, where all blades oscillate in the same mode with the same amplitude and frequency but at various inter-blade phase angles.…”