In order to establish the blade flutter suppression engineering design method, the correlation between blade flutter characteristics and structural parameters of a high-pressure compressor rotor blade was investigated. The energy method based on the phase lagged boundary condition and the eigenvalue method was used to analyze the aeroelastic stability of the prototype blade. By analyzing the unsteady aerowork density distribution under near stall condition, the effects of design parameters such as radial distribution of the blade stagger angle, chord length and tip clearance were investigated to clarify the influence and its extent of each parameter on the flutter, so as to improve the aerodynamic damping. The results show that the tip clearance has the greatest influence on aerodynamic damping, the stagger angle takes the second place, and the chord length is the least. The variation of aerodynamic damping with tip clearance is not monotonous, so there exists a tip clearance to minimize the blade aerodynamic damping, where the blade aeroelastic stability is the worst. Reducing the attack angle and increasing the reduced frequency can improve the aerodynamic damping. In the design phase, the attack angle can be reduced by adjusting the stagger angle, and the reduced frequency can be increased by increasing the chord length. In consideration of the influence on the aerodynamic performance, the change of the attack angle is usually less than 5°. In addition, when adjusting the chord length and tip clearance, ensure that all structural components will not be collided. © 2020, Editorial Department of Journal of Propulsion Technology. All right reserved.
