Abstract
Along with the development of advanced high-performance aero-engines to the higher thrust-weight ratio, further improvement of stage load, the adoption of new materials and new lightweight structures, the aeroelasticity of blade structure is becoming more and more prominent. The high cycle fatigue failure of blades significantly reduces the structural reliability during the process of development and using. At the same time, a large number of failure forms of aero-engine experimental and server can be attributed to aeroelastic problems. Therefore, it is urgent to improve the aeroelastic stability of the blade. One of the most important factors is to suppress the airflow separation, but its mechanism is still unclear. Based on this, this paper combines the aerodynamic damping analysis of energy method with the plasma excitation simulation and references low-speed wind tunnel plasma expansion test to consider the effects of different exciter distributions and intensities on flutter. The results show that stall flutter is related to the flow separation, but the flow separation is not a key factor that determinates whether the flutters occurs or not. Flutter suppression is strongly correlated with the shock wave intensity, amplitude of first harmonic aerodynamic force, low-speed separation and aerodynamic work density. In addition, the relative distribution of the excitation field and the positive work zone also has a direct effect on the suppression of flutter.
Highlights
Blade flutter is one of the fluid-induced aeroelastic self-excited phenomenon, which often occurs in the turbomachinery, especially for the transonic compressor blades
Zhang [4] interpolated the structure obtained from the computational structure dynamics analysis on the fluid grid and applied the computational fluid dynamics (CFD) method to realize the unsteady analysis under the oscillating field, and the results show that the flutter boundary of the compressor blade predicted by the energy method agrees well with the test one
A comparison between Fig.5 and Fig.6 can be found that the airflow separation after strong shock waves and a backflow area is generated at the tip of the blade
Summary
Blade flutter is one of the fluid-induced aeroelastic self-excited phenomenon, which often occurs in the turbomachinery, especially for the transonic compressor blades. The plasma flow control technology is a developing method on the compressor stall margin improvement. Experts and scholars think the plasma excitation has significant technological advantages such as short response time and short excitation frequency bandwidth It has broad application prospects in compressor stall margin improvement. Compering simulation test and actual, Liang et al [13] proved that the aerodynamic excitation is equivalent to the volume force with high accuracy which laid the foundation for the application of plasma flow control technology. Through comparing the aerodynamic damping, aerodynamic work density distribution, static pressure distribution on the blade surface and aerodynamic separation of the flow field, the flutter characteristics of the compressor blades under the conditions with or without plasma excitation have been analyzed. The mechanism of compressor stall margin improvement and flutter suppression have been explained
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