In order to investigate the effect of transition on aerodynamic damping of compressor blades,using a compressor plane cascade R13 as the research object,the aerodynamic damping of different attack angles and different interblade phase angles under inlet Mach number of 0.6 was calculated by using the transition model and the full turbulence model respectively by using the 7-channel influence coefficient method.The results show that the range of the angle of attack calculated by transition is narrower than that of the total turbulence,while the aerodynamic damping obtained by transition is gradually higher than that of the total turbulence with the increase of the angle of attack,and the difference is smaller when the angle of attack is negative;the aerodynamic damping calculated by the transition and total turbulence is little different when the interblade phase angle is close to 0°,but much different when the interblade phase angle is far away from 0°;the aerodynamic power density distribution on the blade surface is changed by transition influence through the pressure amplitude and phase angle on the blade surface,but the overall aerodynamic damping is mainly affected by the influence of pressure phase angle;at different attack angles and interblade phase angles,the pressure phase angles calculated by the transition and total turbulence are quite different,resulting in different aerodynamic damping;when there is obvious transi-tion phenomenon in the middle of compressor blade surface and the angle of attack is large,the transition model should be considered in the calculation of aerodynamic damping.
关键词
转捩/气动阻尼/攻角/叶间相位角/压气机
Key words
transition/aerodynamic damping/angle of attack/interblade phase angle/compressor
维普
万方数据