为探究转捩对压气机叶片气动阻尼的影响规律，以某压气机平面叶栅R13为研究对象，通过7通道影响系数法，分别采用转捩模型和全湍流模型，计算了进口马赫数0.6工况下不同攻角和不同叶间相位角的气动阻尼。结果表明：转捩计算得到的攻角范围比全湍流结果窄，同时转捩计算得到气动阻尼随着攻角的增大而逐渐高于全湍流结果，攻角为负值时两者相差较小；转捩和全湍流计算得到的气动阻尼在叶间相位角接近0°时差别较小，但在远离0°时差别较大；转捩影响通过叶片表面压力幅值和相位角改变叶片表面的气动功密度分布，并且主要通过影响压力相位角影响整体气动阻尼；在不同攻角和叶间相位角下，转捩和全湍流计算得到的压力相位角差别较大，导致整体气动阻尼不同；当压气机叶片表面中部存在明显的转捩现象并且攻角较大时，气动阻尼的计算需要考虑采用转捩模型

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 transition 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.

V232.4

国家科技重大专项资助（J2019Ⅱ00050025）