Mechanism of influence of eccentricity on aeroelastic stability of labyrinth seal ring
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摘要:
针对航空发动机偏心涡动状态的篦齿封严环气弹稳定性问题，提出分别应用旋转坐标系、三维插值与非定常动网格技术，综合考虑篦齿封严环的偏心涡动与模态振型等因素，基于能量法建立了偏心篦齿封严环气弹稳定性求解模型，在验证求解模型准确性基础上，研究了在偏心状态下，涡动频率、进动形式及模态振型对篦齿封严环气弹稳定性的影响规律，分析了气动功在齿腔不同区域分布特性，揭示了偏心涡动对篦齿封严环气弹稳定性的影响机理。研究表明：篦齿封严环低节径气动阻尼比相对于其他节径更易受偏心涡动影响，其中第1节径气动阻尼比会随偏心率的增加逐渐减小，并由正值转变为负值，引发气弹失稳；相对于正进动，反进动形式具有更大的气动阻尼比；对于稳定状态，气动阻尼比随涡动频率增加而增加；篦齿封严环气动功沿轴向呈周期振荡衰减分布，且振荡幅值沿气流方向逐级衰减，稳定状态篦齿封严环低压侧气动功会由负功转变为正功；偏心率的增加引起篦齿封严环轴向各区域气动功逐渐增加，致使总气动功由负转正，导致失稳；偏心率的增加不会改变各区域气动功占总功百分比。
Abstract:In view of the aeroelastic stability problem of the labyrinth seal ring under eccentric whirling state of the aeroengine, the rotating coordinate system, three-dimensional interpolation and unsteady dynamic mesh technology were used to establish a solution model for the aeroelastic stability of the labyrinth seal ring based on the energy method, taking into account the factors of eccentric whirling and modal shape of the labyrinth seal ring. On the basis of verifying the accuracy of the solution model, the aeroelastic stability of the labyrinth seal ring under the eccentric condition was studied. The influence law of whirling frequency, precession form and mode shape on the aeroelastic stability of labyrinth seal ring was analyzed. The distribution characteristics of the aerodynamic work of labyrinth seal ring in different regions of the tooth cavities were analyzed, and the influence mechanism of eccentricity on the aeroelastic stability of labyrinth seal ring was revealed. The results showed that the aerodynamic damping ratio of labyrinth seal ring with low nodal diameter was more susceptible to eccentric whirling than that of other nodal diameters. The aerodynamic damping ratio of the first nodal diameter gradually decreased with the increase of eccentricity and changed from positive to negative value, leading to aerodynamic instability. Compared with the forward precession, the backward precession had larger aerodynamic damping ratio. Under stable state, the aerodynamic damping ratio increased with the increase of the whirling frequency. The aerodynamic work of the labyrinth seal ring presented waveform attenuation and oscillation distribution along the axial direction, and the amplitude of oscillation decayed step by step along the direction of the air flow. The aerodynamic work of the low pressure side of the labyrinth seal ring under stable state changed from negative work to positive work. The increase of eccentricity led to gradual increase of aerodynamic work in each axial region of the labyrinth seal ring, resulting in the change of the total aerodynamic work from negative to positive, resulting in instability. The increase of eccentricity did not change the contribution rate of aerodynamic work in each region to the total work.
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图 2 篦齿封严环气弹稳定性数值求解模型
Figure 2. Numerical model for aeroelastic stability of labyrinth seal ring
图 5 篦齿封严环气弹稳定性分析流程
Figure 5. Analysis process of aeroelastic stability of labyrinth seal ring
图 13 气动阻尼比随涡动频率的变化
Figure 13. Variation of aerodynamic damping ratio with whirling frequency
图 14 气动阻尼比随进动形式的变化
Figure 14. Variation of aerodynamic damping ratio with precession form
图 17 不同偏心率不同轴向位置气动功分布
Figure 17. Aerodynamic work distribution in different axial positions with different eccentricities
图 19 不同节径不同轴向位置气动功分布
Figure 19. Aerodynamic work distribution in different axial positions with different nodal diameter
表 1 工况条件
Table 1. Calculation conditions
参数 数值及说明 出口压力/MPa 0.1 压比 5 转速/（r/min） 5000 偏心率 0/0.1/0.3/0.5 进动形式 正进动/反进动 流体属性 理想空气 湍流模型 k-ε 壁面设置 无滑移光滑壁面 绝热壁面 
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