Study on the influence of support blade vibration on aerodynamic pulsation pressure load
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摘要:
为了探究航空发动机进气支板产生裂纹的原因，设计了基于薄膜传感器的支板测试系统。通过在ANSYS中建立支板及其流场的物理模型，在支板表面施加不同频率的低幅点载荷，以模拟不同转速下后排转子通过转静干涉过程作用到支板表面的激励力，建立Fluent模块与Transient Structural模块之间的双向数据传输来实现双向流固耦合仿真。通过仿真得到瞬时分析的结果（后排转子对支板的激励力可忽略）与实际测试结果进行对比。结果表明：在共振转速附近时，支板表面压力幅值显著增大，与薄膜压力传感器测试所得结果一致。说明叶片共振时，流固耦合作用不可忽略。分析过程与结论为航空发动机进气支板裂纹产生机理分析提供了理论依据，同时为支板结构设计提供了一种思路。
Abstract:In order to investigate the cause of the crack in the aero engine intake support plate, a test system of support plate based on thin film sensor was designed. Then, the physical model of the support plate and its flow field were established in ANSYS, and low amplitude point loads of different frequencies were applied to the surface of the support plate to simulate the exciting force on the surface of the support plate through the static interference process of the rear rotor at different speeds. Two-way data transmission between Fluent module and Transient Structural module was established to realize two-way fluid-structure coupling simulation. Finally, the instantaneous analysis results (the excitation force of the rear rotor on the support plate can be ignored) were compared with the actual test results. The results showed that the surface pressure amplitude of the support plate increased significantly when the resonant speed was near, which was consistent with the measured results of the thin film pressure sensor. It showed that the fluid-structure coupling can’t be ignored when the blade resonated. The analysis process and conclusion could provide a theoretical basis for the analysis of the mechanism of crack generation in the aero-engine intake support plate, and also provide an idea for the design of support plate structure.
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图 5 双向流固耦合仿真求解流程图
Figure 5. Two-way fluid-structure coupling simulation solution flow chart
图 7 支板固、流体域模型及网格划分示意图
Figure 7. Support plate solid and fluid domain model and grid division diagram
图 10 Workbench中的双向流固耦合设置界面
Figure 10. Two-way fluid-structure coupling setup interface in Workbench
图 11 第4阶模态实际压力分布对比
Figure 11. Comparison of the fourth mode and actual pressure distribution
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