| 气流激励下叶片振动响应分析方法 |
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| 引用本文： | 田少杰,漆文凯,许正华.气流激励下叶片振动响应分析方法[J].航空动力学报,2021,36(4):826-838. |
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| 作者姓名： | 田少杰 漆文凯 许正华 |
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| 作者单位： | 南京航空航天大学能源与动力学院,南京210016 |
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| 基金项目： | 国家科技重大专项(2017-Ⅳ-0007-0044) |
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| 摘 要： | 为开展气流激励下叶片振动响应分析方法研究,建立了气动激振力预估方法,采用非线性谐波法对叶排进行三维非定常流动分析,获得叶片表面的脉动压力,编制流固转换程序,计算叶片所受的气动激振力。建立了叶片气动阻尼分析方法,基于能量法和弱耦合分析法,对叶片与流场进行流固弱耦合分析,将气动力对运动的叶片所做的气动负功等效为黏滞阻尼力所做的功,求得转子叶片的模态气动阻尼比。建立了叶片在气流激励下的振动响应分析方法,基于气动激振力和叶片模态气动阻尼比,采用模态叠加法分析叶片振动响应。使用该方法，针对发动机中1.5级压气机转、静子叶排模型，计算了转子叶片在真实流场中的气动激振力、前8阶模态气动阻尼比以及在气动激振力与气动阻尼共同作用下转子叶片的振动响应，振动应力达到100 MPa。
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| 关 键 词： | 叶片 流固耦合 气动激振力 气动阻尼 振动响应 |
| 收稿时间： | 2020/6/20 0:00:00 |
Method of blade vibration response analysis under airflow excitation |
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| TIAN Shaojie,QI Wenkai,XU Zhenghua.Method of blade vibration response analysis under airflow excitation[J].Journal of Aerospace Power,2021,36(4):826-838. |
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| Authors: | TIAN Shaojie QI Wenkai XU Zhenghua |
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| Affiliation: | College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China |
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| Abstract: | In order to study the method of blade vibration response analysis under airflow excitation, the aerodynamic excitation force prediction method was established. The nonlinear harmonic method was used to conduct three-dimensional unsteady flow analysis of the blades, obtain the fluctuating pressure on the blade surface, compile the flow-solid conversion program, and calculate the aerodynamic excitation force on the blade. The aerodynamic damping analysis method for blades was established. Based on the energy method and the weak coupling analysis method, the fluid-solid weak coupling analysis was carried out for blades and flow fields. The aerodynamic negative work done by aerodynamic forces on moving blades was equivalent to the work done by viscous damping force, and the modal aerodynamic damping ratio of rotor blades was obtained. The vibration response analysis method of blade excited by airflow was established, and based on aerodynamic excitation force and modal aerodynamic damping ratio of blade, modal superposition method was adopted. Using this method, the aerodynamic excitation force, the modal aerodynamic damping ratio of the first eight modes and the vibration response of the rotor blade under the combined action of the aerodynamic excitation force and the aerodynamic damping were calculated for the rotor stator blade array model of the 1.5-stage compressor in the engine. The results showed that the vibration stress reached 100 MPa. |
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| Keywords: | blade fluid-solid coupling aerodynamic excitation force aerodynamic damping vibration response |
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