转静干涉对转子叶片颤振特性的影响
发布时间：2018-12-24 10:40
【摘要】：在不同气动工况、不同几何模型下,采用自行开发程序对全环多排的高压压气机进行了流固耦合数值模拟,分析了进口导流叶片(IGV,以下简称导叶)对转子叶片颤振稳定性的影响。通过对气动弹性标准算例4的数值模拟验证了程序在颤振领域的有效性。针对导叶-转子模型和单转子模型,考察了近堵塞点、近设计点和近失速点3个工况下,节径变化对叶片颤振稳定性的影响,给出了气动弹性最不稳定状态对应的叶片振动形式。通过对比发现,导叶作用随工况而异,近堵塞点导叶使得转子1阶弯曲模态气动阻尼提高130.63%。研究表明:导叶引起的非定常压力波反射增强了转子叶片的非定常压力扰动幅值,使得弯曲振型的颤振稳定性增强。基于单转子模型的颤振分析给出了不准确的气动阻尼值。
[Abstract]:Under different aerodynamic conditions and different geometry models, the fluid-solid coupling numerical simulation of high-pressure compressor with full ring and multiple rows was carried out by using self-developed program, and the inlet guide vane (IGV,) was analyzed. The influence of guide vane on the flutter stability of rotor blade. The effectiveness of the program in flutter field is verified by numerical simulation of Aeroelastic standard example 4. For guide vane rotor model and single rotor model, the effects of nodal diameter variation on blade flutter stability were investigated under three operating conditions: near clogging point, near design point and near stall point. The vibration form of blade corresponding to the most unstable state of Aeroelasticity is given. By comparison, it is found that the guide vane action varies with the working conditions, and the aerodynamic damping of the rotor in the first order bending mode is increased by 130.63 because of the near clogging point guide vane. The results show that the unsteady pressure wave reflection caused by the guide blade enhances the amplitude of the unsteady pressure disturbance of the rotor blade and enhances the flutter stability of the bending mode. Based on the flutter analysis of a single rotor model, an inaccurate aerodynamic damping value is given.
【作者单位】： 先进航空发动机协同创新中心;北京航空航天大学能源与动力工程学院;
【分类号】：V232.4
本文编号：2390520
[Abstract]:Under different aerodynamic conditions and different geometry models, the fluid-solid coupling numerical simulation of high-pressure compressor with full ring and multiple rows was carried out by using self-developed program, and the inlet guide vane (IGV,) was analyzed. The influence of guide vane on the flutter stability of rotor blade. The effectiveness of the program in flutter field is verified by numerical simulation of Aeroelastic standard example 4. For guide vane rotor model and single rotor model, the effects of nodal diameter variation on blade flutter stability were investigated under three operating conditions: near clogging point, near design point and near stall point. The vibration form of blade corresponding to the most unstable state of Aeroelasticity is given. By comparison, it is found that the guide vane action varies with the working conditions, and the aerodynamic damping of the rotor in the first order bending mode is increased by 130.63 because of the near clogging point guide vane. The results show that the unsteady pressure wave reflection caused by the guide blade enhances the amplitude of the unsteady pressure disturbance of the rotor blade and enhances the flutter stability of the bending mode. Based on the flutter analysis of a single rotor model, an inaccurate aerodynamic damping value is given.
【作者单位】： 先进航空发动机协同创新中心;北京航空航天大学能源与动力工程学院;
【分类号】：V232.4
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