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首页> 外文期刊>Journal of Engineering for Gas Turbines and Power >Study on the Reduction of the Resonant Stress of Turbine Blades Caused by the Stage Interaction Force (Simultaneous Optimization of Blade Resonant Stress and Amount of Unbalance)
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Study on the Reduction of the Resonant Stress of Turbine Blades Caused by the Stage Interaction Force (Simultaneous Optimization of Blade Resonant Stress and Amount of Unbalance)

机译：阶段相互作用力引起的涡轮叶片谐振应力的减少研究（同时优化叶片共振应力和不平衡量）

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Although the bladed disks of turbomachinery are nominally designed to be cyclically symmetric (tuned system), the vibration characteristics of individual blades on a disk vary slightly owing to manufacturing tolerances, deviations in material properties, wear during operation, etc. These small variations break the cyclic symmetry and split eigenvalue pairs. Actual bladed disks with small variations are called mistuned systems. The resonant stress on a mistuned bladed disk may become large and cause a blade failure due to high cycle fatigue. Especially for a bladed disk with a free-standing blade structure, it is essential to use a sufficiently large safety factor at the design stage, considering the mistuning effect. Traditionally, blade designers have adopted various countermeas-ures to reduce the resonant stress at the design stage. Besides the countermeasures adopted in blade design, for a variable speed engine, which cannot avoid resonance, it is thought that a practical optimization method for a mistuned system (bladed disk with a free-standing blade structure) is to sort the blades so that the resonant stress is minimized. In this study, a simultaneous method for optimizing the blade resonant stress and the amount of unbalance causing rotor vibration is proposed. In this method, first, the natural frequencies and weights of all blades on a disk are measured. Then, a mistuned system is assembled and the analysis model is generated. Next, the resonant stress and the amount of unbalance in the mistuned system are analyzed. To reduce the computation time, the reduced-order model known as fundamental mistuning model (FMM) is used to calculate the resonant stress in the mistuned system. The analyses of the resonant stress and the amount of unbalance are carried out repeatedly, sorting the blades on the disk, and the optimal solution is explored using Monte Carlo simulations (MCS) or discrete differential evolution (DDE). As an example, a mistuned bladed disk of an aero-engine was analyzed, and the validity of the proposed method was verified.
机译：虽然涡轮机的叶片磁盘是名义上被设计成循环对称（调谐系统），但是由于制造公差，材料特性偏差，操作期间佩戴等，磁盘上的各个叶片的振动特性略有不同。这些小变化打破了这些小变化循环对称和分裂特征值对。具有小变化的实际叶片磁盘称为雾化系统。由于高循环疲劳，雾化盘上的谐振应力可能变大并导致叶片失效。特别是对于具有独立刀片结构的叶片盘，考虑到迷雾效果，必须在设计阶段使用足够大的安全系数。传统上，刀片设计师采用了各种抵抗utes，以减少设计阶段的共振应力。除了刀片设计中采用的对策，对于无法避免共振的可变速度发动机，据认为，迷失的系统（带独立刀片结构的叶片盘的实用优化方法是对刀片进行排序共振应力最小化。在该研究中，提出了一种用于优化叶片谐振应力的同时方法和导致转子振动的不平衡量。在该方法中，首先测量磁盘上所有叶片的自然频率和重量。然后，组装雾化系统，并生成分析模型。接下来，分析了迷雾系统中的共振应力和不平衡的量。为了减少计算时间，使用称为基本迷雾模型（FMM）的衰减级模型用于计算雾化系统中的谐振应力。反复分析谐振应力和不平衡量的分析，将叶片上的叶片分类在盘上，并且使用蒙特卡罗模拟（MCS）或离散差分演进（DDE）探索最佳解决方案。例如，分析了空闲发动机的迷雾叶片盘，验证了该方法的有效性。

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  • 来源
    《Journal of Engineering for Gas Turbines and Power》 |2021年第6期|061022.1-061022.10|共10页
  • 作者

    Yasutomo Kaneko; Toshio Watanabe; Tatsuya Furukawa;

  • 作者单位

    Mechanical Engineering and Robotics Course Ryukoku University 1-5 Yokotani Oe-cho Seta Otsu Shiga 520-2194 Japan;

    Mitsubishi Heavy Industries Ltd. 2-1-1 Shinhama Arai-cho Takasago Hyogo 676-8686 Japan;

    Mitsubishi Power Ltd. 2-1-1 Shinhama Arai-cho Takasago Hyogo 676-8686 Japan;

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