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The Impact of Blade and Material Damping in Turbine Blades

机译:叶片和叶片材料阻尼对涡轮叶片的影响

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A method of determining equivalent viscous damping ratio for different rotational speeds and modes as a function of displacement or strain at a reference point in a blade is presented. This method can be adopted using a suitable finite element code, e.g., ANSYS or ABAQUS. The friction damping concept is widely used to reduce resonance stresses in turbomachines. A friction damper has been designed for high pressure turbine stage of a turbojet engine. The objective of this work is to find out effectiveness of the damper while minimizing resonant stresses for sixth and ninth engine order excitation of first flexure mode. The capability to assess damping in the blade from finite element codes avoids costly tests at the initial stages of design.
机译:提出了一种根据叶片中参考点处的位移或应变确定不同转速和模式的等效粘性阻尼比的方法。可以使用适当的有限元代码(例如ANSYS或ABAQUS)采用此方法。摩擦阻尼概念被广泛用于减少涡轮机中的共振应力。摩擦阻尼器已经被设计用于涡轮喷气发动机的高压涡轮级。这项工作的目的是在最大程度地减小第一挠曲模式的第六和第九发动机阶励磁的共振应力的同时,找出阻尼器的有效性。通过有限元代码评估叶片中的阻尼的能力避免了在设计初期就进行昂贵的测试。

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