| 苑旺1，2，申秀丽1，2，董少静1，2.基于拓扑优化的曲边轮廓锯齿叶冠结构设计[J].航空发动机,2019,45(4):32-37 |
| 基于拓扑优化的曲边轮廓锯齿叶冠结构设计 |
| Structure Design of Curved Profile Zigzag Shroud Based on Topology Optimization |
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| DOI： |
| 中文关键词: 锯齿叶冠 拓扑优化 应力水平 振动特性 航空发动机 |
| 英文关键词:zigzag shroud topology optimization stress level vibration characteristics aeroengine |
| 基金项目: |
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| 中文摘要: |
| 针对轻质异形冠结构设计问题，提出了基于结构强度和振动分析的锯齿叶冠轮廓切除原则，采用拓扑优化确定了锯齿
叶冠2 维切除线，通过有限元计算得出叶冠优化后对叶盘结构典型部位应力水平、振动特性的影响。静强度计算结果表明：叶冠优
化后在叶身与上、下缘板连接处Von-Mises 应力分别降低16.1%、5.6%，在叶冠“Z”形凹口处Von-Mises 应力降低24.5%，去除的叶冠
质量占叶片质量的2.4%；模态分析和谐响应分析结果表明：叶冠优化后对叶盘结构振动特性不产生负面影响，保证了叶冠的阻尼减
振作用。 |
| 英文摘要: |
| In view of the structural design problem of the light-weight special-shaped shroud，the contour cutting principle of the
zigzag shroud was put forward based on the structural strength and the vibration analysis. The two-dimension resecting line of the zigzag
shroud was determined by the topology optimization. Through the finite element calculation，the influence of the optimized shroud on the
stress level and vibration characteristics of the typical parts of the blade disk structure was obtained. The results of static strength
calculation show that the Von-Mises stress decreases by 16.1% and 5.6% respectively at the junction between the blade and the upper and
lower listrium after the optimization of the shroud. The Von-Mises stress decreases by 24.5% at the "Z" notch of the shroud，and the weight
of the removed shroud accounts for 2.4% of the blade mass. The results of modal analysis and harmonic response analysis show that there is
no negative influence on the vibration characteristics of the blade disk structure after the optimization of the shroud，and the damping effect
of the shroud is guaranteed.
0 引言
现代航空航天用燃气涡轮发动机的涡轮转子叶
片常采用锯齿形阻尼叶冠[1-2]。相邻叶片的叶冠抵紧后
可以减小叶片的扭曲变形和弯曲变形，增强叶片的刚
性[3]。但是叶冠的使用也带来一些问题：叶冠位于涡轮
转子半径最大处，在高转速下，对叶根和轮盘产生较
大的离心载荷[4]；叶冠本身也会发生故障[5-7]；PSM 公
司R.Seleski 等[8]研究了一系列叶冠掉角故障后，提出
在叶冠结构形式设计中可以考虑将尖角 |
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