风扇叶片非同步振动研究

吕彪; 孟卫华; 陈剑; 张鹏; 侯明

doi:10.13224/j.cnki.jasp.20240601

风扇叶片非同步振动研究

doi: 10.13224/j.cnki.jasp.20240601

中国航发湖南动力机械研究所，湖南株洲 412002

详细信息

作者简介:
吕彪（1989-），男，高级工程师，硕士，主要从事航空发动机结构振动及转子动力学方面的研究。E-mail：905852157@99.com

通讯作者:
孟卫华（1987-），男，高级工程师，硕士，主要从事航空发动机结构强度方面的研究。E-mail：mengweihua1234@163.com

中图分类号: V231.1
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出版历程
- 收稿日期: 2024-08-31
- 网络出版日期: 2025-01-09

Non-synchronous vibration of fan blade

Hunan Aviation Power Plant Research Institute，Aero Engine Corporation of China，Hunan Zhuzhou 412002，China

摘要

摘要:
为了排查前掠风扇叶片低转速性能录取试验过程中发生疲劳断裂的原因，并对风扇叶片改进设计，仿真分析排除了叶片共振和颤振致破坏，高周疲劳分析得到风扇叶片2阶模态危险点与裂纹起始位置吻合，分析认为在低转速下风扇叶片叶尖处存在不稳定气流，产生6.5倍转频激振力，激起了风扇叶片2阶固有模态，进而引发叶片非同步振动。叶尖振幅测量和动态压力测量试验验证了分析结果，在断裂故障转速，动态压力信号出现多个非同步频率，同时风扇叶尖振幅3.7 mm，裂纹起始位置振动应力671.2 MPa。风扇叶片前掠过大，导致前掠部分局部弯曲模态频率低，易被激起共振。改进措施是切除叶片部分前掠，消除前掠部分局部弯曲模态，试验验证改进措施有效。对前掠小展弦比风扇叶片规避非同步振动设计有借鉴意义。
- 风扇叶片 /
- 前掠 /
- 非同步振动 /
- 疲劳断裂 /
- 不稳定气流 /
- 动态压力 /
- 叶尖振幅
Abstract:
The fatigue fracture occurred during the low speed performance test of swept-forward fan blades. The cause was investigated to improve the design. The damage caused by blade resonance and flutter was excluded through simulation analysis. The high-cycle fatigue analysis showed that the second-order modal danger point of the fan blades was consistent with the crack initiation position. The analysis suggested that the unsteady flow at the tip generated 6.5 times the rotational frequency exciting force, which stimulated the second-order natural mode of the fan blades. Blade tip amplitude and dynamic pressure measurement experiments verified the analysis results. At the fracture speed, the dynamic pressure signal exhibited multiple non-synchronous frequencies. The amplitude of the fan blade tip was 3.7 mm, and the vibration stress at the crack initiation position was 671.2 MPa. The fan blade skimmed forward greatly, resulting in low local bending mode frequency of the forward-swept part, which was easy to be resonated. Blade improvement measures were taken to remove partial forward-swept of the blade and eliminate the local bending mode. The experiment verified the effective improvement measures. This scheme is of reference significance for the design of forward swept small aspect ratio fan blades to avoid asynchronous vibration.
- fan blade /
- forward-swept /
- non-synchronous /
- fatigue crack /
- unsteady flow /
- dynamic pressure /
- blade tip vibration amplitude

HTML

图 1 振动时域图和频谱图

Figure 1. Time domain and frequency domain of vibration

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图 2 叶片断裂情况

Figure 2. Blade fracture condition

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图 3 叶片断口形貌

Figure 3. Blade fracture morphology

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图 4 扩展区疲劳条带

Figure 4. Extended zone fatigue striation

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图 5 已知激振源下风扇叶片坎贝尔图

Figure 5. Fan blade Campbell diagram with known excitation source

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图 6 风扇叶片1阶振型及振动应力分布

Figure 6. Fan blade first order vibration mode and vibration stress distribution

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图 7 风扇叶片3阶振型及振动应力分布

Figure 7. Fan blade third order vibration mode and vibration stress distribution

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图 8 各阶模态高周疲劳储备最小位置示意

Figure 8. Location of minimum fatigue store of high cycle fatigue reserve for each mode

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图 9 可能激振源下叶片坎贝尔图

Figure 9. Fan blade Campbell diagram with unknown excitation source

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图 10 测量位置示意图

Figure 10. Sketch of the testing rig

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图 11 风扇叶片叶尖振幅测量结果

Figure 11. Measurement results of blade tip amplitude of fan blades

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图 12 动态压力时域图和谱阵图

Figure 12. Time domain and spectrograms of unsteady pressure

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图 13 风扇叶片前掠部分切除位置

Figure 13. Cutting position of the forward swept part of the fan blade

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图 14 风扇叶片切角前后2阶振型对比

Figure 14. Comparison of second order vibration mode before and after fan blade trimming

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图 15 风扇叶片切角前后2阶振动应力对比

Figure 15. Comparison of second order vibration stress distribution before and after fan blade trimming

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图 16 风扇叶片切角后动态压力时域图和谱阵图

Figure 16. Time domain and spectrograms of unsteady pressure of trimmed fan blades

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图 17 风扇叶片切角后叶尖振幅测量结果

Figure 17. Measurement results of blade tip amplitude of trimmed fan blades

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表 1 风扇叶片切角前后频率对比

Table 1. Frequency of original and trimmed fan blade

阶次频率/Hz 变化率/%

初始状态切后状态

1 646 654 1.2

2 1313 1472 12.1

3 1477 1600 8.3

4 2160 2395 10.9

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