航空发动机双转子模态动平衡方法研究

周旋; 黄江博; 廖明夫; 况钧耀

doi:10.13224/j.cnki.jasp.20230275

航空发动机双转子模态动平衡方法研究

doi: 10.13224/j.cnki.jasp.20230275

西北工业大学动力与能源学院，西安 710129

基金项目: 国家科技重大专项（2017-Ⅳ-0001-0038）

详细信息

作者简介:
周旋（1984-），女，博士生，主要从事转子动力学方面的研究

通讯作者:
廖明夫（1960-），男，教授，博士，主要从事航空发动机转子动力学、风能工程研究。E-mail：mfliao@nwpu.edu.cn

中图分类号: V231.96
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- 被引次数: 0
出版历程
- 收稿日期: 2023-04-24
- 网络出版日期: 2023-08-28

Research on mode dynamic balancing method of dual-rotor aero-engine

School of Power and Energy，Northwestern Polytechnical University，Xi’an 710129，China

摘要

摘要:
针对双转子系统低压激励和高压激励振动模态的正交性受转速比影响，提出了以定转速比转子模态替代实际工作转速线下的转子模态进行双转子系统N₁+N₂和N₁+N₂+4平面模态动平衡的方法。推导了N₁+N₂和N₁+N₂+4平面模态动平衡法的平衡条件，给出了模态不平衡质量和正交校正质量组的计算式，并以某型航空发动机双转子系统为例，给出了N₁+N₂模态动平衡方法平衡各阶模态的过程。最后在双转子实验系统上进行了动平衡验证实验，实验研究发现在定转速比的条件下动平衡的减振效果最大可达72.4%；当高、低压转子转速控制率为实际工作转速线时，在工作转速范围内，各阶临界转速处的振动幅值总量都降低到120 μm以下，满足设计要求。实验结果表明提出的双转子航空发动机模态动平衡方法是可行的。
- 模态动平衡 /
- 不平衡响应 /
- 航空发动机 /
- 双转子系统 /
- 转速比
Abstract:
In view of the dual-rotor system with two sets of vibration modes of low-pressure rotor excitation and high-pressure rotor excitation, the orthogonality of the two vibration modes was affected by the speed ratio, so N₁+N₂ plane and N₁+N₂+4 plane mode dynamic balance method of the dual-rotor system was proposed by replacing the rotor mode under the actual operating speed line with the rotor mode under the constant speed ratio. On the basis of the known modal orthogonality theory of the dual-rotor system, the equilibrium conditions of the two-rotor system N₁+N₂ and N₁+N₂+4 plane mode dynamic balance methods were deduced, and two dynamic balance methods of the calculation equations of the unbalanced mass and the orthogonal correction mass group were given. What’s more, taking a certain type of aero-engine dual-rotor system as an example, the process of balancing each order mode was given by the N₁+N₂ mode dynamic balancing method. Finally, the dynamic balance verification experiment was carried out on the dual-rotor test system. The experimental study found that the vibration reduction effect of dynamic balance method can reach up to 72.4% under the condition of constant speed ratio; when the high and low pressure rotor speed control rate was the actual working speed line in the working speed range, the total vibration amplitude at each critical speed was reduced to below 120 μm, meeting the design requirements. The experimental results showed that the proposed mode dynamic balancing method for the dual-rotor aero-engine is feasible.
- mode dynamic balance /
- unbalanced response /
- aero-engine /
- dual-rotor system /
- speed ratio

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图 1 双转子不平衡分布

Figure 1. Unbalanced distribution of dual-rotor

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图 2 双转子航空发动机模态动平衡流程图

Figure 2. Flow chart of mode dynamic balance of dual-rotor aero-engine

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图 3 双转子实验器实物图

Figure 3. Physical image of the dual-rotor experimental device

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图 4 设计有平衡配重孔的实验器盘部件

Figure 4. Parts of experimental device disk designed with balance weight holes

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图 5 传感器测点排布

Figure 5. Sensor measuring point arrangement

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图 6 高压激励的1阶模态平衡前不平衡响应

Figure 6. Unbalanced response before first-order mode balance of high pressure compressor rotor excitation

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图 7 平衡高压激励1阶模态试重运行

Figure 7. Test weight operation of first-order mode of balanced high pressure excitation

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图 8 平衡高压激励1阶模态配重运行

Figure 8. Counter weight operation of first-order mode of balanced high pressure excitation

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图 9 平衡高压激励1阶模态动平衡前后一倍频响应对比

Figure 9. Comparison of 1× frequency responses before and after balancing first-order mode of high pressure excitation

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图 10 低压激励的1阶模态平衡前不平衡响应

Figure 10. Unbalanced response before first-order mode balance of low pressure compressor rotor excitation

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图 11 平衡低压激励1阶模态试重运行

Figure 11. Test weight operation of first-order mode of balanced low pressure excitation

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图 12 平衡低压激励1阶模态配重运行

Figure 12. Counter weight operation of first-order mode of balanced low pressure excitation

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图 13 平衡低压激励1阶模态动平衡前后一倍频对比

Figure 13. Comparison of 1× frequency responses before and after balancing first-order mode of low pressure excitation

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图 14 双转子系统实际工作转速下运行过程

Figure 14. Operation process of dual-rotor system at actual working speed

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表 1 双转子实验系统测量通道信息

Table 1. Measurement channel information of dual-rotor test system

通道编号	通道信息
CH1	低压风扇竖直
CH2	低压风扇水平
CH3	低压涡轮竖直
CH4	低压涡轮水平
CH5	高压压气机竖直
CH6	高压压气机水平
CH7	高压涡轮水平
CH8	中介轴承水平
CH9	转子系统转速

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表 2 传感器型号与参数

Table 2. Sensor models and parameters

类型	型号	灵敏度	频响范围/kHz
位移	B&K IN-085	8 mV/μm	0～10
速度	B&K VS-080	78 mV/（mm/s）	0.01～1
光电	B&K P-84		0～10

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表 3 双转子实验器模态动平衡所用振型数据

Table 3. Vibration data used in mode balance of dual-rotor experimental device

平衡面	类别	高压激励		低压激励
平衡面	类别	1阶	2阶	1阶	2阶
x₁	无量纲幅值	0.21	0.09	−0.20	0.69
x₁	相位/（°）	−90.5	90.5	90.0	−90.0
x₂	无量纲幅值	0.11	0.14	−0.735	0.18
x₂	相位/（°）	−90.5	91.1	90.0	−90.0
x₃	无量纲幅值	0.18	−0.38	0.22	0.43
x₃	相位/（°）	89.4	89.4	0.6	6.3
x₄	无量纲幅值	−0.79	−0.34	0.03	0.07
x₄	相位/（°）	89.4	89.4	179.3	174.2

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表 4 实验器各通道的转子初始弯曲值

Table 4. Each channel initial bending value of experimental device

通道	幅值/μm	相位/（°）
CH1	20.8	333.3
CH2	20.0	64.8
CH3	13.7	159.5
CH4	16.9	244.9
CH5	36.9	217.5
CH6	31.6	157.4
CH7	15.1	80.8
CH8	17.5	256.7

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