旋转叶片气体激振试验载荷影响因素分析

王怀涛; 耿卫民; 高鹏; 郜伟强; 汤紫薇

doi:10.13224/j.cnki.jasp.20250376

旋转叶片气体激振试验载荷影响因素分析

doi: 10.13224/j.cnki.jasp.20250376

中国航发四川燃气涡轮研究院，成都 610500

详细信息

作者简介:
王怀涛（1992-），男，工程师，硕士生，主要从事航空发动机强度传动试验研究

中图分类号: V231.1
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出版历程
- 收稿日期: 2025-08-11
- 网络出版日期: 2026-10-07

Analysis on factors affecting load in air excitation tests of rotating blades

Sichuan Gas Turbine Establishment，Aero Engine Corporation of China，Chengdu 610500，China

摘要

摘要:
为研究航空发动机叶片在旋转状态下的气体激振响应特性，基于叶盘工作中所受尾流激振载荷的谐波分解原理，建立基于立式轮盘试验器的旋转叶片气体激振试验平台，提出一种融合仿真与试验的气体激振试验载荷分析流程。以某压气机叶盘为例开展旋转状态下振动特性试验研究，系统探究了扰流器轴向距离与舱压对叶片动应变响应的影响规律。试验及分析结果表明：该试验平台能有效模拟旋转叶片所受的周期性气体激振，成功获得压气机叶片的前3阶动频；扰流器在空间上的分布决定旋转叶片所受激振载荷的主要阶次，应变幅值随扰流器与叶片轴向距离呈非线性变化，并在10～12 mm区间存在最优值；舱压在10 kPa范围内，叶片应变幅值与舱压呈正相关。
- 高压压气机 /
- 旋转叶片 /
- 气体激振 /
- 尾流激振 /
- 激振载荷
Abstract:
To investigate the air excitation response characteristics of aero-engine blades under rotating conditions, an air excitation test platform for rotating blades was established based on the vertical disk tester and the harmonic decomposition principle of wake excitation loads experienced during blisk operation. An analytical process for air excitation test loads integrating simulation and experiment was proposed. Taking a compressor blisk as an example, an experimental study on vibration characteristics under rotating conditions was conducted, systematically exploring the influence laws of the axial distance of the flow disturber and the chamber pressure on the dynamic strain response of the blades. The test and analysis results indicated that: this test platform effectively simulated the periodic air excitation experienced by rotating blades, and the first three dynamic frequencies of the compressor blades were successfully obtained; the spatial distribution of the flow disturber determined the main orders of the excitation load on the rotating blades, and the strain response amplitude changed nonlinearly with the axial distance between the flow disturber and the blades, with an optimal value within the 10–12 mm range; within the chamber pressure range of 10 kPa, the blade strain response amplitude was positively correlated with the chamber pressure.
- high-pressure compressor /
- rotating blade /
- air excitation /
- wake excitation /
- excitation loads

HTML

图 1 气体激振载荷分析流程图

Figure 1. Flowchart of air excitation load analysis

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图 2 气体激振试验平台剖视图

Figure 2. Cross-section of air excitation test platform

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图 3 气体激振试验装置

Figure 3. Air excitation test apparatus

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图 4 气体激振试验平台的气体流向

Figure 4. Air flow direction of air excitation test platform

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图 5 扰流器实物图

Figure 5. Photograph of the disturbance device

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图 6 叶片前3阶固有频率模态（K=7）

Figure 6. The first three natural modes of the blade （K=7）

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图 7 叶片坎贝尔图

Figure 7. Campbell diagram of the blade

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图 8 叶片振动响应幅值图

Figure 8. Amplitude response diagram of blade vibration

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图 9 叶片振动频谱图

Figure 9. Frequency spectrum diagram of blade vibration

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图 10 叶背压力分布

Figure 10. Pressure distribution on the blade pressure side

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图 11 4#叶片背面时变压力分布

Figure 11. Time-varying pressure distribution on the 4# blade pressure side

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图 12 振动响应受轴向距离影响的拟合图

Figure 12. Fitting diagram of vibration response affected by axial distance

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表 1 叶片前3阶固有频率对比

Table 1. Comparison of the first three natural frequencies of the blade

阶次	固有频率/Hz
阶次	计算值	实测最大值	最大误差
1	630	640	10
2	1498	1553	55
3	2126	2236	110

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表 2 舱压对激振载荷的影响

Table 2. Influence of chamber pressure on excitation loads

舱压/kPa	微应变/10⁻⁶
舱压/kPa	1#叶片	2#叶片	3#叶片	4#叶片	5#叶片
2	356.6	344.4	380.3	346.4	419.8
4	598.3	591.5	485.7	534.5	602.9
6	865.2	895.3	788.1	790.8	810.4
8	1014.6	1043.9	941.4	963.7	940.9
10	1127.9	1183.4	1014.7	1057	1067.7

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