航空发动机转子叶片扰流激振设计及试验研究

杨正兵; 李京; 李光辉; 胥奇

doi:10.13224/j.cnki.jasp.20230041

航空发动机转子叶片扰流激振设计及试验研究

doi: 10.13224/j.cnki.jasp.20230041

杨正兵^{1, 2},
李京³,
李光辉²,
胥奇^3,*, ,

1.
西北工业大学动力与能源学院，西安 710072
2.
中国航发四川燃气涡轮研究院，成都 610500
3.
西南交通大学力学与航空航天学院，成都 611756

基金项目: 装发预研项目（7301509）；国家自然科学基金（12072292）；四川省科技计划重点研发项目（2022YFG0083）

详细信息

作者简介:
杨正兵（1985-），男，高级工程师，博士生，主要从事振动试验技术研究

通讯作者:
胥奇（1987-），男，副教授，博士，主要从事结构动力学、振动控制研究。E-mail：xuqi@swjtu.edu.cn

中图分类号: V21
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- 文章访问数: 17
- HTML浏览量: 3
- PDF量: 6
- 被引次数: 0
出版历程
- 收稿日期: 2023-01-29
- 网络出版日期: 2023-10-27

Design and experimental study on turbulence excitation of aeroengine rotor blade system

YANG Zhengbing^{1, 2},
LI Jing³,
LI Guanghui²,
XU Qi^{3,*
, ,}

1.
School of Power and Energy， Northwestern Polytechnical University，Xi’an 710072，China
2.
Sichuan Gas Turbine Establishment， Aero Engine Corporation of China，Chengdu 610500，China
3.
School of Mechanics and Aerospace Engineering， Southwest Jiaotong University，Chengdu 610031，China

摘要

摘要:
为了研究转子叶片共振状态下的动力学参数特征，提出一种基于转子叶片系统扰流激励共振的方法。通过转子系统和扰流柱的结构设计和合理布局，采用双向流固耦合计算方法，仿真分析了不同工况下叶片的动态响应特性，实现了目标转速范围内转子叶片在不需要外加激励源的条件下出现明显1阶共振。试验研究表明：若激励气体压力变大，能明显导致叶片动应变上升；同时较慢的转子升速速率也会导致叶片动应变增加。因此，试验中可通过调节激励气体压力和转子升速速率对叶片动态响应进行控制。该研究工作为有效提高试验这为高速旋转状态下转子叶片共振时刻的动应变、叶尖振幅、疲劳特性研究提供了途径。
- 转子叶片系统 /
- 扰流激励 /
- 共振 /
- 动应变 /
- 流固耦合
Abstract:
To study the parametric resonance characteristics of rotor blade systems, a method based on turbulent excitation was proposed. Through proper structure design and layout of the rotor system and turbulent column, and by using the fluid-solid coupling calculation method, the dynamical characteristics of the blade responses under different working conditions were simulated and analyzed, and significant first-order resonance of the rotor blades within the target rotation velocity range was achieved, even without the need of extra excitations. During the experimental verification, the dynamic responses of the rotor blade system can be greatly enlarged by increasing the turbulent excitation pressure. Similarly, slow speed-up rate of the rotor blade system also increased the dynamic responses of the system. Hence via proper turbulent excitation pressure and speed-up rate, the blade dynamical response can be effectively controlled. This work can provide a technical support for the study of dynamical strain, blade tip amplitude, and fatigue characteristics of the resonant rotor blade system at high rotation velocities.
- rotor blade system /
- turbulent excitation /
- resonance /
- dynamical strain /
- fluid-solid coupling

HTML

图 1 叶盘有限元模型

Figure 1. Finite element model of a blisk

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图 2 转子叶片第1阶振型

Figure 2. First order mode shape of rotor blade system

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图 3 叶片共振转速图

Figure 3. Campbell chart of rotor blade system

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图 4 扰流激励装置结构图

Figure 4. Sketch of turbulent excitation setup

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图 5 计算域

Figure 5. Computational domain

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图 6 转子变形云图

Figure 6. Displacement distribution of rotor blade system

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图 7 转子应力云图

Figure 7. Stress distribution of rotor blade system

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图 8 叶根应力时间历程图

Figure 8. Time history of stress of blade root

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图 9 叶根应力的快速傅里叶变换

Figure 9. Fast Fourier transformation of stress of blade root

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图 10 试验件结构

Figure 10. Experimental setup

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图 11 转子叶片应变测点位置

Figure 11. Test point of strain of rotor blade system

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图 12 动应变响应幅值

Figure 12. Dynamic strain response amplitude

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图 13 不同升速速率叶片动应变变化曲线

Figure 13. Blade dynamical strain at different speed-up rates

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表 1 叶片1阶固有频率计算结果

Table 1. Calculated first mode frequencies of rotor blade system

工况/（r/min）	动频/Hz	静频/Hz
6000	814	800
12000	838	800
15000	856	800

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表 2 有限元和试验模态频率

Table 2. Mode frequencies of FEM analysis and experiments

工况/（r/min）	动频（无气体激励）/Hz	动频（含气体激励）/Hz	动频数据相对误差/%	试验/Hz	试验数据相对误差/%
6000	814	781.3	4	804	1.2
12000	838	813.8	2	832	0.7
15000	856	854.5	0.1

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表 3 不同激励气体压力下叶片动应变响应

Table 3. Blade dynamical strain at different turbulent excitation pressure

气激压力/MPa	动应变/με
0	721
0.4	1086
0.57	1646
0.72	2069

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表 4 安装与拆除扰流柱状态叶片动应变响应

Table 4. Blade dynamical strain of mounting/dismantling turbulent excitation columns

叶片动应变/με	共振点/（r/min）
叶片动应变/με	6000～6100	12000～12200
安装扰流柱	753	1420
拆除扰流柱	115	183

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