轴向间距对转子叶片颤振特性的影响机理

郑赟; 余永博

doi:10.13700/j.bh.1001-5965.2017.0251

轴向间距对转子叶片颤振特性的影响机理

doi: 10.13700/j.bh.1001-5965.2017.0251

郑赟^{1, 2, ,},
余永博^{1, 2}

1.
先进航空发动机协同创新中心, 北京 100083
2.
北京航空航天大学能源与动力工程学院, 北京 100083

详细信息

作者简介:
郑赟男, 博士, 讲师。主要研究方向:计算流体力学、叶轮机械气动弹性数值模拟

余永博男, 硕士研究生。主要研究方向:叶轮机械气动弹性数值模拟

通讯作者:
郑赟, E-mail: zheng_yun@buaa.edu.cn

中图分类号: V211.6
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出版历程
- 收稿日期: 2017-04-25
- 录用日期: 2017-08-11
- 网络出版日期: 2018-04-20

Influence mechanism of axial spacing on rotor blade flutter characteristics

ZHENG Yun^{1, 2
, ,},
YU Yongbo^{1, 2}

1.
Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100083, China
2.
School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

More Information

Corresponding author: ZHENG Yun, E-mail: zheng_yun@buaa.edu.cn

摘要

摘要:
使用自行开发的非定常流固耦合数值模拟程序，研究了上游叶排影响转子叶片颤振特性的机理，采用影响系数法分析轴向间距影响转子气动弹性稳定性的规律。结果表明：在协调叶栅中，叶片吸力面相邻的叶片振动对转子叶片气动阻尼的大小起决定性作用，其影响甚至超过振动叶片本身的影响；多排环境中，导叶（IGV）对转子叶片气动阻尼最小值的影响最大，并使其对应的节径增大；相邻叶片振动引起的通道变化抑制了导叶对非定常压力波的反射作用；随着轴向间距的减小，导叶对非定常压力波的反射作用减弱了非定常压力波的周向衰减，从而增大了叶片振动的非定常影响范围；在多排环境中使用影响系数法需要测量更多的叶片才能得到较为准确的气动阻尼。
- 轴向间距 /
- 影响系数法 /
- 气动弹性稳定性 /
- 颤振 /
- 气动阻尼
Abstract:
The mechanism of the upstream blade row affecting the flutter characteristics of the rotor blade is studied, using the self-developed unsteady fluid-solid coupling numerical simulation program. The influence coefficient method is used to analyze the effect of axial spacing on the aeroelastic stability of rotor. The results show that the neighboring blade vibration, which adjacent to the certain blade's suction side, determines the value of rotor aerodynamic damping in the tuned cascade, and its effect is even larger than the certain blade vibration itself; in the multi-row environment, inlet guide vanes(IGV) mainly affects the minimum aerodynamic damping of rotor blade, and IGV increases the nodal diameter value of the most unstable point of aeroelasticity; the channel change caused by blade vibration restrains the reflection of IGV on unsteady pressure wave; with the decrease of axial spacing, the range of unsteady influence of blade vibration is obviously increased, since the effect of IGV on the unsteady pressure wave attenuates the circumferential attenuation of unsteady pressure wave; the influence coefficient method needs to measure more blades to obtain more accurate aerodynamic damping in the multi-row environment.
- axial spacing /
- influence coefficient method /
- aeroelastic stability /
- flutter /
- aerodynamic damping

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图 1 转子叶栅几何示意图

Figure 1. Geometric sketch map of rotor cascade

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图 2 导叶-转子叶片单通道网格

Figure 2. IGV-rotor blade single-passage grids

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图 3 叶片表面定常压力系数分布

Figure 3. Distribution of steady pressure coefficient on blade surface

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图 4 不同轴向间距下的气动阻尼系数

Figure 4. Aerodynamic damping coefficient with different axial spacing

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图 5 叶片间相位角为-72°时，单转子各叶片气动阻尼系数分量

Figure 5. Each blade's aerodynamic damping coefficient component of single-rotor at inter blade phase angle equals to -72°

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图 6 不同轴向间距下气动阻尼系数分量

Figure 6. Aerodynamic damping coefficient component with different axial spacing

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图 7 不同叶片数下气动阻尼系数

Figure 7. Aerodynamic damping coefficient with different blade numbers

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图 8 b0表面无量纲非定常气动功、压力幅值和相位

Figure 8. Non-dimensional unsteady aerodynamic work, pressure amplitude and phase on b0 surface

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图 9 b-1表面无量纲非定常气动功、压力幅值和相位

Figure 9. Non-dimensional unsteady aerodynamic work, pressure amplitude and phase on b-1 surface

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表 1 叶片几何和实验参数

Table 1. Blade geometry and experimental parameters

参数	数值
弦长/mm	72
栅距/mm	56.25
安装角/(°)	56.65
振幅/(10^-4m)	3
振动方向/(°)	60.4
振动频率/Hz	149
折合频率	0.118 7

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表 2 边界条件

Table 2. Boundary conditions

参数	数值
进口总压/kPa	160.9
进口总温/K	317.8
出口静压/kPa	101.3
出口气流角/(°)	-71.5
出口等熵马赫数	0.85

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表 3 不同叶片数下气动阻尼系数相对误差

Table 3. Relative error of aerodynamic damping coefficients with different blade numbers

%
叶片编号	Δx/c=10%	Δx/c=15%	Δx/c=30%	Δx/c=50%	Δx/c=70%	Δx/c=90%	Δx/c=150%	单转子
b-1~b0	14.58	18.50	23.31	19.25	13.24	8.40	2.21	0.77
b-1~b1	12.27	13.84	15.77	11.08	6.39	3.09	0.37	0.76
b-2~b2	4.08	5.64	7.42	5.10	2.51	0.81	0.13	2.30
b-3~b3	2.57	1.99	1.44	1.76	1.97	1.84	0.63	0.24
b-5~b5	0.44	0.34	0.03	0.09	0.01	0.11	0.34	0.02

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