航空发动机风扇转子叶片抗鸟撞改进设计

汪松柏; 牛潇; 霍嘉欣; 张震相; 江柏均; 刘昭威

doi:10.13224/j.cnki.jasp.20230494

航空发动机风扇转子叶片抗鸟撞改进设计

doi: 10.13224/j.cnki.jasp.20230494

中国航发四川燃气涡轮研究院，成都 610500

基金项目: 四川省科技计划项目（2021YFG0182，2021ZDZX0003）

详细信息

作者简介:
汪松柏（1989-），男，高级工程师，博士生，主要从事航空发动机压气机设计研究。E-mail：wsb_buaa@163.com

中图分类号: V231.1
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- 文章访问数: 215
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- 被引次数: 0
出版历程
- 收稿日期: 2023-07-29
- 网络出版日期: 2023-10-25

Improved design for anti-bird impact of aero-engine fan rotor blades

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

摘要

摘要:
为提高航空发动机风扇转子叶片抗鸟撞能力，基于光滑粒子流体动力学（SPH）方法及LS-DYNA显式动力学分析软件对风扇转子叶片的抗鸟撞能力进行评估，分析了不同关键设计参数对气动性能和叶片抗鸟撞性能的影响。结果表明：真实鸟体撞击风扇转子叶片后，主要造成叶片前缘变形、卷边和撕裂。风扇气动性能随叶片前缘半径增大而降低，当前缘半径超过0.25 mm后，风扇的稳定裕度急剧下降；最大厚度位置后移对风扇气动性能有益，但风扇转子叶片抗鸟撞能力下降。在保证风扇气动性能的前提下，通过合理选取设计参数，对风扇转子叶片进行改进设计，改进后叶片的抗鸟撞能力由30 g提高到50 g，抗鸟撞能力得到明显提升。
- 风扇转子叶片 /
- 光滑粒子流体动力学（SPH） /
- 鸟撞 /
- 改进设计 /
- 气动性能
Abstract:
In order to improve the bird impact resistance of aero-engine fan rotor blades, the smoothed particle hydrodynamics (SPH) method and LS-DYNA software were used to evaluate the bird impact resistance of fan rotor blades, and the effects of key design parameters on aerodynamic performance and bird impact resistance were analyzed. The results indicated that the realistic bird impact mainly caused deformation, curling, and tearing of rotor blade leading edge. The aerodynamic performance decreased with the increase of the leading edge radius, the stability margin sharply decreased as the leading edge radius was larger than 0.25 mm. The maximum thickness position moving afterward was beneficial for aerodynamic performance, while the bird impact resistance decreased. By selecting reasonable design parameters to maintain the aerodynamic performance, the fan rotor blade design was improved. The anti-bird ability of fan rotor blade had been significantly increased from 30 g to 50 g.
- fan rotor blade /
- smoothed particle hydrodynamics (SPH) /
- bird impact /
- improved design /
- aerodynamic performance

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图 1 鸟体的SPH模型

Figure 1. SPH model for bird

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图 2 鸟撞试验后风扇前缘变形和损伤

Figure 2. Deformation and damage of fan leading edge after the bird impact test

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图 3 风扇叶片鸟撞有限元模型

Figure 3. Bird impact finite element model for fan blade

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图 4 风扇转子叶片鸟撞后的有效塑性应变

Figure 4. Effective plastic strain distribution of the fan rotor blades after bird compact

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图 5 数值模拟和试验结果的展向变形对比

Figure 5. Span deformation comparison between numerical simulation and experimental results

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图 6 风扇转子叶片结构

Figure 6. Blade structure of the fan rotor

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图 7 前缘半径对风扇气动性能的影响

Figure 7. Effect of leading edge radius on fan performance

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图 8 最大厚度位置对风扇气动性能的影响

Figure 8. Effect of maximum thickness position on fan performance

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图 9 90%叶高截面静熵的对比

Figure 9. Comparison of static entropy at 90% span

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图 10 塑性应变大于0.1区域的叶片表面积随最大厚度位置变化

Figure 10. Surface area of blade with plastic strain greater than 0.1 changing with the maximum thickness position

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图 11 最大厚度位置为0.55时鸟撞后叶片的塑性应变

Figure 11. Plastic strain of blades after bird impact on 0.55 maximum thickness position

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图 12 前缘半径沿叶高方向的分布

Figure 12. Distribution of leading edge radius along fan blade height

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图 13 最大厚度位置沿叶高方向的分布

Figure 13. Distribution of maximum thickness position along fan blade height

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图 14 风扇叶片改进前后叶型的对比

Figure 14. Comparison of fan blades profile before and after improvement

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图 15 风扇部件改进前后的试验特性对比

Figure 15. Comparison of fan experimental performance before and after improvement

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图 16 50 g鸟体撞击改进后风扇转子叶片的全过程模拟

Figure 16. Process simulation of 50 g bird impact with improved design of fan rotor blade

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表 1 TC4材料参数^[21]

Table 1. Material parameters of TC4^[21]

参数		数值
基本材料性能	密度ρ/（kg/m³）	4440
	切变模量G/GPa	44
	弹性模量E/GPa	115
	泊松比ν	0.34
	熔点T_metl/℃	1640
	比定压热容c_p/（J/（kg·℃））	611
Johnson-Cook 本构模型	A/MPa	862.40
	B/MPa	1084.64
	n	0.341
	C	0.01823
	m	0.76728
	D₁	−0.09
	D₂	0.27
	D₃	0.48
	D₄	0.014
	D₅	3.87
Gruneisen 状态方程	C/（m/s）	5130
	S₁	1.028
	S₂	0
	S₃	0
	γ₀	1.23
	$a$	0.17

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表 2 鸟体的材料参数^[22]

Table 2. Material parameters of bird^[22]

参数	数值
密度/（kg/m³）	900
弹性模量/GPa	10.0
泊松比	0.3
屈服应力/MPa	1.0
切变模量/MPa	5.0
失效应变	1.25

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表 3 风扇叶片改进前后抗鸟撞能力对比

Table 3. Comparison of bird impact resistance of fan blades before and after improvement

参数	数值
参数	原始	改进后	降低幅度/%
叶片展向最大变形量/mm	25.9	16.7	35.5
变形叶片数	10	6	40
塑性应变大于0.1 区域的叶片表面积/mm²	587	318	45.8

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