GH2787压气机叶片激光-喷丸复合强化疲劳强度提升方法

胡殿印; 王涛; 杜俊良; 陆炜鑫; 毛建兴; 张晓杰; 徐兴伟; 王荣桥

doi:10.13224/j.cnki.jasp.20240017

GH2787压气机叶片激光-喷丸复合强化疲劳强度提升方法

doi: 10.13224/j.cnki.jasp.20240017

胡殿印^{1, 2,},
王涛³,
杜俊良^{1, 4},
陆炜鑫¹,
毛建兴^{1, 2,*, ,},
张晓杰^{2, 3},
徐兴伟⁴,
王荣桥^{2, 3}

1.
北京航空航天大学航空发动机研究院，北京 100191
2.
北京航空航天大学航空发动机结构强度北京市重点实验室，北京 100191
3.
北京航空航天大学能源与动力工程学院，北京 100191
4.
中国航发成都发动机有限公司，成都 610500

基金项目: 国家自然科学基金（52275142）；国家科技重大专项（J2019-Ⅳ-0009-0077）

详细信息

作者简介:
胡殿印（1980-），女，教授，博士，研究领域为航空发动机结构强度及可靠性设计。E-mail：hdy@buaa.edu.cn

通讯作者:
毛建兴（1989-），男，副研究员，博士，研究领域为表面强化机理与寿命预测方法。E-mail：maojx@buaa.edu.cn

中图分类号: V263.5
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出版历程
- 收稿日期: 2024-01-06
- 网络出版日期: 2024-08-30

Coupled laser-shot peening for fatigue strength enhancement method on GH2787 compressor blade

HU Dianyin^{1, 2
,},
WANG Tao³,
DU Junliang^{1, 4},
LU Weixin¹,
MAO Jianxing^{1, 2,*
, ,},
ZHANG Xiaojie^{2, 3},
XU Xingwei⁴,
WANG Rongqiao^{2, 3}

1.
Research Institute of Areo-Engine，Beihang University，Beijing 100191，China
2.
Beijing Key Laboratory of Aero-Engine Structure and Strength，Beihang University，Beijing 100191，China
3.
School of Energy and Power Engineering，Beihang University，Beijing 100191，China
4.
Chengdu Engine Company Limited，Aero Engine Corporation of China，Chengdu 610500，China

摘要

摘要:
以GH2787压气机叶片为研究对象，提出一种激光-喷丸复合强化工艺方案，兼顾了激光强化在残余应力层深度上的突出优势，以及喷丸强化表层残余应力水平高、可抑制表面缺陷敏感性的技术特点，从而实现叶片表面完整性的综合改善。对强化后叶片表面完整性及疲劳强度开展测试，结果表明：激光-喷丸复合强化对压气机叶片疲劳强度提升效果最为显著，相比于无强化叶片，疲劳强度提升20.6%；配合抛光处理后，疲劳强度增幅进一步提升至28.1%，显著高于单独采用喷丸强化的15.9%和单独采用激光强化的18.3%。研究工作为压气机叶片表面强化工艺实施及抗疲劳设计提供理论依据及数据支撑。
- 压气机叶片 /
- 疲劳强度 /
- 表面强化 /
- 残余应力 /
- 表面形貌
Abstract:
Taking a compressor blade made of GH2787 as the research object, an approach of coupling laser shock peening and shot peening was proposed for taking advantages of individual laser shock peening and shot peening. This led to a high level of residual stress and sensitivity inhibition of defects on component surface, so as to comprehensively improve the surface integrity of the blade. The surface integrity and fatigue strength of the strengthened blades were tested, and the coupled laser-shot peening exhibited the most significant effect on compressor blade fatigue strength improvement. The fatigue strength of the coupled laser-shot peened compressor blades was improved by 20.6%, which was further increased to 28.1% after following polishing treatment. The increase of fatigue strength was significantly higher than the individual laser shock peening and shot peening, i.e., 15.9% and 18.3%, respectively. This work provides theoretical basis and data support for the implementation of compressor blade surface strengthening technology and anti-fatigue design.
- compressor blade /
- fatigue strength /
- surface strengthening /
- residual stress /
- surface topography

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图 1 叶片结构

Figure 1. Structure size of blade

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图 2 残余应力测点示意图（单位：mm）

Figure 2. Schematic diagram of the residual stress measurement point （unit：mm）

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图 3 步进法示意图

Figure 3. Process of step-forward method

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图 4 振动应力测点示意图（单位：mm）

Figure 4. Schematic diagram of the dynamic stress measurement point （unit：mm）

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图 5 叶片振动夹具及叶片夹持方式

Figure 5. Blade vibration fixture and blade clamping method

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图 6 叶片表面机械加工缺陷

Figure 6. Machining defects on blade surface

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图 7 叶片起裂位置

Figure 7. Origin of blade cracking

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图 8 叶片疲劳破坏位置表面形貌

Figure 8. Surface morphology of blade fatigue damage position

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图 9 喷丸强化

Figure 9. Shot peening

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图 10 激光冲击强化

Figure 10. Laser shock peening

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图 11 不同强化方式叶片表面形貌对比

Figure 11. Comparison of blade morphology with different surface strengthening methods

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图 12 不同表面强化方式叶片表面粗糙度对比

Figure 12. Comparison of blade surface roughness with different surface strengthening methods

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图 13 不同表面强化方式叶片表面残余应力对比

Figure 13. Comparison of residual stress on blade surface with different surface strengthening methods

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图 14 不同强化方式叶片深度方向残余压应力

Figure 14. Residual compressive stress in depth direction of blade with different strengthening methods

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图 15 不同表面强化方式叶片表面硬度对比

Figure 15. Comparison of blade surface hardness with different surface strengthening methods

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图 16 不同表面强化方式叶片叶尖变形程度对比

Figure 16. Comparison of blade tip deformation degree with different surface strengthening methods

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图 17 叶片振动疲劳试验结果

Figure 17. Results of blade vibration fatigue test

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表 1 GH2787基础力学性能数据

Table 1. Basic mechanical property data of GH2787

参数	数值
密度/10³ （kg/m³）	8.04
弹性模量/GPa	214
泊松比	0.3
屈服强度/MPa	635
抗拉强度/MPa	980

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表 2 叶片最终表面铣削工艺参数

Table 2. Final surface milling process parameters of blade

参数	数值
铣削速度/（m/min）	100.5
铣削宽度/mm	0.33
刀具转速/（r/min）	2000
铣削深度/mm	0.1
每齿进给/mm	0.15

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表 3 叶片振动疲劳强度试验结果

Table 3. Vibration fatigue strength test results of blades

叶片编号	疲劳强度/MPa	疲劳强度均值/MPa
N-1	417.1	402.0
N-2	400.5
N-3	412.0
N-4	399.0
N-5	381.6

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表 4 试验矩阵

Table 4. Test matrix

叶片编号	强化方式	是否抛光	件数
N-1～N-5	无强化	是	5
S-1～S-2	喷丸	否	2
S-3～S-4	喷丸	是	2
L-1～L-2	激光	否	2
L-3～L-4	激光	是	2
LS-1～LS 2	复合	否	2
LS-3～LS 4	复合	是	2

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表 5 表面强化叶片振动疲劳试验结果

Table 5. Vibration fatigue test results of surface strengthened blades

强化方式	是否抛光	编号	疲劳强度/ MPa	疲劳强度均值/ MPa
喷丸	否	S-1	444.8	465.8
	否	S-2	486.8	465.8
	是	S-3	503.8	492.9
	是	S-4	482.0	492.9
激光	否	L-1	461.1	470.5
	否	L-2	479.9	470.5
	是	L-3	462.7	476.3
	是	L-4	490.0	476.3
复合	否	LS-1	466.7	485.0
	否	LS-2	503.3	485.0
	是	LS-3	513.7	514.9
	是	LS-4	516.1	514.9

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