外物损伤对叶片振动疲劳裂纹扩展性能的影响

doi:10.12382/bgxb.2022.0109

摘要/Abstract

摘要：

为研究外物损伤(FOD)对航空发动机叶片的疲劳裂纹扩展影响,基于落锤冲击试验系统,在不同冲击能量下进行TC4钛合金试件的FOD模拟试验及振动疲劳试验,获得损伤试件的裂纹长度与疲劳寿命的关系,并拟合疲劳断口裂纹形貌参数,建立疲劳裂纹扩展寿命预测计算模型。研究结果表明:损伤缺口的深度和宽度随冲击能量的减小而非线性的减小。当冲击能量较大时,试件的疲劳裂纹先沿弯曲微裂纹扩展,后沿直线扩展;当冲击能量较小时,试件疲劳裂纹保持直线扩展。裂纹的萌生寿命与冲击能量、应力水平二者相关。

关键词: 外物损伤, 叶片, 落锤冲击, TC4钛合金, 振动疲劳, 裂纹扩展

Abstract:

In order to study the effect of foreign object damage (FOD) on the fatigue crack propagation of aero-engine blades, using the drop weight impact testing equipment, the FOD simulation test and vibration fatigue test of TC4 titanium alloy specimens were carried out under different impact energies. The relationship between the crack length and fatigue life of the damaged specimens was obtained, and the parameters of fatigue fracture crack morphology were fitted to establish a fatigue crack growth prediction and calculation model. The results showed that: The depth and width of the notch decreased nonlinearly with the decrease of impact energy; when the impact energy is large, the fatigue crack propagates first along the bending microcrack and then along the straight line; when the impact energy is small, the fatigue crack of the specimen keeps linear propagation; the crack initiation life is related to both impact energy and stress level.

Key words: foreign object damage, blade, drop impact, TC4 titanium alloy, vibration fatigue, crack propagation

杨硕, 杜天玮, 张晓鹏, 马梁, 张桂昌. 外物损伤对叶片振动疲劳裂纹扩展性能的影响[J]. 兵工学报, 2023, 44(6): 1713-1721.

YANG Shuo, DU Tianwei, ZHANG Xiaopeng, MA Liang, ZHANG Guichang. Effect of Foreign Object Damage on Vibration Fatigue Crack Propagation of Blades[J]. Acta Armamentarii, 2023, 44(6): 1713-1721.

图/表 17

表1 TC4钛合金化学成分

Table 1 Chemical composition of TC4 titanium alloy

表2 TC4钛合金力学参数

Table 2 Mechanical properties of TC4 titanium alloy

屈服应力/ MPa	极限应力/ MPa	弹性模量/ GPa	密度/ (kg·m^-3)	泊松比
881	1025	112	4420	0.34

图1 试件几何尺寸(单位:mm)

Fig.1 Geometry and dimensions of specimen (unit: mm)

图2 落锤几何尺寸

Fig.2 Geometry and dimensions of drop hammer

图3 冲击试验系统

Fig.3 Impact testing equipment

表3 冲击试验方案

Table 3 Impact test scheme

试件编号	E/J	h/m
H45-1	4.52	0.45
H45-2
H35-3	3.52	0.35
H35-4
H25-5	2.51	0.25
H25-6

表4 不同冲击能量条件下缺口型损伤形貌图

Table 4 Morphologies of notch-type damage under different impact energies

表5 不同冲击能量下的缺口尺寸

Table 5 Notch depths x and widths y for different energies

试件编号	h/m	E/J	x/mm	y/mm
H45-1	0.45	4.52	1.56	0.77
H45-2	0.45	4.52	1.58	0.74
H35-3	0.35	3.52	1.44	0.63
H35-4	0.35	3.52	1.39	0.62
H25-5	0.25	2.51	1.08	0.31
H25-6	0.25	2.51	1.15	0.35

图4 振动设备与试件

Fig.4 Equipment andspecimen

图5 应力与振幅的关系曲线

Fig.5 Amplitude vs stress curves

图6 试件裂纹扩展路径

Fig.6 Crack propagation of notched specimen

表6 裂纹扩展寿命试验结果

Table 6 Test results of crack growth life

试件编号	2A/mm	表面应力/MPa	f_i/Hz	f_f/Hz	N_i/次	N_f/次	N_p/次	c_i/mm	c_f/mm
H45-1	12	208	92.1	87.4	42057	124057	82000	0.4	8.1
H45-2	11	191	98.9	90.9	54054	144063	90009	0.4	5.9
H35-3	11	191	92.9	86.6	145047	236047	91000	0.5	8.0
H35-4	12	208	97.8	91.4	170045	226059	56014	0.4	7.6
H25-5	18	309	96.7	92.7	20066	48053	27987	1.0	7.5
H25-6	15	258	95.8	91.8	25488	70066	44578	1.0	7.3

图7 裂纹长度与循环周期曲线

Fig.7 Crack length vs cycles curves

图8 试件断口裂纹形状

Fig.8 Crack shape of specimen at fracture surface

图9 断口形状与表面裂纹长度拟合曲线

Fig.9 Fitted curves of fracture shape and surface crack length

图10 裂纹扩展速率结果

Fig.10 Results of crack growth rate

图11 裂纹扩展试验结果与预测结果对比

Fig.11 Comparison of test results and prediction results of crack growth life

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