航空发动机轮盘中心孔模拟试验件设计方法及试验验证

魏大盛; 冯俊淇; 马梦弟; 姚利信; 王延荣

doi:10.13224/j.cnki.jasp.20220205

航空发动机轮盘中心孔模拟试验件设计方法及试验验证

doi: 10.13224/j.cnki.jasp.20220205

1.
北京航空航天大学能源与动力工程学院，北京 100191
2.
北京航空航天大学江西研究院，南昌 330096

基金项目: 国家科技重大专项（J2019-Ⅳ-0012-0080）

详细信息

作者简介:
魏大盛（1978-），男，副教授、博士生导师，博士，主要从事航空发动机用材料及结构强度研究。E-mail：dasheng.w@163.com

中图分类号: V231.95
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出版历程
- 收稿日期: 2022-04-12
- 网络出版日期: 2022-09-12

Design method and test verification of simulated specimen of aeroengine disc center hole

1.
School of Energy and Power Engineering，Beihang University，Beijing 100191，China
2.
Jiangxi Research Institute，Beihang University，Nanchang 330096，China

摘要

摘要:
依据涡轮盘有限元计算结果，确定盘心考核位置处的应力状态，并将周向应力和轴向应力比值以及轮盘中心孔处周向应力沿径向的应力梯度作为设计指标，保证模拟件应力状态与实际轮盘一致。针对轮盘中心孔考核位置，本文共设计两类模拟件：一是反映双轴应力状态的多轴模拟件，二是反映应力梯度的平板缺口模拟件。分别采用两种试验件，结合轮盘实际载荷条件开展低循环疲劳试验，并对试验结果进行统计分析。进而，采用多轴疲劳寿命预测模型及考虑应力梯度影响的寿命预测模型对两种试验件的疲劳寿命进行评估，双轴模拟件的预测结果均在2倍分散带内，平板缺口模拟件的预测结果均在3倍分散带内，此寿命预测结果对实际轮盘设计具有参考价值。
- 涡轮盘 /
- 模拟试验件 /
- 结构强度 /
- 多轴疲劳 /
- 应力梯度
Abstract:
According to the finite element simulation results of the turbine disc, the stress state at the inspection position of the disk center was determined, and the ratio of the circumferential stress and axial stress and the radial stress gradient of the circumferential stress at the disc center hole were taken as the design indexes to ensure the consistency of stress state of the simulated specimen with the actual disc. Two kinds of simulators, namely, the multi axial simulators reflecting the biaxial stress state, and the plate notch simulators reflecting the stress gradient, were designed for the inspection position of the center hole of the wheel disc. Low cycle fatigue tests were carried out by using these two kinds of specimens under actual load conditions of the disc, and the test results were statistically analyzed. Furthermore, the multi-axial fatigue life prediction model and the life model considering the influence of stress gradient were used to evaluate the fatigue life of these two simulated specimens. The scatter bands of the prediction results of biaxial simulated specimen were within 2 and those of the flat notch simulated specimen were within 3. The results could provide engineering reference for the life evaluation of aeroengine structures.
- turbine disc /
- simulated specimen /
- structural strength /
- multi-axial fatigue /
- stress gradient

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图 1 有限元模型

Figure 1. Finite element model

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图 2 轮盘中心孔边应力分布

Figure 2. Stress distribution around the disc center hole

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图 3 轮盘中心孔处周向应力沿径向的应力梯度

Figure 3. Circumferential stress gradient along radial direction at the disc center hole

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图 4 轮盘中心孔多轴应力模拟件尺寸示意图

Figure 4. Dimension diagram of multiaxial stress simulator of the disc center hole

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图 5 轮盘中心孔多轴应力模拟件结构尺寸（单位：mm）

Figure 5. Structural dimensions of multiaxial stress simulator of the disc center hole （unit: mm）

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图 6 轮盘中心孔应力梯度模拟件尺寸示意图

Figure 6. Dimension diagram of stress gradient simulator of the disc center hole

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图 7 不同缺口半径对应力梯度的影响

Figure 7. Influence of different notch radius on stress gradient

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图 8 不同缺口净截面宽度对应力梯度的影响

Figure 8. Influence of different net section width of notch on stress gradient

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图 9 轮盘中心孔应力梯度模拟件结构尺寸（单位：mm）

Figure 9. Structural dimensions of stress gradient simulator of the disc center hole （unit: mm）

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图 10 盘心多轴应力模拟件试验结果

Figure 10. Test results of disk centered multiaxial stress simulator

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图 11 裂纹萌生位置断口分析

Figure 11. Fracture analysis of crack initiation position

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图 12 盘心应力梯度模拟件试验结果

Figure 12. Test results of disc center hole stress gradient simulator

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图 13 轮盘中心孔多轴应力模拟件寿命预测结果

Figure 13. Life prediction results of multiaxial stress simulators for the disc center hole

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图 14 轮盘中心孔应力梯度模拟件寿命预测结果

Figure 14. Life prediction results of stress gradient simulator for the disc center hole

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表 1 Udimet 720Li材料属性

Table 1. Material properties of Udimet 720Li

温度/℃	弹性模型/GPa	泊松比	线膨胀系数/10⁻⁵	热导率/（W/（m·℃））	比热容/(J/（kg·℃））	密度/（kg/m³）
500	197.6	0.347	1.38	17.7	510.6	8148

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表 2 不同直梁宽度对应力比值的影响

Table 2. Influence of different straight beam width on stress ratio

直梁宽度${H_3}$/mm	应力比值
2.9	−0.264
3.5	−0.304
3.2	−0.237
3.3	−0.227
3.4	−0.220

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表 3 不同异形孔圆角对应力比值的影响

Table 3. Influence of different special-shaped hole fillet on stress ratio

异形孔圆角${R_3}$/mm	应力比值
3.5	−0.218
4.0	−0.222
4.5	−0.220

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表 4 不同工作段宽度对应力比的影响

Table 4. Influence of different working section width on stress ratio

工作段宽度${B_1}$/mm	应力比值
2.0	−0.171
1.5	−0.087

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表 5 不同缺口半径

Table 5. Different notch radius

净截面宽度/mm	缺口半径/mm
8	0.1
8	0.3
8	0.5

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表 6 不同缺口净截面宽度

Table 6. Different net section width of notches

净截面宽度/mm	缺口半径/mm
8	0.1
16	0.1
22	0.1

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表 7 轮盘中心孔多轴应力模拟件试验数据

Table 7. Test data of multiaxial stress simulator of the disc center hole

试件编号	温度/ ℃	载荷比	最大载荷/ kN	寿命/ 10⁴次
S1	500	0.05	20.13	150.6
S2	500	0.05	20.13	154.5
S3	500	0.05	20.13	173.0
S4	500	0.05	20.13	210.6
S5	500	0.05	20.13	119.9
S6	500	0.05	20.13	119.8
S7	500	0.05	20.13	105.1
S8	500	0.05	20.13	91.2
S9	500	0.05	20.13	130.8

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表 8 轮盘中心孔应力梯度模拟件试验数据

Table 8. Test data of stress gradient simulator of the disc center hole

试件编号	温度/ ℃	载荷比	截面积/ mm²	最大载荷/ kN	寿命/ 10⁴次
P1	500	0.05	13.65	13.73	146.0
P2	500	0.05	14.34	14.42	75.0
P3	500	0.05	13.95	14.03	109.5
P4	500	0.05	14.34	14.43	292.4
P5	500	0.05	14.07	14.16	163.4
P6	500	0.05	14.39	14.48	227.6
P7	500	0.05	12.58	12.66	137.4
P8	500	0.05	12.39	12.47	101.0
P9	500	0.05	12.83	12.91	267.4

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表 9 轮盘中心孔多轴应力模拟件应力应变结果

Table 9. Stress and strain results of multiaxial stress simulator of the disc center hole

加载状态	应力/MPa	应变
最大	1073.1	0.0058308
最小	53.654	0.0002915

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表 10 轮盘中心孔应力梯度模拟件应力应变结果

Table 10. Stress and strain results of the simulator of the stress gradient in the disc center hole

加载状态	应力/MPa	应变
最大	1063.6	0.005375
最小	53.2	0.000269

下载: 导出CSV

参考文献(20)

[1]	孙国芹. 高温多轴疲劳行为及寿命预测研究[D]. 北京: 北京工业大学, 2009. SUN Guoqin. Research on multiaxial fatigue behavior and life prediction at high temperature[D]. Beijing: Beijing University of Technology, 2009. (in Chinese)
[2]	STAMOULIS K,GIANNAKOPOULOS A E. Size effects on strength, toughness and fatigue crack growth of gradient elastic solids[J]. International Journal of Solids & Structures,2008,45(18): 4921-4935.
[3]	FILIPPINI M. Stress gradient calculations at notches[J]. International Journal of Fatigue,2000,22(5): 397-409. doi: 10.1016/S0142-1123(00)00010-4
[4]	王延荣,李宏新,袁善虎,等. 考虑应力梯度的缺口疲劳寿命预测方法[J]. 航空动力学报,2013,28(6): 1208-1214. doi: 10.13224/j.cnki.jasp.2013.06.025 WANG Yanrong,LI Hongxin,YUAN Shanhu,et al. Method for notched fatigue life prediction with stress gradient[J]. Journal of Aerospace Power,2013,28(6): 1208-1214. (in Chinese) doi: 10.13224/j.cnki.jasp.2013.06.025
[5]	魏芷峰,王延荣,袁善虎,等. 涡轮盘低循环疲劳寿命预测方法与流程[J]. 燃气涡轮试验与研究,2014,27(5): 25-29,48. doi: 10.3969/j.issn.1672-2620.2014.05.005 WEI Zhifeng,WANG Yanrong,YUAN Shanhu,et al. Life prediction method and procedure for low-cycle fatigue of turbine disk[J]. Gas Turbine Experiment and Research,2014,27(5): 25-29,48. (in Chinese) doi: 10.3969/j.issn.1672-2620.2014.05.005
[6]	文保平,张镇生,闵行. 非均匀应力场对构件疲劳强度的影响——应力梯度效应[J]. 机械强度,1990,12(1): 13-18. doi: 10.3321/j.issn:1001-9669.1990.01.001 WEN Baoping,ZHANG Zhensheng,MIN Hang,et al. Influence of inhomogeneous stress field on the member fatigue strength—stress gradients effect[J]. Mechanical Strength,1990,12(1): 13-18. (in Chinese) doi: 10.3321/j.issn:1001-9669.1990.01.001
[7]	柳云瀚. 基于临界距离理论的涡轮盘高温低周疲劳寿命预测[D]. 成都: 电子科技大学, 2018. LIU Yunhan. High temperature low cycle fatigue life prediction of turbine disk using critical distance theory[D]. Chengdu: University of Electronic Science and Technology of China, 2018. (in Chinese)
[8]	ADMINISTRATION F A. Advisory circular 33.70-1, guidance material for aircraft engine life-limited parts requirements[J]. Washington DC: FAA, 2009.
[9]	European Aviation Safety Agency. CS-E (Amendment 3) certification specification for engines [M]. Koln, Germany: European Aviation Safety Agency, 2010.
[10]	CASTILLO E,CONEJO A J,MÍNGUEZ R,et al. An alternative approach for addressing the failure probability-safety factor method with sensitivity analysis[J]. Reliability Engineering & System Safety,2003,82(2): 207-216.
[11]	CASTILLO E,MÍNGUEZ R,TERÁN A R,et al. Design and sensitivity analysis using the probability-safety-factor method. An application to retaining walls[J]. Structural Safety,2004,26(2): 159-179. doi: 10.1016/S0167-4730(03)00039-0
[12]	国家标准化管理委员会. 金属材料轴向等幅低循环疲劳试验方法: GB/T 15248-2008[S]. 北京: 国家标准化管理委员会, 2008: 1-17.
[13]	国家标准化管理委员会. 金属材料疲劳试验轴向应变控制方法: GB/T 26077-2010[S]. 北京: 国家标准化管理委员会, 2011: 1-22 .
[14]	中国航空工业总公司. 金属材料轴向加载疲劳试验方法: HB 5287-1996[S]. 北京: 中国航空工业总公司, 1996: 1-22.
[15]	SMITH K N,WATSON P,TOPPER T H. A stress-strain function for the fatigue of metals[J]. Journal of Materials,1970,5(4): 767-778.
[16]	WALKER K. The effect of stress ratio during crack propagation and fatigue for 2024-T3 and 7075-T6 aluminum[J]. American Society for Testing and Materials,1970,462(1): 1-14.
[17]	DOWLING N E. Mean stress effects in stress-life and strain-life fatigue[J]. SAE Technical Paper,2004,32(12): 1004-1019.
[18]	DOWLING N E,CALHOUN C A,ARCARI A. Mean stress effects in stress-life fatigue and the Walker equation[J]. Fatigue & Fracture of Engineering Materials & Structures,2009,32(3): 163-179.
[19]	DOWLING N E. Mean stress effects in strain-life fatigue[J]. Fatigue & Fracture of Engineering Materials & Structures,2009,32(12): 1004-1019.
[20]	NEUBER H. Theory of notch stresses: principles for extract calculation of strength with reference to structural form and material[M]. 2nd ed. Berlin: Springer-Verlag, 1958.