目的 解决航空铝合金材料大气腐蚀失效问题。方法 提出了一种针对铝合金材料实验室加速腐蚀环境谱编制及其与实际大气间等效加速关系的“双桥连接式”快速确定方法。该方法以材料的腐蚀电量和腐蚀失重大小作为当量参数,实现了在没有外场长期暴晒试验件的情况下,通过大气环境监测数据、实验室腐蚀失重试验和短期大气暴露试验结果计算获得等效加速关系。结果 依据所提等效加速关系确定方法,首先搜集并处理了某热带海洋大气环境10 a的大气监测数据,编制了气候环境总谱和化学环境总谱,其次基于环境因素加权浓缩的方法编制了模拟某热带大气环境的实验室加速腐蚀环境谱。随后通过实地短期大气环境ACM监测以及实验室腐蚀失重试验等手段,计算并获得了ZL114A铝合金在所编制的加速环境谱作用下的等效加速关系为74 h/a。为了验证所提等效加速关系确定方法的可行性,本文采用SEM、CT扫描等手段分别测量大气暴露6个月、大气暴露1 a和实验室加速腐蚀环境谱作用72 h的ZL114A铝合金的表面损伤形貌、点蚀坑尺寸、疲劳寿命和断口形貌。结论 结果表明,大气暴晒试件和加速腐蚀试件的腐蚀损伤模式相同,损伤严重程度与所得等效加速关系相符。
Abstract
To deal with the atmospheric corrosion failure of aviation aluminum alloy materials, a "double bridge connection" method for rapid determination of aluminum alloy accelerated corrosion environmental spectrum and its equivalent acceleration relationship with the actual atmosphere was proposed. The method takes the corrosion electricity and corrosion weight loss of materials as equivalent parameters, and mainly includes three steps: preparing the laboratory accelerated environment spectrum based on the method of "weighted concentration of environmental factors", obtaining the long-term cumulative corrosion electricity in the actual atmospheric environment based on the "electricity (current) equivalent bridge", and determining the equivalent acceleration relationship based on the "weight loss equivalent bridge". The equivalent acceleration relationship is obtained through the calculation of atmospheric environment monitoring data, laboratory corrosion weight loss test and short-term atmospheric exposure test results without long-term exposure test pieces. Firstly, according to the proposed method for determining the equivalent acceleration relationship, the atmospheric environment monitoring data of a tropical area for 10 years are collected and sorted out, and the climatic environment spectrum and chemical environment spectrum of the atmospheric environment in this area are compiled. By analyzing the content and products of corrosive media in the atmosphere and the method of weighted concentration, and combined with the test method of periodic infiltration, a laboratory accelerated corrosion environment spectrum is compiled. Secondly, the atmospheric corrosion monitoring technology (ACM) and electrochemical workstation are used to measure and calculate the corrosion current and conversion coefficient of ZL114A aluminum alloy in different temperature and humidity atmospheric environments and different concentrations and types of acid solutions. Combined with the short-term (85 days) measurement results of environmental temperature and humidity, corrosion current and corrosion electricity, the cumulative corrosion electricity of ZL114A aluminum alloy exposed to the island atmosphere for 10 years is 3050339.15c according to the "electricity (current) equivalent bridge". Next, a laboratory corrosion weight loss test is carried out to obtain the average corrosion weight loss rate of ZL114A aluminum alloy per unit area under the action of accelerated corrosion environment spectrum in the laboratory. Then, according to the corrosion weight loss electricity conversion relationship of the aluminum alloy in the field environment, the corrosion weight loss of the aluminum alloy exposed in the field atmospheric environment for 10 years is calculated to be 57.96 g. Afterwards, according to the "weight loss equivalent bridge", the equivalent acceleration relationship between the three types of laboratory accelerated corrosion environment spectrum and the actual atmospheric environment is calculated to be 74 h/a. Finally, in order to verify the feasibility of the proposed method for determining the equivalent acceleration relationship, the surface damage morphology, pitting pit size, fatigue life and fracture morphology of ZL114A aluminum alloy are measured by SEM, CT scanning and other means after 6 months of atmospheric exposure, 1 year of atmospheric exposure and 72 hours of laboratory accelerated corrosion environment spectrum. The results show that the corrosion damage modes of atmospheric exposure specimens and accelerated corrosion specimens are the same, and the damage severity is consistent with the equivalent acceleration relationship.
关键词
ZL114A铝合金 /
加速腐蚀 /
腐蚀失重 /
等效加速关系 /
热带海洋大气环境 /
点蚀
Key words
ZL114A aluminum alloy /
accelerated corrosion /
corrosion weight loss /
equivalent acceleration relationship /
tropical marine atmospheric environment /
pitting corrosion
{{custom_sec.title}}
{{custom_sec.title}}
{{custom_sec.content}}
参考文献
[1] LIU Z, LI X, MU Z.Research on Fatigue Property of Aero Aluminum Alloy in Airport Environment Based on Corrosion Grade[J]. Journal of Mechanical Strength, 2014.
[2] PELTIER F, THIERRY D.Development of Reliable Accelerated Corrosion Tests for Aluminum Alloys Used in the Aerospace Industry[J]. Corrosion, 2023, 79(9): 1006-1016.
[3] LIAO M, RENAUD G, BELLINGER N C.Fatigue Modeling for Aircraft Structures Containing Natural Exfoliation Corrosion[J]. International Journal of Fatigue, 2007, 29(4): 677-686.
[4] XU Y, WANG X J, YAN Z T, et al.Corrosion Properties of Light-Weight and High-Strength 2195 Al-Li Alloy[J]. Chinese Journal of Aeronautics, 2011, 24(5): 681-686.
[5] ZHANG S, ZHANG T, HE Y T, et al.Long-Term Atmospheric Corrosion of Aluminum Alloy 2024-T4 in Coastal Environment: Surface and Sectional Corrosion Behavior[J]. Journal of Alloys and Compounds, 2019, 789: 460-471.
[6] ZHANG S, ZHANG T, HE Y T, et al.Long-Term Atmospheric Pre-Corrosion Fatigue Properties of Epoxy Primer-Coated 7075-T6 Aluminum Alloy Structures[J]. International Journal of Fatigue, 2019, 129: 105225.
[7] ZHANG T Y, ZHANG T, HE Y T, et al.Probabilistic Model of the Pre-Corrosion Fatigue Life of Epoxy-Coated Aluminum Alloys Based on the Single Point-Group Model of the Maximum Likelihood Method[J]. International Journal of Fatigue, 2023, 171: 107580.
[8] ZHANG T Y, ZHANG T, HE Y T, et al.Probabilistic Model of the Fatigue Life of Epoxy-Coated Aluminum Alloys Considering Atmospheric Exposure[J]. International Journal of Fatigue, 2022, 162: 106899.
[9] ZHANG T Y, ZHANG T, HE Y T, et al.Corrosion and Aging of Organic Aviation Coatings: A Review[J]. Chinese Journal of Aeronautics, 2023, 36(4): 1-35.
[10] ZHANG T Y, ZHANG T, HE Y T, et al.Aging and Corrosion Behavior of Epoxy Primer Coated Aluminum Alloys in UVA, UVA-Neutral and UVA-Acidic Alternating-Immersion Environments[J]. Engineering Failure Analysis, 2021, 130: 105759.
[11] LI X G, ZHANG D W, LIU Z Y, et al.Materials Science: Share Corrosion Data[J]. Nature, 2015, 527(7579): 441-442.
[12] WANG B B, WANG Z Y, HAN W, et al.Atmospheric Corrosion of Aluminium Alloy 2024-T3 Exposed to Salt Lake Environment in Western China[J]. Corrosion Science, 2012, 59: 63-70.
[13] SUN S Q, ZHENG Q F, LI D F, et al.Long-Term Atmospheric Corrosion Behaviour of Aluminium Alloys 2024 and 7075 in Urban, Coastal and Industrial Environments[J]. Corrosion Science, 2009, 51(4): 719-727.
[14] ZHANG R X, ZHAO W D, ZHANG H, et al.Fatigue Performance Rejuvenation of Corroded 7075-T651 Aluminum Alloy through Ultrasonic Nanocrystal Surface Modification[J]. International Journal of Fatigue, 2021, 153: 106463.
[15] SONG H P, LIU C C, ZHANG H, et al.Experimental Investigation on Damage Evolution in Pre-Corroded Aluminum Alloy 7075-T7651 under Fatigue Loading[J]. Materials Science and Engineering: A, 2021, 799: 140206.
[16] ZHANG C, CHEN Y H, YAO W X.The Use of Fractal Dimensions in the Prediction of Residual Fatigue Life of Pre-Corroded Aluminum Alloy Specimens[J]. International Journal of Fatigue, 2014, 59: 282-291.
[17] XU X C, LIU D X, AO N, et al.Effects of Pre-Corrosion on Mechanical Properties of 7B50-T7751 Aluminum Alloy in Sodium Chloride Solution[J]. Materials and Corrosion, 2018, 69(7): 870-880.
[18] CHEN X, YANG L, DAI H L, et al.Exploring Factors Controlling Pre-Corrosion Fatigue of 316L Austenitic Stainless Steel in Hydrofluoric Acid[J]. Engineering Failure Analysis, 2020, 113: 104556.
[19] MENAN F, HENAFF G.Influence of Frequency and Exposure to a Saline Solution on the Corrosion Fatigue Crack Growth Behavior of the Aluminum Alloy 2024[J]. International Journal of Fatigue, 2009, 31(11/12): 1684-1695.
[20] MENAN F, HÉNAFF G. Synergistic Action of Fatigue and Corrosion during Crack Growth in the 2024 Aluminium Alloy[J]. Procedia Engineering, 2010, 2(1): 1441-1450.
[21] ZHANG H W, HE Y T, LIU C, et al. Effect of Interactive Periods to Corrosion-Fatigue Life on LY12CZ Alloy[J]. Applied Mechanics and Materials, 2011, 66/67/68: 96-101.
[22] 陈跃良, 卞贵学, 张勇, 等. 飞机结构电偶腐蚀数值模拟[M]. 北京: 国防工业出版社, 2020.
CHEN Y L, BIAN G X, ZHANG Y.Numerical Simulation of Galvanic Corrosion in Aircraft Structures[M]. Beijing: National Defense Industry Press, 2020.
[23] 穆志韬, 柳文林, 于战樵. 飞机服役环境当量加速腐蚀折算方法研究[J]. 海军航空工程学院学报, 2007, 22(3): 301-304.
MU Z T, LIU W L, YU Z Q.Research on Accelerated Corrosion Equivalent Conversion Method of Aircraft Service Environment[J]. Journal of Naval Aeronautical Engineering Institute, 2007, 22(3): 301-304.
[24] 刘元海, 任三元. 典型海洋大气环境当量加速试验环境谱研究[J]. 装备环境工程, 2011, 8(1): 48-52.
LIU Y H, REN S Y.Study on Equivalent Accelerated Corrosion Test Environment Spectrum of Typical Marine Atmosphere[J]. Equipment Environmental Engineering, 2011, 8(1): 48-52.
[25] 陈跃良, 段成美, 金平, 等. 飞机结构局部环境加速腐蚀当量谱[J]. 南京航空航天大学学报, 1999, 31(3): 338-341.
CHEN Y L, DUAN C M, JIN P, et al.Local Environmental Equivalent Spectrum for Accelerated Corrosion of Aircraft Structure[J]. Journal of Nanjing University of Aeronautics & Astronautics, 1999, 31(3): 338-341.
[26] 刘文珽, 李玉海, 陈群志, 等. 飞机结构腐蚀部位涂层加速试验环境谱研究[J]. 北京航空航天大学学报, 2002, 28(1): 109-112.
LIU W T, LI Y H, CHEN Q Z, et al.Accelerated Corrosion Environmental Spectrums for Testing Surface Coatings of Critical Areas of Flight Aircraft Structures[J]. Journal of Beijing University of Aeronautics and Astronautics, 2002, 28(1): 109-112.
[27] 蒋冬滨. 飞机结构关键危险部位加速腐蚀试验环境谱研究[J]. 航空学报, 1998, 19(4): 434-438.
JIANG D B.Study on Accelerated Corrosion Test Environment Spectrum for Critical Area[J]. Acta Aeronautica et Astronautica Sinica, 1998, 19(4): 434-438.
[28] 孙祚东. 军用飞机典型铝合金结构腐蚀损伤规律及加速腐蚀试验方法研究[D]. 哈尔滨: 哈尔滨工程大学, 2005.
SUN Z D.Study on corrosion damage of the typical aluminum alloy of air force plane and the test of accelerated corrosion[D]. Harbin: Harbin Engineering University, 2005.
[29] 贺小帆, 刘文珽. 疲劳关键件加速腐蚀因子可靠性分析[J]. 航空学报, 2005, 26(3): 315-319.
HE X F, LIU W T.Reliability Analysis of Accelerated Corrosion Factor for Fatigue Critical Components[J]. Acta Aeronautica et Astronautica Sinica, 2005, 26(3): 315-319.
[30] CHAUSSUMIER M, MABRU C, SHAHZAD M, et al.A Predictive Fatigue Life Model for Anodized 7050 Aluminium Alloy[J]. International Journal of Fatigue, 2013, 48: 205-213.
基金
国家自然科学基金青年C类(52505164);国家自然科学基金面上项目(52575191);中国博士后面上基金(2024M764268)