Corrosion of Aircraft Structures Made of Aluminum Alloys

Abolikhina, E. V.; Molyar, A. G.

doi:10.1023/b:masc.0000031656.94285.4c

Cited by 10 publications

(22 citation statements)

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“…На сучасному етапі розвитку дозвукової та надзвукової авіації алюмінієві сплави є головним конструкційним матеріалом в літакобудуванні. Зокрема, широко застосовуються алюмінієві сплави, що деформуються, систем: Al-Cu-Mg (серія 2ххх) та Al-Zn-Mg-Cu (серія 7ххх) [1][2][3][4]. Їх хімічний склад наведено в табл.…”

Section: різнеunclassified

“…із пресованих профілів Д16, Д16 ч , 1163 і В95, В95 пч , В95 оч , а штамповки лопатей повітряних гвинтів і різноманітні вузли кріплення -зі сплавів Д1 і Д1 ч . Для верхніх панелей, які під час польоту знаходяться в стиснутому стані, використовується високоміцний сплав В95Т1 системи легування Al-Zn-Mg-Cu, загартований і зістарений на максимальну міцність, а для нижніх панелей, що витримують у польоті розтягуючі навантаження -високоресурсний сплав Д16Т системи легування Al-Cu-Mg [4].…”

Section: таблицяunclassified

“…Мікроструктури сплавів Д16Т і В95Т1, з яких виробляють відповідно нижні та верхні панелі крил літака наведено рис. 1 [4].…”

Section: таблицяunclassified

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Structural aluminum alloys of the Al−Cu−Mg and Al−Zn−Mg−Сu systems in aircraft construction. Review

Prigunova¹,

Neduzhyi²

2022

Processy litʹâ

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A review of scientific and technical information on structural deformable aluminum alloys, Al-Cu-Mg (series 2xxx) and Al-Zn-Mg-Cu (series 7xxx) systems was conducted. Their chemical and phase composition, alloying methods, mechanical and operational properties, influence of technological factors were analyzed. Examples of the use of these alloys in aircraft construction are given. It is shown that among the alloys of the Al-Cu-Mg system (D1, B65, D16, D16ч, 1163, D19, etc.), the strongest is D16 and its improved modifications D16ч and 1163, the mechanical properties of which in the heat-hardened state are equal to low-carbon steels. Alloys D16, D16оч, 1163 have high strength characteristics at 20 0С and elevated temperatures, especially in the form of sheets and pressed parts. Therefore, it is a common material for the manufacture of aircraft skins in the engine area, which is subject to heating. However, an increase in strength leads to a decrease in plasticity. Alloys based on the Al-Zn-Cu-Mg system (В95, В95пч, В95оч, В96, В96Ц, В96Ц1, В96Ц3, В94, В93, В92, etc.) are the most high-strength among deformable aluminum alloys, so they are widely used in responsible power elements of aircraft and rocket engineering in the form of pressed and forged products. The strongest of them is B96Ц, especially its modification B96Ц1, in which, unlike the B95 alloy, manganese and chromium are partially or completely replaced by zirconium. The B95 alloy has high compressive strength and is used to cover the upper surface of aircraft wings, which is in a compressed state during flight. The inner surface of the wing is made of D16, D16ч, 1163 alloys that withstand tensile loads in flight. In terms of strength, the B95 alloy exceeds the similar characteristics of the D16 alloy by 20-25%, and in terms of yield strength by 40%. Replacing the D16 alloy with B95 makes it possible to reduce the weight of the aircraft to 5 tons. Almost all the large-sized stamped parts for the world’s largest turboprop An-22 “Antey” transport aircraft are made from the B93 forging alloy, which is alloyed with iron and heat-treated according to the T1 regime.The main disadvantage of high-strength alloys of the Al-Cu-Mg and Al-Zn-Mg-Cu systems is their tendency to degrade, which is caused by the action of various types of loads and corrosive environments during aircraft and flight basing and is accompanied by the development of fatigue or corrosion-fatigue cracks. Alternative points of view regarding the causes of these phenomena and ways of improving the properties of products made of these alloys by alloying, thermal and deformation treatments are considered. Keywords: deformable structural aluminum alloys; aircraft construction, chemical and phase composition, alloying, mechanical properties, corrosion resistance, heat treatment.

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Section: різнеunclassified

Section: таблицяunclassified

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Structural aluminum alloys of the Al−Cu−Mg and Al−Zn−Mg−Сu systems in aircraft construction. Review

Prigunova¹,

Neduzhyi²

2022

Processy litʹâ

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“…Steels combined with corrosion attack are commonly present in industrial applications: offshore petroleum platforms, combustion camera engines, oil and gas pipelines, bridges, marine and planes structures, vessels containing corrosion fluids or gas, etc. (Abolikhina and Molyar, 2003;Chandler, 1985;Galtier and Bertrand, 2002;Jacobson, 2005;MacClelland and Reifel, 1986;Song and Saraswathy, 2007). Very often in these applications, the mechanical elements are subjected to oscillating loads and environment leading to fatigue-corrosion conditions.…”

Section: Introductionmentioning

confidence: 99%

Ultrasonic fatigue testing on high strength steel: Effect of stress concentration factors associated with corrosion pitting holes

Almaraz

Mora

2012

International Journal of Damage Mechanics

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Ultrasonic fatigue tests at the frequency of 20 kHz were carried out on the hot rolled low alloy steel grade (known as R5), which according to the International Classification Society of offshore systems, it is a steel with the highest ultimate tensile strength to manufacture mooring chains and accessories intended to position mooring applications. Tests were carried out at constant load ratio R ¼ À1 on pre-corroded and no-corroded hourglass shape specimens; pre-corrosion was implemented according to ASTM standard G85. Stress concentration between two and three close hemispherical pitting holes on hourglass shape specimen undergoing uniaxial loading were obtained by finite element method. Experimental results show that fatigue life decreases with the proximity of two close pitting holes on the fracture surface. An exponential law is proposed for the stress concentration factor evolution with the proximity of two close pitting holes of identical radius; the trend of this law is confirmed by experimental results. Finally, fracture surfaces were analyzed and conclusions were listed concerning fatigue life, proximity of pitting holes on fracture surface, and the associated stress concentration factors.

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“…In particular, stress corrosion cracking, corrosion pitting and exfoliation corrosion are commonly found in aircraft structures [12,13]. There is a critical need to perform in-situ quantitative thickness measurements to determine the degree of corrosion and provide correlation to component's residual fatigue life.…”

Section: Introductionmentioning

confidence: 99%

High-temperature integrated and flexible ultrasonic transducers for nondestructive testing

Kobayashi

Jen

Bussière

et al. 2009

NDT & E International

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Corrosion of Aircraft Structures Made of Aluminum Alloys

Cited by 10 publications

References 0 publications

Structural aluminum alloys of the Al−Cu−Mg and Al−Zn−Mg−Сu systems in aircraft construction. Review

Structural aluminum alloys of the Al−Cu−Mg and Al−Zn−Mg−Сu systems in aircraft construction. Review

Ultrasonic fatigue testing on high strength steel: Effect of stress concentration factors associated with corrosion pitting holes

High-temperature integrated and flexible ultrasonic transducers for nondestructive testing

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