US2003070734A1PendingUtilityA1

Damage tolerant aluminum alloy product and method of its manufacture

Priority: Dec 22, 1998Filed: Jul 16, 2002Published: Apr 17, 2003

Est. expiryDec 22, 2018(expired)· nominal 20-yr term from priority

Inventors:Alfred Ludwig Heinz Alfred Johann Peter Haszler

C22C 21/16B32B 15/016Y10T428/12764C22F 1/057

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References

Claims

Abstract

The invention relates to a product comprising an aluminum base alloy consisting of (in weight %): Cu 3.8-4.9, Mg 1.2-1.8, Mn 0.1-0.9, Fe max. 0.12, Si max. 0.10, Ti max. 0.15, Zn max. 0.20, Cr max. 0.10, impurities each max. 0.05, total max. 0.15, balance aluminum. The product having a minimum L-0.2% yield strength of 300 MPa or more, a minimum LT-0.2% yield strength of 270 MPa, a minimum T-L fracture toughness K C(ao) of 100 MPa. {square root}m or more for a 700 mm wide CCT-panel, and has in both L/ST- and LT/ST-sections an average grain size of at least 6 according to ASTM4 E-112. Further the invention relates to a method for the manufacturing of such a product.

Claims

exact text as granted — not AI-modified

1 . A damage tolerant alloy product comprising an aluminum base alloy consisting essentially of (in weight %):

Cu
3.8-4.9

Mg
1.2-1.8

Mn
0.1-0.9

Fe
max. 0.12

Si
max. 0.10

Ti
max. 0.15

Zn
max. 0.20

Cr
max. 0.10

impurities each max. 0.05

total max. 0.15

balance aluminum,

said product having a minimum L-0.2% yield strength of 300 MPa or more, a minimum LT-0.2% yield strength of 270 MPa, a minimum T-L fracture toughness K C(ao) of 100 MPa. {square root}m or more for a 700 mm wide CCT-panel, and having in both L/ST- and LT/ST-sections an average grain size of at least 6 according to ASTM E-112.

2 . The product in accordance with claim 1 , wherein the Cu content is in a range of 3.8 to 4.7%.

3 . The product in accordance with claim 1 , wherein the Cu content is in a range of 3.9 to 4.6%.

4 . The product in accordance with claim 1 , wherein the Mg content is in a range of 1.2 to 1.7%.

5 . The product in accordance with claim 1 , wherein the Mn content is in a range of 0.1 to 0.8%.

6 . The product in accordance with claim 1 , wherein the product has minimum longitudinal (L)-0.2% yield strength of 360 MPa or more, the minimum 0.2% yield strength in the TL-direction (transverse direction) is 300 MPa.

7 . The product in accordance with claim 1 , wherein the product has minimum transverse (TL)-tensile strength of 440 MPa or more and a minimum longitudinal (L)-tensile strength of 475 MPa or more.

8 . The product in accordance with claim 1 , wherein the product has minimum L-T fracture toughness K C(ao) of 105 MPa. {square root}m for 700 mm wide CCT-panels.

9 . The product in accordance with claim 1 , wherein the minimum T-L fracture toughness K C(ao) is 170 MPa. {square root}m or more for 2000 mm wide CCT-panels.

10 . The product in accordance with claim 1 , wherein the minimum T-L fracture toughness K C(ao) is 175 MPa. {square root}m or more for 2000 mm wide CCT-panels.

11 . The product in accordance with claim 1 , wherein the grain aspect ratio in both L/ST- and LT/ST-sections is 1:4 or less.

12 . The product in accordance with claim 1 , wherein the grain aspect ratio in both L/ST- and LT/ST-sections is 1:3 or less.

13 . The product in accordance with claim 1 , wherein the grain aspect ratio in both L/ST- and LT/ST-sections is 1:2 or less.

14 . The product in accordance with claim 1 , wherein the product is a sheet product.

15 . The product in accordance with any one of claim 1 , wherein the product is a plate product.

16 . A composite comprising the product in accordance with claim 1 , and a cladding on the product, the cladding comprising a higher purity aluminum alloy than said product.

17 . A composite comprising the product in accordance with claim 1 , and a cladding on the product, the cladding comprising a member of the group consisting of:
(i) an alloy of the Aluminum Association AA1000 series; (ii) an alloy of the Aluminum Association AA6000 series; and (iii) an alloy of the Aluminum Association AA7000 series.

18 . A method for manufacturing a damage tolerant alloy product, comprising the steps of:
(a) casting an ingot or a slab comprising an aluminum alloy consisting of (in wt. %): Cu 3.8-4.9 Mg 1.2-1.8 Mn 0.1-0.9 Fe max. 0.12 Si max. 0.10 Ti max. 0.15 Zn max. 0.20 Cr max. 0.10 impurities each max. 0.05 total max. 0.15 balance aluminum; (b) hot rolling the ingot to form an intermediate product; (c) cold rolling the intermediate product to form a rolled product in both the length and in the width direction with a total cold deformation of more than 60%; (d) solution heat treating the intermediate product after cold rolling in at least one direction; (e) cooling the solution heat treated intermediate product; and (f) ageing the cooled intermediate product;
said damage tolerant product having a minimum L-0.2% yield strength of 300 MPa or more, a minimum LT-0.2% yield strength of 270 MPa, a minimum T-L fracture toughness K C(ao) of 100 MPa. {square root}m or more for a 700 mm wide CCT-panel, and having in both L/ST- and LT/ST-sections an average grain size of at least 6 according to ASTM E-112.

19 . The method in accordance with claim 18 , wherein during step (b) the ingot is hot rolled in both the length and in the width direction.

20 . The method in accordance with claim 18 , wherein during step (c) the intermediate product is first cold rolled in the one direction with a total cold deformation in the range of 20 to 55% and then further cold rolled in the other direction to a rolled product with a total cold deformation of 60% or more.

21 . The method in accordance with claim 20 , wherein the process step (c) comprises the sequential steps of:
(c-i) first cold rolling the intermediate product in one direction with a total cold deformation in the range of 20 to 55%; (c-ii) solution heat treating the intermediate product after cold rolling; (c-iii) tempering the solution heat treated intermediate product to a T3 or a T351-temper; (c-iv) soft annealing the tempered intermediate product; and (c-v) cold rolling of the soft annealed intermediate product in at least another direction to a final gauge thickness with a total cold deformation of more than 60%.

22 . The method in accordance with claim 21 , wherein during process step (c-v) the soft annealed intermediate product is being cold rolled in both the length and in the width direction.

23 . The method in accordance with claim 21 , wherein the hot rolling of the ingot to the intermediate product occurs after homogenization at a temperature of 400 to 505° C.

24 . The method in accordance with claim 21 , wherein solution heat treating of the intermediate product after cold rolling in at least one direction occurs at a temperature of 460 to 505° C. for 5 to 120 minutes.

24 . The method in accordance with claim 21 , wherein the solution heat treated intermediate product is cooled to a temperature of 175° C. or lower.

25 . The method in accordance with claim 21 , wherein soft annealing of the cooled intermediate product occurs at a temperature of 300 to 430° C. for 0.5 to 12 hours.

26 . The method in accordance with claim 21 , wherein between cold rolling passes, the intermediate product is inter-annealed at a temperature of 300 to 430° C. for 0.5 to 12 hours.

27 . An aircraft skin comprising a sheet or plate of the damage tolerant alloy product of claim 1 .

28 . An aircraft skin comprising a sheet or plate of the damage tolerant alloy product made by the method of claim 18 .

29 . A damage tolerant alloy product comprising an aluminum base alloy consisting of (in weight %):