EP0848073B1

EP0848073B1 - Stress relieving of an age hardenable aluminium alloy product

Info

Publication number: EP0848073B1
Application number: EP19970203934
Authority: EP
Inventors: Alfred Johann Peter Haszler; Alfred Ludwig Heinz; Otmar Martin Müller
Original assignee: Corus Aluminium Walzprodukte GmbH
Current assignee: Novelis Koblenz GmbH
Priority date: 1996-12-16
Filing date: 1997-12-15
Publication date: 2002-05-08
Anticipated expiration: 2017-12-15
Also published as: EP0848073A1

Description

BACKGROUND OF THE INVENTION

1. FIELD OF THE INVENTION

The invention relates to a method of stress relieving an age hardenable aluminium alloy product by a permanent cold plastic deformation operation after solution heat treatment and quenching.

2. DESCRIPTION OF THE PRIOR ART

Manufacture of age hardenable aluminium alloy products requires solution heat treatment and quenching of the product. Since residual stresses due to the quenching operation do not allow for machining operations without simultaneous distortion of the machined parts, the products are stress relieved. In case of flat products (e.g. rolled plate) this has been accomplished by a stretching operation using a permanent plastic deformation of a few percent of the original dimension. Usually this stretching is done in the length direction which is normally also the rolling direction.
US-A-4294625 for example describes a process in which aluminium alloy is cast, hot worked into plate, solution treated, quenched, pre-aged, cold rolled to reduce thickness by 11 ± 2% and then stretched for stress relieving prior to ageing. The product is for use in aircraft. WO 95/24514 similarly briefly mentions stretching a quenched thick aluminium alloy product to improve flatness and reduce residual stress. JP-A-54-102214 describes manufacture of aluminium alloy pipe or rod with low residual stress, by hardening followed by stretch levelling by 0.5 - 1.0%, then roll levelling and further stretch levelling by 0.5 - 1.0%, followed by tempering at 210 - 250°C for 1 - 2 hours to relieve stress further.
It has also been proposed to employ cold compression as a stress-relieving step. GB-A-2025818 discusses manufacture of aluminium alloy rings by hot ring rolling, solution heat treatment, quenching, cold rolling for stress relieving and ageing. The diameter expansion in the cold rolling is 1 to 3%. Similarly JP-A-3-2359 describes cold compression of a complex shaped hollow conical billet of aluminium alloy, after solution heat treatment and prior to ageing. JP-A-4-187747 describes two-axis cold compression carried out on an aluminium alloy block of complex shape having insert parts located in apertures.
In conventional cold stretching, if the cross-section of the product (plate) is large (e.g. very thick or very wide plate) the strength of the stretcher machine may be insufficient to achieve the desired stretching degree. This of course depends not only on the dimensions of the plate but also on the plate alloy or - more precisely - on the flow stress of the plate material in the solutionized and quenched condition.

SUMMARY OF THE INVENTION

The object of the invention is therefore to provide a method of stress relieving of an age hardenable aluminium alloy product which is especially applicable to alloy product of large cross-section.
According to the invention there is provided a method of manufacture of a product of an age hardenable aluminium alloy, said product is a plate product, having a length-, a width- and a thickness-direction, comprising the steps of :-
(i) casting said age hardenable alloy;
(ii) shaping said cast alloy to form a shaped product;
(iii) solution heat treating said shaped product;
(iv) quenching the solution heat treated product;
(v) performing stress relieving of said quenched product by applying a permanent cold plastic deformation by applying a stress-relieving cold mechanical stretch to said product in said length direction, and wherein the step (a) of applying a stress-relieving cold mechanical stretch to said product in said length direction, is followed by the step (b) of applying a stress-relieving cold compression to said product being applied in said thickness direction.
In this method, the age hardening may be natural ageing or artificial ageing.
It has been found, as will be shown below, that replacement of the conventional mechanical stretching as a stress relieving method by cold compression alone results in loss of strength and toughness properties of the final product, although distortion after machining is improved. By applying combined stretching and compression the loss of properties is recovered while at the same time the improved distortion is retained.
To obtain full advantage of the invention the stress relieving permanent deformation by stretching, defined as the permanent elongation in the direction of stretching should be not more than 15 %, should more preferably be in the range of 0.3 - 5 %, and most preferably be in the range of 0.5 - 3 %.
Similarly preferably the stress relieving permanent deformation by compression, defined as the permanent reduction in the direction of compression should be in the range of 0.2 - 5 %, and should more preferably be in the range of 0.5 - 3 %.
In practice the cold compression may be given by forging, e.g. by a forging tool in overlapping steps. The stress relieving stretching of the product preferably takes place before the compression. The deformation is preferably given before substantially any age hardening after quenching.
Full advantage of the invention is obtained when the product is a thick plate having a final thickness of 2 inches(5cm) or more, preferably 4 inches (10cm) or more and most preferably 6 inches (15cm) or more.
The invention is particularly effective in meeting requirements of strength and toughness properties and distortion when the aluminium alloy belongs to the Aluminium Association AA 2XXX, the AA 6XXX or the AA 7XXX series.
Preferably the distortion after machining is less than 50µm.

DESCRIPTION OF PREFERRED EMBODIMENTS

An example of the invention and comparative examples will now be described, but the invention is not limited to the particular example given.

Experiment 1 (Comparative)

There were manufactured two 6 inch (15cm) plates of the aluminium alloy AA 7050 T 745X by casting, homogenizing, hot rolling, solution heat treating and quenching, stress relieving (immediately after quenching) and age hardening. The manufacturing procedure for both plates was the same except for the stress relieving which for one plate was executed by a conventional mechanical stretching in the length direction of the plate and for the other plate by cold compression. The cold compression was performed in the through thickness direction in order to achieve a stress relieved or stress reduced material. The compression was performed using a forging press. Because the product (plate) was much longer than the forging tool the cold compression operation was performed in a number of steps with an overlapping zone in each step in order to guarantee that the entire volume of the product was compressed and therefore stress relieved or stress reduced.

The two plates were tested. The amount of cold deformation and the test results are shown in Table 1.

Property	Cold deformation
	Stretching 1.9 - 2.0%	Compression 2.2 - 2.4%
Tensile L, s/4	TYS [MPa]	460	445
	UTS [MPa]	513	510
	A_4d [%]	10.7	10.3
Tensile LT, s/4	TYS [MPa]	456	451
	UTS [MPa]	521	516
	A_4d [%]	7.7	8.1
Tensile ST, s/2	TYS [MPa]	424	401
	UTS [MPa]	490	487
	A_4d [%]	4.0	4.1
K_Ic L-T, s/4	[MPa m^0.5]	28.33	28.34
K_Ic T-L, s/4	[MPa m^0.5]	24.41	23.67
K_Ic S-L, s/2	[MPa m^0.5]	24.22	24.0
Machining distortion	[10^-6m]	70 - 100	40 - 50

L, S, T, LT, L-T, etc. denote the testing directions in accordance with ASTM E399. ;Tensile testing was performed in accordance with ASTM E8 and ASTM B557. TYS is tensile yield strength. UTS is ultimate tensile strength. A_4d is elongation at fracture for a round tensile specimen with a gauge length of four times diameter. Fracture toughness testing for K_Ic values was performed according to ASTM B645 and ASTM E399. Machining distortion testing was carried out in accordance with Boeing Materials Specification BMS 7-323B, para. 8.6 and Figs. 4 and 5.
This experiment shows that the cold compression results in lower distortion after machining when compared to stretched material of same history and similar level of cold deformation. At the same time it was found that the cold compressed material has a lower tensile strength both in the direction of cold compression (the thickness direction) and in the length direction. This at best results in a narrow manufacturing window to obtain the required properties.

Experiment 2

This includes another comparative example and an example of the invention.
Two identical plates similar to those used in Experiment 1 (same alloy) were made by the same procedure as in Experiment 1 except that their thickness was 8.6 inches (21.8cm) and that the stress relieving for one plate was a cold compression in the thickness direction only and for the other plate a combination of mechanical stretching in the length direction and cold forging in the thickness direction.

Table 2 gives the deformation degrees and the results of tests on the products.

Property	Cold deformation
	cold compressed 1.6 - 1.9 %	stretched 0.6 - 0.7 % and cold compressed 0.9 - 1.1 %
tension L, T/4	TYS [MPa]	421	431
	UTS [MPa]	498	505
	A_4d [%]	11.0	9.5
tension LT, T/4	TYS [MPa]	420	421
	UTS [MPa]	491	493
	A_4d [%]	10.0	10.9
tension ST, T/2	TYS [MPa]	375	382
	UTS [MPa]	480	485
	A_4d [%]	7.0	5.7
K_Ic L-T, T/4	[MPa m^0.5]	26.2	27.7
K_Ic T-L, T/4	[MPa m^0.5]	26.1	27.2
K_Ic S-L, T/2	[MPa m^0.5]	21.6	24.2
Machining distortion	[10^-6m]	50	50

The loss in strength experienced with a cold compression alone was avoided by the combined process both for the L and the ST testing direction. Surprisingly it was found also that the toughness level of the combined stretched/cold compressed material was much better as compared to the product cold compressed only. This effect is more pronounced for the S-L than for the T-L and the L-T testing direction. The degree of distortion after machining is virtually the same for the two different processes. Therefore the process of invention permits manufacture of large cross-sections (wide and thick) of high strength age hardenable alloys with an improved property combination with respect to strength and toughness and simultaneously a similar level of distortion after machining when compared to the material which is cold compressed only, but otherwise has the same manufacturing history.

Claims

Method of manufacture of a product of an age hardenable aluminium alloy, said product is a plate product, having a length-, a width- and a thickness-direction, comprising the steps of :-

(i) casting said age hardenable alloy;

(ii) shaping said cast alloy to form a shaped product;

(iii) solution heat treating said shaped product;

(iv) quenching the solution heat treated product;

(v) performing stress relieving of said quenched product by applying a permanent cold plastic deformation by applying a stress-relieving cold mechanical stretch to said product in said length direction,

characterised in that the step (a) of applying a stress-relieving cold mechanical stretch to said product in said length direction, is followed by the step (b) of applying a stress-relieving cold compression to said product being applied in said thickness direction.
Method according to claim 1, wherein said steps (a) and (b) are performed substantially before age hardening has taken place following the quenching.
Method according to any one of claims 1 to 2, wherein permanent deformation in said step (a), defined as the permanent elongation in the direction of stretching, is not more than 15 %.
Method according to claim 3, wherein said permanent deformation in step (a) is in the range 0.3 - 5 %.
Method according to claim 4, wherein said permanent deformation in step (a) is in the range 0.5 - 3 %.
Method according to any one of claims 1 to 5, wherein permanent deformation in said step (b), defined as the permanent reduction in the direction of compression, is in the range 0.2 - 5 %.
Method according to claim 6, wherein said permanent deformation in step (b) is in the range 0.5 - 3 %.
Method according to any one of claims 1 to 7, wherein the step (b) said cold compression is applied by a forging tool in overlapping steps.
Method according to any one of claims 1 to 8, in which the product is a thick plate having a final thickness of at least 2 inches (5 cm).
Method according to claim 9, wherein said final thickness is at least 4 inches (10 cm).
Method according to claim 10, wherein said final thickness is at least 6 inches (15 cm).
Method according to any one of claims 1 to 11, wherein the aluminium alloy of said product belongs to one of the AA 2XXX, AA 6XXX and AA 7XXX series.