Method of manufacturing heat treated sheet and plate with reduced levels of residual stress and improved flatness
This invention describes a method of producing a flat aluminum sheet product by providing an aluminum alloy stock, hot working the aluminum alloy stock through preheating and hot rolling, side sawing the aluminum alloy stock, subjecting the aluminum alloy stock to solution heat treatment, cold rolling the aluminum alloy stock to reduce its thickness by about 0.25% to about 5%, and finally stretching the aluminum alloy stock.
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The present invention relates generally to methods for making aluminum alloy sheet. Specifically, the present invention relates to a method of making an aluminum alloy sheet for use in aerospace applications wherein the sheet exhibits lower compressive and tensile stresses and improved flatness.
BACKGROUND OF THE INVENTIONAircraft wings have traditionally been machined either mechanically or chemically from an aluminum sheet selected from the Aluminum Association's designated 2XXX, 6XXX, or 7XXX series of aluminum alloys. The aluminum alloy sheets used in aerospace applications have to exhibit high fracture toughness, fatigue crack growth resistance, high cycle fatigue resistance, and corrosion resistance. In order to meet these needs, conventional manufacturing techniques have typically required that the aluminum sheet be subjected to solution heat treatment followed by quench in order to enhance the mechanical properties of the sheet. However, a side effect of this process is that distortion of the aluminum sheet can occur during machining to its final product form due to the interaction of inherent residual stresses, such as compressive and tensile stresses, and the severe thermal action of the solution heat treatment and quench. The distortion, which manifests itself as product warping, is considerable when the final product is as large as an aircraft wing.
To minimize these distortions and to improve product flatness, traditional manufacturing techniques have often used shot peening, mechanical bump forming, or stretching after solution heat treatment. Of these techniques, stretching after solution heat treatment has the added advantage of enhancing the mechanical properties of some aluminum alloys. However, products that are formed using conventional processes that utilize solution heat treating and quenching followed by stretching still exhibit compressive stresses near the surface and tensile stresses near the mid-plane. These residual stresses ultimately leads to product warping during the machining of the aluminum sheet into an aircraft wing.
Therefore, there exists a need for producing a large flat aluminum sheet product that is suitable for aerospace applications that does not distort during machining and that exhibits mechanical and physical properties that are equivalent if not improved over aluminum sheet products currently produced through conventional methods of manufacturing.
The present invention is a response to this need for producing a large flat aluminum sheet that would be suitable for aerospace applications by providing a method that reduces compressive and tensile stresses through the aluminum sheet's thickness while improving the mechanical properties of the sheet as compared to aluminum sheets produced through conventional methods of manufacture.
SUMMARY OF THE INVENTIONThis invention describes a method of producing a flat aluminum sheet product by providing an aluminum alloy stock, hot working the aluminum alloy stock through preheating and hot rolling, side sawing the aluminum alloy stock, subjecting the aluminum alloy stock to solution heat treatment, cold rolling the aluminum alloy stock to reduce its thickness by about 0.25% to about 5%, including all fractional values and points within this range, and finally stretching the aluminum alloy stock.
The preheating operation can have a temperature range from about 870 degrees Fahrenheit to about 1050 degrees Fahrenheit, including all fractional values and points within this range. It is noted that one skilled in the art would know which temperature to select for a given aluminum alloy and the amount of time the given aluminum alloy should be preheated.
The solution heat treatment operation can have a temperature range from about 870 degrees Fahrenheit to about 1050 degrees Fahrenheit, including all fractional values and points within this range. For the Aluminum Association's designated 7XXX series alloys, the preferred temperature range is from about 880 degrees Fahrenheit to about 900 degrees Fahrenheit, including all fractional values and points within this range. For the Aluminum Association's designated 2XXX series alloys, the preferred temperature range is from about 900 degrees Fahrenheit to about 930 degrees Fahrenheit, including all fractional values and points within this range. For the Aluminum Association's designated 6XXX series alloys, the preferred temperature range is from about 950 degrees Fahrenheit to about 1050 degrees Fahrenheit, including all fractional values and points within this range. Alternatively, the solution heat treatment could conform with the AMS 2772 standard.
After the solution heat treatment operation, the aluminum alloy stock is cold rolled to reduce the thickness of the stock by about 0.25% to about 5%. One or more cold rolling passes may be used to reduce the thickness of the stock to the desired thickness.
After the cold rolling process, the aluminum alloy stock is stretched or elongated by about 0.5% to about 4%, including all fractional values and points within this range. Preferably, the aluminum alloy stock is stretched by about 1% to about 3%.
The total amount of cold working (cold rolling+stretching) is about 2% to about 6%, including all fractional values and points within this range. Preferably, the total amount of cold working is about 3% to about 5%.
The aluminum alloys that may be used in this invention would include several of the Aluminum Association's designated 2XXX, 6XXX, and 7XXX series of aluminum alloys. For example, some aluminum alloys that may be used in connection with this invention would include, but shall not be limited to, aluminum alloy 2024 and its variants, 6061, 6013, 7075, and 7085.
An aspect of this invention is to provide an aluminum sheet product that does not exhibit or has minimal through-thickness stress gradients such as compressive and tensile stresses.
Another aspect of this invention is to provide an aluminum sheet product that does not distort during machining to its final product form.
Another aspect of this invention is provide an aluminum sheet product that has similar if not greater mechanical properties than aluminum products utilizing conventional methods of making aluminum sheet.
Another aspect of this invention is to provide an aluminum sheet that would be suitable for aerospace applications.
Another aspect of this invention is to provide an aluminum sheet that would be suitable for machining into an aircraft wing or stabilizer.
BRIEF DESCRIPTION OF THE DRAWINGS
The accompanying figures and the description that follows set forth this invention in its preferred embodiment. However, it is contemplated that persons generally familiar with the manufacture of aluminum alloy sheet or plate will be able to apply the novel characteristics of the structures and methods illustrated and described herein in other contexts by modification of certain details. Accordingly, the figures and description are not to be taken as restrictive on the scope of this invention, but are to be understood as broad and general teachings. It is noted that any ranges disclosed in the figures and description shall include all fractional values and points within those ranges.
The method disclosed includes providing an aluminum alloy stock selected from the 2XXX, 6XXX, or 7XXX series of aluminum alloys, hot working the aluminum alloy stock through preheating and hot rolling, side sawing the aluminum alloy stock to remove side cracks that would cause the aluminum sheet or plate to break during the stretching process, subjecting the aluminum alloy stock to solution heat treatment, cold rolling the aluminum alloy stock to reduce its thickness by about 0.25% to about 5%, and finally stretching the aluminum alloy stock by about 0.5% to about 4%, preferably stretching the aluminum alloy stock by about 1% to about 3%. The total amount of cold working (cold rolling+stretching) is about 2% to about 6%. Preferably, the total amount of cold work done on the aluminum sheet is about 3% to about 5%.
In
Plates #1 and #2 were stretched by 2.75% but the plates were not cold rolled. Plate #1 exhibited a dished condition at the first and second ends (0 and 200 on the x-axis) having approximate values of −7.62 mm (−0.3 inches) and −4.57 mm (−0.18 inches), respectively, while the middle section of the plate, having a range between −1.52 mm (−0.06 inches) to −2.54 mm (−0.10 inches), had a flatter orientation when compared to the two ends. In contrast, plate #2 was dished and crowned. As can be seen in
In contrast to plates #1 and #2, plates #3-6 were subjected to a combination of cold rolling and stretching. Plate #3 was cold rolled 3.3% and stretched by 1%. The total amount of cold work done on Plate #3 was 4.3%. As can be seen in
Plate #4 was cold rolled 2.8% and stretched by 1%. The total amount of cold work done to plate #4 was 3.8%. Again, as seen in
Plate #5 was cold rolled 1.7% and stretched by 2%. The total amount of cold work done to plate #5 was 3.7%. As seen in
Plate #6 was cold rolled 1.2% and stretched by 2.5%. The total amount of cold work done to plate #6 was 3.7%. Again, as seen in
E is the elastic modulus, v is Poisson's ratio, b is the sheet or plate thickness and σL and σLT are the longitudinal and long-transverse residual stresses measured as a function of depth through the thickness of the sheet or plate using any of several methods common to the industry.
As can be seen in
As stated above, plates #1, 2, and 7 were not cold rolled prior to being stretched by 2.75%. As can be seen in
Table 1 depicts the mechanical property summaries of aluminum plates that were cold rolled prior to stretch (column 3) and aluminum plates that were not cold rolled prior to stretch (column 2). Additionally, an approximation of a commercially acceptable standard is also listed in Table 1. “LT” stands for long transverse direction or across the width of the aluminum plate. “L” stands for longitudinal direction or down the length of the plate. “Ult” represents ultimate tensile strength, “Yield” represents tensile yield strength, and “Elg” represents percent elongation. “T-L Klc” refers to the fracture toughness of the aluminum plate when the plate is pulled in the transverse direction and the crack propagates in the longitudinal direction. “L-T Klc” refers to the fracture toughness of the plate when the plate is pulled in the longitudinal direction and the crack propagates in the transverse direction. “L Comp Yield” represents longitudinal compressive yield strength, which represents the yield strength of the plate when it is subjected to compressive forces. All of the plates in Table 1 were made from Aluminum Association designated 7055 aluminum alloy and were subjected to AMS 2772 solution heat treatment.
As can be seen in Table 1, column 2, the mechanical properties of the aluminum plates were higher than the approximated commercial standard when the plates were stretched. In the long-transverse direction, the stretched aluminum plates exhibited a 2% to 7% increase in ultimate tensile strength (LT Ult), a 3% to 8% increase in yield strength (LT Yield), and a 4% to 36% increase in elongation (LT Elg) over the approximated commercial standard found in column 1. In the longitudinal direction, the stretched aluminum plates exhibited a 3% to 8% increase in ultimate yield strength (LT Ult), a 2% to 6% increase in yield strength (LT Yield), and an 8% to 39% increase in elongation (L Elg) over the approximated commercial standard. Additionally, the stretched plates in column 2 exhibited a 4% to 8% increase in longitudinal compressive yield strength (L Comp Yield) over the approximated commercial standard. As can be seen in Table 1, the stretched plates in column 2 exhibited a 6% to 21% increase in fracture toughness over the approximated commercial standard in the “T-L” direction and a 17% to 30% increase in fracture toughness in the “L-T” direction.
When the aluminum plates were subjected to a cold rolling operation prior to stretching, the mechanical properties of the plates were further enhanced. As can be seen in Table 1, in the long-transverse direction the cold rolled and stretched plates in column 3 exhibited a 5% to 9% increase in ultimate tensile strength (LT Ult), a 5% to 10% increase in yield strength (LT Yield), and a 5% to 37% increase in elongation (LT Elg) over the approximated commercial standard found in column 1. The plates in column 3 also exhibited, in the long-transverse direction, a 2% increase in ultimate tensile strength (LT Ult), a 2% increase in yield strength (LT Yield), and a 1% increase in elongation (LT Elg) when compared to the plates in column 2 that underwent only a stretching operation. In the longitudinal direction, the plates in column 3 exhibited a 5% to 9% increase in ultimate tensile strength (L Ult), a 4% to 8% increase in yield strength (L Yield), and a 10% to 40% increase in elongation (L Elg) over the approximated commercial standard. The cold rolled and stretched plates also exhibited, in the longitudinal direction, a 2% increase in ultimate tensile strength (L Ult), a 2% increase in yield strength (L Yield), and a 2% increase in elongation (L Elg) when compared to the plates found in column 2. When compared to the approximated commercial standard found in column 1, the plates in column 3 exhibited a 5% to 9% increase in longitudinal compressive yield strength (L Comp Yield). When compared to the plates in column 2, the plates in column 3 exhibited a 6% increase in longitudinal compressive yield strength (L Comp Yield).
As can be seen in Table 1, the cold rolled and stretched plates in column 3 exhibited a 13% to 27% increase in fracture toughness over the approximated commercial standard in the “T-L” direction, a 12% to 26% increase in fracture toughness over the approximated commercial standard in the “L-T” direction, and an 8% increase in fracture toughness in the “T-L” direction when compared to the plates in column 2.
In addition to tensile properties, Table 1 also shows that the plates in column 3 exhibited an EA-EB rating, which is a higher rating than the commercially accepted EC rating, in the ASTM G34 EXCO 48 hour corrosion test.
Having described the presently preferred embodiments, it is to be understood that the invention may be otherwise embodied within the scope of the appended claims.
Claims
1. A method of producing an aluminum sheet or plate product comprising:
- providing an aluminum alloy stock;
- hot working said aluminum alloy stock;
- side sawing said aluminum alloy stock;
- solution heat treating and quenching said aluminum alloy stock;
- cold rolling said aluminum alloy stock to reduce the thickness of said aluminum alloy stock by about 0.25% to about 5%; and
- stretching said aluminum alloy stock.
2. A method according to claim 1 wherein:
- providing an aluminum alloy stock selected from the 2XXX, 6XXX, or 7XXX series of aluminum alloys.
3. A method according to claim 1 wherein:
- hot working comprises preheating and hot rolling.
4. A method according to claim 1 wherein:
- solution heat treating said aluminum alloy stock from about 870° F. to about 1050° F.
5. A method according to claim 2 wherein:
- solution heat truncating said 7XXX aluminum alloy stock from about 880° F. to about 900° F.
6. A method according to claim 2 wherein:
- solution heat treating said 2XXX aluminum alloy stock from about 900° F. to about 930° F.
7. A method according to claim 2 wherein:
- solution heat treating said 6XXX aluminum alloy stock from about 950° F. to about 1050° F.
8. A method according to claim 1 wherein:
- stretching said aluminum alloy stock by about 0.5% to about 4%.
9. A method according to claim 1 wherein:
- cold rolling and stretching said aluminum alloy stock by about 2% to about 6%.
10. An aluminum sheet or plate exhibiting improved flatness and mechanical strength made by a process comprising:
- providing an aluminum alloy stock;
- hot working said aluminum alloy stock;
- side sawing said aluminum alloy stock;
- solution heat treating and quenching said aluminum alloy stock;
- cold rolling said aluminum alloy stock to reduce the thickness of said aluminum alloy stock by about 0.25% to about 5%; and
- stretching said aluminum alloy stock.
11. An aluminum sheet or plate according to claim 10 wherein:
- providing an aluminum alloy stock selected from the 2XXX, 6XXX, or 7XXX series of aluminum alloys.
12. An aluminum sheet or plate according to claim 10 wherein:
- hot working comprises preheating and hot rolling.
13. An aluminum sheet or plate according to claim 10 wherein:
- solution heat treating said aluminum alloy stock from about 870° F. to about 1050° F.
14. An aluminum sheet or plate according to claim 11 wherein:
- solution heat treating said 7XXX aluminum alloy stock from about 880° F. to about 900° F.
15. An aluminum sheet or plate according to claim 11 wherein:
- solution heat treating said 2XXX aluminum alloy stock from about 900° F. to about 930° F.
16. An aluminum sheet or plate according to claim 11 wherein:
- solution heat treating said 6XXX aluminum alloy stock from about 950° F. to about 1050° F.
17. An aluminum sheet or plate according to claim 10 wherein:
- stretching said aluminum alloy stock by about 0.5% to about 4%.
18. An aluminum sheet or plate according to claim 10 wherein:
- cold rolling and stretching said aluminum alloy stock by about 2% to about 6%.
19. A method of producing an aluminum sheet or plate product comprising:
- providing an aluminum alloy stock;
- hot working said aluminum alloy stock;
- side sawing said aluminum alloy stock;
- solution beat treating and quenching said aluminum alloy stock;
- cold rolling said aluminum alloy stock to reduce the thickness of said aluminum alloy stock by about 0.25% to about 5%; and
- stretching said aluminum alloy stock by at about 0.5% to about 4%.
20. A method according to claim 19 wherein:
- providing an aluminum alloy selected from the 2XXX, 6XXX, or 7XXX scrics of aluminum alloys.
21. A method according to claim 19 wherein:
- hot working comprises preheating and hot rolling.
22. A method according to claim 19 wherein:
- solution heat treating said aluminum alloy stock from about 870° F. to about 1050° F.
23. A method according to claim 20 wherein:
- solution heat treating said 7XXX aluminum alloy stock from about 880° F. to about 900° F.
24. A method according to claim 20 wherein:
- solution heat treating said 2XXX aluminum alloy stock from about 900° F. to about 930° F.
25. A method according to claim 20 wherein:
- solution heat treating said 6XXX aluminum alloy stock from about 950° F. to about 1050° F.
26. A method according to claim 19 wherein:
- cold rolling and stretching said aluminum alloy stock by about 2% to about 6%.
Type: Application
Filed: Dec 7, 2004
Publication Date: Jun 8, 2006
Applicant:
Inventors: Lynn Oswald (Bettendorf, IA), Greg Venema (Bettendorf, IA), Robert Schultz (Leechburg, PA)
Application Number: 11/006,141
International Classification: C22F 1/04 (20060101);