AU578828B2

AU578828B2 - High strength, ductile, low density aluminum base-lithium- zirconium alloys

Info

Publication number: AU578828B2
Application number: AU57749/86A
Authority: AU
Inventors: Colin Mclean Adam; Richard Lister Bye Jr.; Santosh Kumar Das; Nack Joon Kim
Original assignee: Allied Corp
Current assignee: Allied Corp
Priority date: 1985-07-08
Filing date: 1986-04-11
Publication date: 1988-11-03
Anticipated expiration: 2006-04-11
Also published as: JPS62502295A; EP0229075B1; AU5774986A; JPS648066B2; EP0229075A1; DE3665884D1; CA1280342C; WO1987000206A1

Description

DESCRIPTION

HIGH STRENGTH, DUCTILE, LOW DENSITY ALUMINUM

ALLOYS AND PROCESS FOR MAKING SAME

1. Field of the Invention The invention relates to a process for making high strength, high ductility, low density aluminum-based alloys, and, in particular, to the alloys that are characterized by a homogeneous distribution of composite

10 precipitates in the aluminum matrix thereof. The microstructure is developed by heat treatment method consisting of initial solutionizing treatment followed by multiple aging treatments,

2. Background of the Invention

₁ _. There is a growing need for structural alloys with improved specific strength to achieve substantial weight savings in aerospace applications. Aluminum-lithium alloys offer the potential of meeting the weight savings due to the pronounced effects of lithium on the mechanical and physical properties of aluminum alloys.

20 The addition of one weight percent lithium ( ~3.5 atom percent) decreases the density by ~3% and increases the elastic modulus by ~6% , hence giving a substantial increase in the specific modulus (E/ p ). Moreover,

25 heat treatment of alloys results in the precipitation of a coherent, metastable phase, δ' (AI3L1) which offers considerable strengthening. Nevertheless, development and widespread application of the Al-Li alloy system have been impeded mainly due to its inherent

30 brittleness.

It has been shown that the poor toughness of alloys in the Al-Li system is due to brittle fracture along the grain or subgrain boundaries. The two dominant micro- structural features responsible for their brittleness -.

_. appear to be the precipitation of intermetallic phases along the grain and/or subgrain boundaries and the marked planar slip in the alloys, which create stress concentrations at the grain boundaries. The inter- granular precipitates tend to embrittle the boundary, and simultaneously extract Li from the boundary region to form precipitate free zones which act as sites of strain localization. The planar slip is largely due to . the shearable nature of δ' precipitates which result in decreased resistance to dislocation slip on planes containing the sheared δ¹ precipitates.

Several metallurgical approaches have been under¬ taken to circumvent these problems. It has been found that the PFZ (precipitate free zone) and precipitate-

10 induced intergranular fracture can be reduced by controlling processing to avoid the intergranular precipitation of stable Al-Li, Al-Cu-Li, Al-Mg-Li phases. The problem of planar slip can be partly alleviated by promoting slip dispersion through the addition of dispersoid forming elements and the controlled co-precipitation of Al-Cu-Li, Al-Cu-Mg and/or Al-Li«Mg intermetallics. The dispersoid forming elements include Mn, Fe, Co, etc. The co-precipitation of Cu and/or Mg containing intermetallics appears to be relatively effective in dispersing the dislocation movement. However, the sluggish formation of these intermetallics requires the thermomechanical treatments involving stretching operations and multiple aging

__ treatments (P.J. Gregson and M.M. Flower, Acta

Metallu-rgica., vol. 33, pp. 527-537, 1985), or a high Cu content which adversely affects the density of alloys (B van der Brandt, P.J. von den Brink, H.F. de Jong, L. Katgerman, and H. Kleinjan, in "Aluminum-Lithium Alloy

_3Q II", Metallurgical Society of AIME, pp. 433-446, 1984). Moreover, the properties of alloys thus processed were less than satisfactory.

Recently., a new approach has been suggested to modify the deformation behavior of Al-Li alloy system

_ through the development of Zr modified δ' precipitate. This approach is based on the observation that the metastable A^Zr phase in the Al-Zr alloy system is highly resistant to dislocation shear and is of the same crystal structure (LI2) as δ' . In this regard, attempts have been made to produce a ternary ordered composite l3(Li, Zr) phase in the aluminum matrix with an alloy of Al-2.34 Li-1.07Zr (F.W. Gayle and J.B. Vander Sande, Scripta Metallurgica, Vol. 18, pp. 473-478, 1984). However, the process for developing a homogeneous dis¬ tribution of such phase has required the strict control of processing parameters during the thermomechanical processing, as well as prolonged solutionizing and/or aging treatments. From the practical point of view, this process is quite undesirable and may also result in undesirable microstructural features such as recrystal- lization and wide precipitate free zones. Moreover, the process cannot be effectively applied to low Zr (e.g., 0.2 wt% Zr) containing alloys which produce a small volume fraction of heterogeneously distributed coarse composite precipitates (P.L. Makin and B. Ralph, Journal of Materials Science, vol. 19, pp. 3835-3843, 1984; P.J. Gregson and H.M. Flower, Journal of Materials Science Letters, vol. 3, pp. 829-834, 1984; P.L. Makin, D.J. Lloyd, and W.M. Stobbs, Philosophical Magazine A, vol. 51, pp. L41-L47, 1985).

Despite considerable efforts to develop low density aluminum alloys, conventional techniques, such as those discussed above, have been unable to provide low density aluminium alloys having the sought for combination of high strength, high ductility and low density. As a result, conventional aluminum-lithium alloy systems have not been entirely satisfactory for applications such as aircraft structural components, wherein high strength, high ductility and low density are required.

SUMMARY OF THE INVENTION

The present invention provides a process for making aluminium-lithium alloys containing a high density of substantially uniformly distributed shear resistant dispersoids which markedly improve the strength and ductility thereof. The low density aluminum-base alloys, of the invention consist essentially of the formula ^Albal^Zra^L b^xc wherein X is at least one element selected from the group consisting of Cu, Mg, Si, Sc, Ti, U, Hf, Cr, V, Mn, Fe, Co and Ni, "a" ranges from about 0.15-2 wt%, "b" ranges from about 2.5-5 wt%, "c" . ranges from about 0-5 wt% and the balance is aluminum. The icrostructure of these alloys is characterized by the precipitation of composite Al^Li, Zr) phase in the aluminum matrix thereof. This microstructure is developed in accordance with the process of the present

10 invention by subjecting an alloy having the formula delineated above to solutionizing treatment followed by multiple aging treatments. An improved process for making high strength, high ductility, low density aluminum-based alloy is thereby provided wherein the ,.. aluminum-based alloy produced has an improved combination of strength and ductility (at the same density) .

The high strength, high ductility, low density aluminum-based alloy produced in accordance with the present invention has a controlled composite Alo(Li, Zr) precipitate which, advantageously, offers a wide range of strength and ductility combinations.

BRIEF DESCRIPTION OF THE DRAWINGS

The invention will be more fully understood and -,- further advantages will become apparent when reference is made to the following detailed description and the accompanying drawings, in which:

Fig. 1 is a dark field transmission electron micro¬ graph of an alloy having the composition Al-3.lLi-2Cu-

30 lMg-0.5Zr, the alloy having been subjected to double aging treatments (170°C for 4 hrs. followed by 190°C for 16 hrs.) to develop a composite precipitate in the aluminum matrix thereof;

Fig. 2 is a weak beam dark field micrograph of an 5 alloy having the composition Al-3.7Li-0.5Zr, illustrating the resistance of the composite precipitate to dislocation shear during deformation;

Fig. 3(a) shows the planar slip observed in an alloy having the composition Al-3.7Li-0.5Zr, the alloy having been subjected to a conventional aging treatment (180°C for 16 hours) ;

Fig. 3(b) shows the beneficial effect of subjecting the alloy of Fig.3(a) to treatment in accordance with the claimed process (160°C for 4 hrs. followed by 180°C for 16 hrs.), thereby promoting the homogeneous deformation thereof;

Fig. 4 shows the sheared δ' precipitates observed

10 in an alloy having the composition Al-3.lLi-2Cu-lMg- 0.5Zr, the alloy having been subjected to a conventional aging treatment (190°C for 16 hours) ; and

Fig. 5 shows the development of composite precipi¬ tates in an alloy having the composition Al-3.2Li-3Cu- 1.5Mg-0.2Zr, the alloy having been subjected to

15 treatment in accordance with the claimed process (170°C for 4 hrs. followed by 190°C for 16 hrs) .

DESCRIPTION OF THE PREFERRED EMBODIMENTS

In general, the present invention relates to the process of making high strength, high ductility, and low

20 density Al-Li-Zr-X alloys. The process involves the use of multiple aging steps during heat treatment of the alloy. The alloy is characterized by a unique micro¬ structure consisting essentially of "composite" __ Al (Li,Zr) precipitate in an aluminum matrix (Fig. 1) due to the heat treatment as hereinafter described. The alloy may also contain other Li, Cu and/or Mg containing precipitates provided such precipitates do not significantly deteriorate the mechanical and physical 0 properties of the alloy.

The factors governing the properties of the Al-Li- Zr-X alloys are primarily its Li content and micro¬ structure and secondarily the residual alloying elements. The microstructure is determined largely by the composition and the final thermomechanical 5 treatments such as extusion, forging and/or heat treatment parameters. Normally, an alloy in the as- processed condition (cast, extruded or forged) has large intermetallic particles. Further processing is required to develop certain microstructural features for certain characteristic properties.

The alloy is given an initial solutionizing treat- ₅ ment, that is, heating at a temperature ( τ_) for a period of time sufficient to substantially dissolve most of the intermetallic particles present during the forging or extrusion process, followed by cooling to ambient temperature at a sufficiently high rate to _lπ retain alloying elements in said solution. Generally, the time at temperature T-_j_, will be dependent on the composition of the alloy and the method of fabrication (e.g., ingot cast, powder metallargy processed) and will typically range from about 0.1 to 10 hours. The alloy

₁₅ is then reheated to an aging temperature, T2, for a period of time sufficient to activate the nucleation of composite Al3(Li, Zr) precipitates, and cooled to ambient temperature, followed by a second aging treatment at temperature, T3, for a period of time sufficient for the growth of the composite Al (Li, Zr) precipitate and a dissolution <~s ~ 5' precipitate whose nucleation is not aided by Zr. The alloy at this point is characterized by a unique mⁱcrostructure which con¬ sists essentially of composite Al (Li, Zr) precipi-

- tate. This composite AI (Li, Zr) precipitate is re¬ sistant to dislocation shesr and quite effective in dispersing dislocation motion (Fig. 2). The result is that the alloy containing an optimum amount of composite Al3(Li, Zr) precipitate deforms.-by a homogeneous mode of

__n deformation resulting in improved mechanical properties. Fig. 3(b) clearly shows the homogeneous mode of deformation in an alloy subjected to the process claimed in this invention, while Fig . 3(a) shows the severe planar slip observed in a conventionally

__ processed alloy due to the shearing of δ¹ precipitates by dislocations (see Fig. 4). The combination of ductility with high strength is best achieved in accordance with the invention when the density of the shear resistant dispersoids ranges from about 10 to 60 percent by volume, and preferably from about 20-40 percent by volume.

The exact temperature, Tη_, to which the alloy is heated in the solutionizing step is not critical as long as there is a dissolution of intermetallic particles at this temperature. The exact temperature, T2, in the first aging step where the nucleation of composite AI3 (Li, Zr) precipitate is promoted, depends upon the alloying elements present and upon the final aging step. The optimum temperature range for T2, is from about 100°C to 180°C. The exact temperature, T3, whose range is from 120°C to 200°C, depends on the alloying elements present and mechanical properties desired. Generally,^" the times at temperatures T2 and T3 are different depending upon the composition of the alloy and the thermomechanical processing history, and will typically range from about 0.1 to 100 hours.

EXAMPLE 1

The ability of composite Al (Li, Zr) precipitates to modify the deformation behavior of Al-Li-Zr alloys is illustrated as follows:

Fig. 2 is a weak beam dark field transmission electron micrograph showing microstructure of a deformed alloy (Al-3.7Li-0.5Zr) which has. been solutionized at 540°C for 4 hrs. and subsequently ayed at 160°C for 4 hrs. followed by final aging at 180°C for 16 hrs. Such heat treatment promotes the precipitation of. composite Al₃(Li, Zr) which is highly resistant to dislocation shear and is quite effective in dispersing the dislocation movement.

Fig. 3(a) shows a bright field electron micrograph showing microstructure of a deformed alloy (Al-3.7Li- 0.5Zr) which has not been given the claimed process. The alloy had been aged, for 16 hrs. at 180°C after solutionizing at 540° for 4 hrs. This alloy showed the pronounced planar slip which is the common deformation characteristic of brittle alloy. In contrast, Fig. 3(b) illustrates the beneficial effect of the claimed process on the deformation behavior of an alloy having the composition Al-3.7Li- 0.5Zr. After solutionizing at 540°C for 4 hrs., the alloy had been subjected to the double aging treatment of 160°C for 4 hrs. and 180°C for 16 hrs. The deformation mode of this alloy is quite homogeneous indicating high ductility.

Example 2

An alloy having a composition of Al-3.lLi-2Cu-lMg- 0.5Zr was developed for medium strength applications as shown in Table I. The alloy was solutionized at 540°C for 2.5 hrs., quenched into water at about 20°C and given conventional single aging and the claimed double aging treatments.

TABLE I

0.2% Yield Ultimate Tensile Elongation to Strength (MPa) Strength (MPa) Failure (%) Aged at 190°C for 16 hrs. 524 592 3.6

Aged at 170°C for 4 hrs. and

190°C for 16 hrs. 530 606 6.1

Conventional aging treatment (190°C for 16 hrs.) showed poor ductility (3.6%) due to the shearing of δ' precipitate (Fig. 4) , while composite precipitate developed by double aging (Fig. 1) improve both strength and ductility (6.1% elongation) .

Example 3 A high strength Al-Li alloy was made to satisfy the requirements for high strength applications for aero¬ space structure. An alloy having a composition of Al- 3.2Li-2Cu-2Mg-0.5Zr was solutionized at 542°C for 4 hrs. As shown in Table II, conventional aging treatment (190°C for 16 hrs.) showed lower strength (yield strength of 521 MPa) and ductility (3.6%) . However, double aging of the alloy (160°C for 4 hrs. followed by 180°C for 16 hrs.) gave significantly higher strength _\jield strength of 554 MPa) and ductility (5.5%) , which meets property requirements for high strength alloys needed for aerospace structural applications.

TABLE II

0.2% Yield Ultimate Tensile Elongation Strength (MPa) Strength (MPa) to Failure (%) Aged at 190°C for 16 hrs. 521 595 3.6

Aged at 160°C for 4 hrs. and 180°C for 16 hrs. 554 631 5.5 Example 4 This example illustrates the beneficial effect of the claimed process on the mechanical properties of a simple ternary alloy Al-3.7Li-0.5Zr. The alloy was solutionized at 540°C for 4 hrs., and subsequently aged as shown in Table IIJ. The resulting tensile properties show that the claimed process results in improved strength and ductility compared to the conventional process.

TABLE III

Aging Treatment 0.2% Yield Ultimate Tensile .Elongation to Strength (MPa) Strength (MPa) Fracture (%)

140°C, 16 hr. 424 442 4.2

120°C, 4 hr. +

140°C, 16 hr. 434 460 6.0

160°C, 16 hr. 419 431 3.2

140°C, 4 hr. +

160°C, 16 hr. 425 448 4.8

140°C, 16 hr. +

160°C, 16 hr. 426 451 45

Example 5

A wide range of mechanical properties can be achieved by using multiple aging conditions. Fo^r - . example, a triple aging treatment (120°C, 4 hrs. + 140°C, 16 hrs. + 160°C, 4 hrs.) produced yield strength of 446 MPa and ultimate tensile strength of 464 MPa with 4.6% elongation. As a result, a variety of heat treatments of the alloys according to the claims can be employed to produce alloys having a variety of mechanical properties. ^

Example 6

This example illustrates the potential of the claimed process for the development of composite pre¬ cipitate in low Zr containing Al-Li alloys. Fig. 5 shows the dark field electron micrograph of a typical alloy Al-3.2Li-3Cu-l.5Mg-0.2Zr which had been solutionized at 540°C for 4 hrs., reheated to 170°C for 4 hrs. followed by final aging at 190°C for 16 hrs. The large volume fraction of composite Al₃ (Li, Zr) precipi¬ tate observed in suc an alloy indicates that the claimed process is also quite effective in Al-Li alloys having low Zr content of 0.2%. Having thus described the invention in rather full detail, it will be understood that such detail need not be strictly adhered to but that further changes and modifications may suggest themselves to one skilled in the art, all falling within the scope of the present invention as defined by the subjoined claims.

Claims

What is claimed is:

1. A process for increasing the strength and ductility of low density aluminum-base alloys comprising the steps of subjecting an Al-Li alloy, to multiple aging treatments to form therein a microstructure wherein a high density of shear resistant dispersoids are substantially uniformly distributed, said alloy consisting essentially of the formula Al_j:)aτ_Zr_aLi_j:)X_c, wherein X is at least one element selected from the

10 group consisting of Cu, Mg, Si, Sc, Ti, U, Hf, Be, Cr, V, Mn, Fe, Co and Ni, "a" ranges from about 0.15-2 wt%, "b" ranges from about 2.5-5 wt%, "c" ranges from 0 to about 5 wt% and the balance is aluminum.

2. A process according to claim 1 wherein said alloy is characterized by the precipitation of composite

15 AI3 (Li, Zr). phase in an aluminum matrix.

3. A process as recited by claim 1, wherein the number of aging treatments ranges from 2 to 10.

4. A process as recited by claim 1, wherein the number of aging treatments ranges from 2 to 5.

20

5. A process for making high strength, high ductility, low density aluminum-lithium.alloy, comprising the steps of: heatjng an aluminum alloy, consisting essentially - _. of the for ul.?. Al_]-)aτ_Zr_aLi_]:)χc, wherein X is at least one element selected from the group consisting of Cu, Mg, V, Si, Sc, T_ , U, Hf, Be, Cr, Mn, Fe, Co and Ni, "a" ranges from about 0.15-2 wt%, "b" ranges from about 2.5-5wt%, "c" ranges fro ^-^G to about 5 wt% and balance of 0 aluminum, to a temperature, T-_j_, for a period of time sufficient to substantially dissolve most of the intermetalliσ particles therein; cooling said al_Loy to ambient temperature at rates sufficient to retain its elements in supersaturated 5 solid solution; heating said alloy to a temperature, T2, for a period of time sufficient to activate nucleation of composite AI3 (Li, Zr) precipitates; cooling said alloy to ambient temperature; heating said alloy to a temperature, T3, for a period of time sufficient to effect additional growth of composite AI3 (Li, Zr) precipitates, and dissolution of δ' precipitates whose nucleation is not aided by Zr; and cooling said alloy to ambient temperature to produce therein a controlled precipitation of composite AI3 (Li, Zr) phase in said aluminum matrix.

10 6. A process according to claim 1, further comprising the step of stretching said solutionized alloy.

7. A process according to claim 5, further comprising the step.,of stretching said alloy.

, _.

8. ,A process according to claim 5 wherein -^ ranges from about 50.0^oC to 555°C, T₂ ranges from about 100°C to 180°C and T3 ranges from about 120°C to 200°C.

20

5

0

5