High performance AlSiMgCu casting alloy

Abstract

New aluminum casting alloys having 8.5-9.5 wt. % silicon, 0.8-2.0 wt. % copper (Cu), 0.20-0.53 wt. % magnesium (Mg), and 0.35 to 0.8 wt. % manganese are disclosed. The alloy may be solution heat treated, treated in accordance with T5 tempering and/or artificially aged to produce castings, e.g., for cylinder heads and engine blocks. In one embodiment, the castings are made by high pressure die casting.

Claims

1. An aluminum casting alloy consisting of: 8.5-9.5 wt. % silicon; 0.8-1.2 wt. % copper (Cu); wherein 2.5(Cu+10Mg)5.8; 0.36-0.53 wt. % magnesium (Mg); 0.35 to 0.8 wt. % manganese; up to 0.05 wt. % zinc; up to 0.01 wt. % silver; up to 0.05 wt. % nickel; up to 0.01 wt. % hafnium; 0.10-0.35 wt. % iron; 0.03-0.15 wt. % titanium; 0.07-0.30 wt. % zirconium; 0.07-0.30 wt. % vanadium; wherein 0.14Zr+V0.40 up to 0.03 wt. % of one or more of strontium, sodium and antimony; other elements being 0.04 wt. % each and 0.12 wt. % in total; the balance being aluminum.

2. The alloy of claim 1, wherein the ratio of iron to manganese is 0.5.

3. The alloy of claim 2, wherein the alloy includes from 0.4 to 0.45 wt. % Mg, and wherein 4.7(Cu+10Mg)5.8.

4. The alloy of claim 3, wherein the alloy includes from 0.10 to 0.30 wt. % Fe.

5. The alloy of claim 4, wherein the alloy includes from 0.45-0.70 wt. % Mn.

6. A method comprising: (a) introducing the molten aluminum alloy of claim 1 into a mold; (b) removing a defect-free shape cast article from the mold; and (c) tempering the shape cast article to one of a T5, T6 or T7 temper.

7. The method of claim 6, wherein the mold is a high pressure die casting mold and the step of introducing is by high pressure die casting.

8. The alloy of claim 5, wherein the alloy includes at least 0.08 wt. % of each of Zr and V.

9. The alloy of claim 5, wherein the alloy includes at least 0.09 wt. % of each of Zr and V.

10. The alloy of claim 8, wherein the alloy includes 0.16-0.35 wt. % of Zr+V.

11. The alloy of claim 9, wherein the alloy includes 0.18-0.35 wt. % of Zr+V.

12. The alloy of claim 9, wherein the alloy includes 0.20-0.30 wt. % of Zr+V.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) FIG. 1 is a graph of phase equilibria involving (Al) and liquid in an AlCuMgSi system.

(2) FIG. 2 is a graph of the effect of Cu additions on the solidification path of Al-9% Si-0.4% Mg-0.1% Fe alloy.

(3) FIG. 3 is a graph of the effect of Cu content on phase fractions in Al-9%-0.4% Mg-0.1% Fe-x % Cu alloys.

(4) FIG. 4 is a graph of the effect of Cu and Mg content on the Q-phase formation temperature of Al-9% SiMgCu alloys.

(5) FIG. 5 is a graph of the effect of Mg and Cu content on the equilibrium solidus temperature of Al-9% SiMgCu alloys.

(6) FIG. 6 is a graph of the effect of Mg and Cu content on the equilibrium solidus temperature (T.sub.S) and Q-phase formation temperature (T.sub.Q) of Al-9% SiMgCu alloys.

(7) FIG. 7 is a graph of the effect of zinc and silicon on the fluidity of Al-x % Si-0.5% Mg-y % Zn alloys

(8) FIG. 8 is an SEM (scanning electron micrograph) @200 magnification, showing spherical Si particles and un-dissolved Fe-containing particles.

(9) FIGS. 9a-b are photographs of undissolved Fe-containing particles in the investigated alloys.

(10) FIGS. 10a-d are graphs of the effect of aging condition on tensile properties of the Al-9Si-0.5Mg alloy.

(11) FIGS. 11a-d are graphs of the effect of Cu on tensile properties of the Al-9% Si-0.5% Mg alloy.

(12) FIGS. 12a-d are graphs of the effect of Cu and Zn on tensile properties of the Al-9% Si-0.5% Mg alloy.

(13) FIGS. 13a-d are graphs of the effect of Mg content on tensile properties of the Al-9% Si-1.25% CuMg alloy.

(14) FIGS. 14a-d are graphs of the effect of Ag on tensile properties of the Al-9% Si-0.35% Mg-1.75% Cu alloy.

(15) FIGS. 15a-d are graphs of tensile properties for six alloys aged for different times at an elevated temperature, as described in the disclosure.

(16) FIG. 16 is a graph of Charpy impact energy (CIE) vs. yield strength for five alloys aged for different times at an elevated temperature.

(17) FIG. 17 is a graph of S-N fatigue curves of selected alloys aged at 155 C. for 15 hours. Smooth, Axial; stress ratio=1.

(18) FIG. 18 is a graph of S-N fatigue curves of selected alloys aged at 155 C. for 60 hours. Smooth, Axial; stress ratio=1.

(19) FIG. 19a-d-23a-d are optical micrographs of cross-sections of samples of five alloys as cast and machined and aged for two different time periods at an elevated temperature after 6-hour ASTM G110.

(20) FIG. 24 is a graph of depth of attack of selected alloys aged for different time periods on the as-cast and machined surfaces after a 6-hour G110 test.

(21) FIG. 25 is a graph of Mg and Cu content correlated to strength and ductility for Al-9SiMgCu alloys.

(22) FIG. 26 is a graph of tensile properties of a specific alloy (alloy 9) after exposure to high temperatures.

(23) FIGS. 27a and 27b are scanning electron micrographs of a cross-section of a sample of alloy 9 prior to exposure to high temperatures.

(24) FIGS. 28a-e are a series of scanning electron micrographs of a cross-section of alloy 9 after exposure to increasing temperatures correlated to a tensile property graph of alloy 9 and A356 alloy.

(25) FIG. 29 is a graph of yield strength at room temperature for various alloys.

(26) FIG. 30 is a graph of yield strength after exposure to 175 C. for various alloys.

(27) FIG. 31 is a graph of yield strength after exposure to 300 C. for various alloys.

(28) FIG. 32 is a graph of yield strength after exposure to 300 C. for various alloys.

(29) FIG. 33 is a graph of yield strength after exposure to 300 C. for various alloys.

(30) FIG. 34 is a graph of yield strength after exposure to 300 C. for various alloys.

EXAMPLE 1

High Performance AlSiCuMg Cast Alloys

(31) 1.1 Alloy Development Methods Based on Computational Thermodynamics

(32) To improve the performances of AlSiMgCu cast alloys, a novel alloy design method was used and is described as follows:

(33) In AlSiMgCu casting alloys, increasing Cu content can increase the strength due to higher amount of -Al.sub.2Cu and Q precipitates but reduce ductility, particularly if the amount of un-dissolved constituent Q-phase increases. FIG. 1 shows the calculated phase diagram of the AlCuMgSi quaternary system, as shown in X. Yan, Thermodynamic and solidification modeling coupled with experimental investigation of the multicomponent aluminum alloys. University of WisconsinMadison, 2001, which is incorporated in its entirety by reference herein. FIG. 1 shows the three phase equilibria in ternary systems and the four phase equilibria quaternary monovariant lines. Points A, B, C, D, E and F are five phase invariant points in the quaternary system. Points T1 to T6 are the four-phase invariant points in ternary systems and B1, B2 and B3 are the three phase invariant points in binary systems. The formation of Q-phase (AlCuMgSi) constituent particles during solidification is almost inevitable for an AlSiMg alloy containing Cu since Q-phase is involved in the eutectic reaction (invariant reaction B). If these Cu-containing Q-phase particles cannot be dissolved during solution heat treatment, the strengthening effect of Cu will be reduced and the ductility of the casting will also suffer.

(34) In order to minimize/eliminate un-dissolved Q-phase (AlCuMgSi) and maximize solid solution/precipitation strengthening, the alloy composition, solution heat treatment and aging practice should be optimized. In accordance with the present disclosure, a thermodynamic computation was used to select alloy composition (mainly Cu and Mg content) and solution heat treatment for avoiding un-dissolved Q-phase particles. Pandat thermodynamic simulation software and the PanAluminum database LLC, Computherm, Pandat Software and PanAluminum Database. http://www.computherm.com were used to calculate these thermodynamic data.

(35) The inventors of the present disclosure recognize that adding Cu to AlSiMg cast alloys will change the solidification sequence. FIG. 2 shows the predicted effect of 1% Cu (all compositions in this report are in weight percent) on the solidification path of Al-9% Si-0.4% Mg-0.1% Fe. More particularly, the solidification temperature range is significantly increased with the addition of 1% Cu due to the formation of Cu-containing phases at lower temperatures. For the Al-9% Si-0.4% Mg-0.1% Fe-1% Cu alloy, Q-AlCuMgSi formed at 538 C. and Al.sub.2Cu phase formed at 510 C. The volume fraction of each constituent phase and their formation temperatures are also influenced by the Cu content.

(36) FIG. 3 shows the predicted effect of Cu content on phase fractions in Al-9% Si-0.4% Mg-0.1% Fe-x % Cu alloys. As the Cu content increases, the amount of -Al.sub.2Cu and Q-AlCuMgSi increases while the amount of Mg.sub.2Si and -AlFeMgSi decreases. In alloys with more than 0.7% Cu, Mg.sub.2Si phase will not form during solidification. The amount of Q-AlCuMgSi is also limited by the Mg content in the alloy if the Cu content is more than 0.7%.

(37) The Q-AlCuMgSi phase formation temperature (T.sub.Q) in Al-9% SiMgCu alloys is a function of Cu and Mg content. The formation temperature of a constituent phase is defined as the temperature at which the constituent phase starts to form from the liquid phase. FIG. 4 shows the predicted effects of Cu and Mg content on the formation temperature of Q-AlCuMgSi phase. The formation temperature of Q-AlCuMgSi phase decreases with increasing Cu content; but increases with increasing Mg content.

(38) In accordance with the present disclosure, in order to completely dissolve all the as-cast Q-AlCuMgSi phase particles, the solution heat treatment temperature (T.sub.H) needs to be controlled above the formation temperature of the Q-AlCuMgSi phase, i.e., T.sub.H>T.sub.Q. The upper limit of the solution heat treatment temperature is the equilibrium solidus temperature (T.sub.S) in order to avoid re-melting. As a practical measure, the solution heat treatment temperature is controlled to be at least 5 to 10 C. below the solidus temperature to avoid localized melting and creation of metallurgical flaws known in the art as rosettes. Hence, in practice, the following relationship is established:
T.sub.S10 C.>T.sub.H>T.sub.Q(1)

(39) In accordance with the present disclosure, to achieve this criterion, the alloy composition, mainly the Cu and Mg contents, should be selected so that the formation temperature of Q-AlCuMgSi phase is lower than the solidus temperature. FIG. 5 shows the predicted effects of Cu and Mg content on the solidus temperature of Al-9% SiCuMg alloys. As expected, the solidus temperature decreases as the Cu and Mg content increases. It should be noted that Mg content increases the formation temperature of the Q-AlCuMgSi phase but decreases the solidus temperature as indicated in FIG. 6. The Q-AlCuMgSi phase formation temperature surface and the (T.sub.S10 C.) surface (10 C. below the solidus temperature surface) are superimposed in FIG. 6. These two surfaces intersect along the curve A-B-C. The area that meets the criterion of Equation (1) is on the right hand side of curve A-B-C, i.e., T.sub.Q<T.sub.S10 C. Projection of the curve A-B-C to the CuMg composition plane yields the center line Cu+10Mg=5.25 of the preferred composition boundary, as shown in FIG. 25. The lower boundary, Cu+10Mg=4.73, was defined by the intersection of the Q-AlCuMgSi phase formation temperature surface and the (T.sub.S15 C.) surface (15 C. below the solidus temperature surface). The upper boundary, Cu+10Mg=5.78, was defined by the intersection of the Q-AlCuMgSi phase formation temperature surface and the (T.sub.S5 C.) surface (5 C. below the solidus temperature surface). For Al-9% Si-0.1% Fe-x % Cu-y % Mg alloys, Q-AlCuMgSi phase particles can be completely dissolved during solution heat treatment when the Cu and Mg contents are controlled within these boundaries.

(40) In accordance with the present disclosure, the preferred Mg and Cu content to maximize the alloy strength and ductility is shown in FIG. 25.

(41) The preferred relationship of Mg and Cu content is defined by:
Cu+10Mg=5.25 with 0.5<Cu<2.0
The upper bound is Cu+10Mg=5.8 and the lower bound is Cu+10Mg=4.7.

(42) The foregoing approach allows the selection of a solutionization temperature by (i) calculating the formation temperature of all dissolvable constituent phases in an aluminum alloy; (ii) calculating the equilibrium solidus temperature of an aluminum alloy; (iii) defining a region in AlCuMgSi space where the formation temperature of all dissolvable constituent phases is at least 10 C. below the solidus temperature. The AlCuMgSi space is defined by the relative % composition of each of Al, Cu, Mg and Si and the associated solidus temperatures for the range of relative composition. For a given class of alloy, e.g., AlCuMgSi, the space may be defined by the solidus temperature associated with relative composition of two elements of interest, e.g., Cu and Mg, which are considered relative to their impact on the significant properties of the alloy, such as tensile properties. In addition, the solutionizing temperature may be selected to diminish the presence of specific phases, e.g., that have a negative impact on significant properties, such as, tensile properties. The alloy, e.g., after casting, may be heat treated by heating above the calculated formation temperature of the phase that needs to be completely dissolved after solution heat treatment, e.g., the Q-AlCuMgSi phase, but below the calculated equilibrium solidus temperature. The formation temperature of the phase that needs to be completely dissolved after solution heat treatment and solidus temperatures may be determined by computational thermodynamics, e.g., using Pandat software and PanAluminum Database available from CompuTherm LLC of Madison, Wis.

(43) 1.2 Composition Selection for Tensile Bar Casting

(44) Based on the foregoing analysis, several Mg and Cu content combinations were selected as given in Table 3. Additionally, studies by the present inventors have indicated that an addition of zinc with a concentration greater than 3 wt % to AlSiMg(Cu) alloys can increase both ductility and strength of the alloy. As shown in FIG. 7, zinc can also increase the fluidity of AlSiMg alloys. Thus, an addition of zinc (4 wt %) was also evaluated. It has also been reported L. A. Angers, Development of Advanced I/M 2xxx Alloys for High Speed Civil Transport Applications, Alloy Technology Division Report No. AK92, 1990-04-16 that an addition of Ag can accelerate age-hardening of high Cu-containing (>1.5 wt %) aluminum alloys, and increase the tensile strength at room temperature and elevated temperature. An addition of Ag (0.5 wt %) was also included in alloys with higher Cu content such as 1.75 wt % Cu. Hence, ten alloy compositions were selected for evaluation. The target compositions of these alloys are given in Table 3. It should be noted that alloy 1 in Table 3 is the baseline alloy, A359.

(45) TABLE-US-00001 TABLE 3 Target Compositions (all values in weight percent) Alloy Si Cu Mg Zn Ag Fe Sr* Ti B 1 Al9Si0.5Mg 9 0 0.5 0 0 <0.1 0.0125 0.04 0.003 2 Al9Si0.35Mg0.75Cu4Zn 9 0.75 0.35 4 0 <0.1 0.0125 0.04 0.003 3 Al9Si0.45Mg0.75Cu4Zn 9 0.75 0.45 4 0 <0.1 0.0125 0.04 0.003 4 Al9Si0.45Mg0.75Cu 9 0.75 0.45 0 0 <0.1 0.0125 0.04 0.003 5 Al9Si0.5Mg0.75Cu 9 0.75 0.5 0 0 <0.1 0.0125 0.04 0.003 6 Al9Si0.35Mg1.25Cu 9 1.25 0.35 0 0 <0.1 0.0125 0.04 0.003 7 Al9Si0.45Mg1.25Cu 9 1.25 0.45 0 0 <0.1 0.0125 0.04 0.003 8 Al9Si0.55Mg1.25Cu 9 1.25 0.55 0 0 <0.1 0.0125 0.04 0.003 9 Al9Si0.35Mg1.75Cu 9 1.75 0.35 0 0 <0.1 0.0125 0.04 0.003 10 Al9Si0.35Mg1.75Cu0.5Ag 9 1.75 0.35 0 0.5 <0.1 0.0125 0.04 0.003

(46) A modified ASTM tensile-bar mold was used for the casting. A lubricating mold spray was used on the gauge section, while an insulating mold spray was used on the remaining portion of the cavity. Thirty castings were made for each alloy. The average cycle time was about two minutes. The actual compositions investigated are listed in Table 4, below.

(47) TABLE-US-00002 TABLE 4 Actual Compositions (all values in weight percent) Alloy Si Cu Mg Zn Ag Fe Sr* Ti B 1 Al9Si0.5Mg 8.87 0.021 0.48 0 0 0.079 0.0125 0.05 0.003 2 Al9Si0.35Mg0.75Cu4Zn 9.01 0.75 0.37 4.03 0 0.077 0.0125 0.031 0.003 3 Al9Si0.45Mg0.75Cu4Zn 9.09 0.75 0.46 4.02 0 0.081 0.0125 0.04 0.003 4 Al9Si0.45Mg0.75Cu 9.18 0.76 0.45 0 0 0.083 0.0125 0.042 0.003 5 Al9Si0.5Mg0.75Cu 9.02 0.77 0.49 0 0 0.081 0.0125 0.013 0.003 6 Al9Si0.35Mg1.25Cu 9.02 1.25 0.34 0 0 0.088 0.0125 0.03 0.003 7 Al9Si0.45Mg1.25Cu 9.11 1.28 0.44 0 0 0.082 0.0125 0.04 0.003 8 Al9Si0.55Mg1.25Cu 8.99 1.27 0.53 0 0 0.1 0.0125 0.04 0.003 9 Al9Si0.35Mg1.75Cu 9.29 1.83 0.37 0 0 0.08 0.0125 0.048 0.003 10 Al9Si0.35Mg1.75Cu0.5Ag 8.88 1.78 0.35 0 0.5 0.081 0.0125 0.044 0.003
The actual compositions are very close to the target compositions. The hydrogen content (single testing) of the castings is given in Table 5.

(48) TABLE-US-00003 TABLE 5 Hydrogen Content of the Castings Alloy H Content (ppm) 1 Al9Si0.5Mg 0.14 2 Al9Si0.35Mg0.75Cu4Zn 0.11 3 Al9Si0.45Mg0.75Cu4Zn 0.19 4 Al9Si0.45Mg0.75Cu 0.11 5 Al9Si0.5Mg0.75Cu 0.14 6 Al9Si0.35Mg1.25Cu 0.15 7 Al9Si0.45Mg1.25Cu 0.13 8 Al9Si0.55Mg1.25Cu 0.16 9 Al9Si0.35Mg1.75Cu 0.13 10 Al9Si0.35Mg1.75Cu0.5Ag Not measured Note: alloy 3 was degassed with porous lance; all other alloys were degassed using a rotary degasser.
1.3 The Preferred Solution Heat Treat Temperature as a Function of Cu and Mg

(49) To dissolve all the Q-AlCuMgSi phase particles, the solution heat treatment temperature should be higher than the Q-AlCuMgSi phase formation temperature. Table 6 lists the calculated final eutectic temperature, Q-phase formation temperature and solidus temperature using the targeted composition of the ten alloys investigated.

(50) TABLE-US-00004 TABLE 6 Calculated Final Eutectic Temperature, Q-phase Formation Temperature and Solidus Temperature for Ten Investigated Casting Alloys Final eutectic Q-phase Solidus temper- forming temper- ature, temperature, ature, Alloy C. C. C. 1 Al9Si0.5Mg 560 563 2 Al9Si0.35Mg0.75Cu4Zn 470 518 540 3 Al9Si0.45Mg0.75Cu4Zn 470 518 543 4 Al9Si0.45Mg0.75Cu 510 541 554 5 Al9Si0.5Mg0.75Cu 510 541 553 6 Al9Si0.35Mg1.25Cu 510 533 552 7 Al9Si0.45Mg1.25Cu 510 536 548 8 Al9Si0.55Mg1.25Cu 510 538 545 9 Al9Si0.35Mg1.75Cu 510 528 543 10 Al9Si0.35Mg1.75Cu0.5Ag 510 526 543
Based on the above mentioned information, two solution heat treatment practices were defined and used. Alloys 2, 3, 9 and 10 had lower solidus temperature and/or lower final eutectic/Q-phase formation temperature than others. Hence a different SHT practice was used.

(51) The practice I for alloys 2, 3, 9 and 10 was: 1.5 hour log heat-up to 471 C. 2 hour soak at 471 C. 0.5 hour ramp up to 504 C. 4 hour soak at 504 C. 0.5 hour ramp up to T.sub.H 6 hour soak at T.sub.H CWQ (Cold Water Quench)
and practice II for other six alloys was: 1.5 hour log heat-up to 491 C. 2 hour soak at 491 C. 0.25 hour ramp up to 504 C. 4 hour soak at 504 C. 0.5 hour ramp up to T.sub.H 6 hour soak at T.sub.H CWQ (Cold Water Quench)
The final step solution heat treatment temperature T.sub.H was determined from following equation based on Mg and Cu content:
T.sub.H( C.)=57010.48*Cu71.6*Mg1.3319*Cu*Mg0.72*Cu*Cu+72.95*Mg*Mg,(2)
where, Mg and Cu are magnesium and copper contents, in wt. %. A lower limit for T.sub.H is defined by:
T.sub.Q=533.620.98*Cu+88.037*Mg+33.43*Cu*Mg0.7763*Cu*Cu126.267*Mg*Mg(3)
An upper limit for T.sub.H is defined by:
T.sub.S=579.210.48*Cu71.6*Mg1.3319*Cu*Mg0.72*Cu*Cu+72.95*Mg*Mg(4)

(52) The microstructure of the solution heat treated specimens was characterized using optical and SEM microscopy. There were no un-dissolved Q-phase particles detected in all the Cu-containing alloys investigated. FIG. 8 shows the microstructure of the Al-9% Si-0.35% Mg-1.75% Cu alloy (alloy #9) in the T6 temper. Si particles were all well-spheroidized. Some un-dissolved particles were identified as -AlFeSi, -AlFeMgSi and Al.sub.7Cu.sub.2Fe phases. The morphologies of these un-dissolved phases are shown in FIG. 9 at higher magnification.

(53) 1.4 Experimental Results

(54) 1.4.1 Property Characterization

(55) Tensile properties were evaluated according to the ASTM B557 method. Test bars were cut from the modified ASTM B108 castings and tested on the tensile machine without any further machining. All the tensile results are an average of five specimens. Toughness of selected alloys was evaluated using the un-notched Charpy Impact test, ASTM E23-07a. The specimen size was 10 mm10 mm55 mm machined from the tensile-bar casting. Two specimens were measured for each alloy.

(56) Smooth S-N fatigue test was conducted according to the ASTM E606 method. Three stress levels, 100 MPa, 150 MPa, and 200 MPa were evaluated. The R ratio was 1 and the frequency was 30 Hz. Three replicated specimens were tested for each condition. Test was terminated after about 10.sup.7 cycles. Smooth fatigue round specimens were obtained by slightly machining the gauge portion of the tensile bar casting.

(57) Corrosion resistance (type-of-attack) of selected conditions was evaluated according to the ASTM G110 method. Corrosion mode and depth-of-attack on both the as-cast surface and machined surface were assessed.

(58) All the raw test data including tensile, Charpy impact and S-N fatigue are given in Tables 7 to 9. A summary of the findings is given in the following sections.

(59) TABLE-US-00005 TABLE 7 Mechanical properties of various alloys aged at 155 C. for different times* Aged at Aged at 155 C. for 15 hrs 155 C. for 30 hrs UTS TYS E Q UTS TYS E Q Alloy (MPa) (MPa) (%) (MPa) (MPa) (MPa) (%) (MPa) 1. Al9Si0.5Mg 405.8 323.3 8.3 543.2 398.5 326.5 6.5 520.4 2. Al9Si0.35Mg0.75Cu4Zn 431.5 342.0 5.5 542.6 433.5 358.0 4.5 531.5 3. Al9Si0.45Mg0.75Cu4Zn 460.5 370.5 5.5 571.6 469.0 378.5 7.0 595.8 4. Al9Si0.45Mg0.75Cu 451.5 339.0 6.5 573.4 450.5 354.8 5.0 555.3 5. Al9Si0.5Mg0.75Cu 426.0 317.3 8.0 561.5 442.8 348.2 6.7 566.4 6. Al9Si0.35Mg1.25Cu 411.2 299.2 7.3 540.2 436.3 326.3 7.0 563.1 7. Al9Si0.45Mg1.25Cu 424.3 328.0 4.8 525.8 453.8 353.0 5.8 567.7 8. Al9Si0.55Mg1.25Cu 444.8 336.5 6.0 561.6 460.3 365.3 4.8 561.8 9. Al9Si0.35Mg1.75Cu 465.7 325.0 9.0 608.8 459.5 355.3 5.5 570.6 10. Al9Si0.35Mg1.75Cu0.5Ag 463.3 343.0 7.5 594.5 471.7 364.5 6.3 591.9 Aged at 155 C. for 60 hrs Alloy UTS (MPa) TYS (MPa) E (%) Q (MPa) 1. Al9Si0.5Mg 398.7 340.2 5.3 507.7 2. Al9Si0.35Mg0.75Cu4Zn 446.8 366.0 6.5 568.7 3. Al9Si0.45Mg0.75Cu4Zn 465.3 390.7 5.0 570.2 4. Al9Si0.45Mg0.75Cu 464.0 373.5 6.5 585.9 5. Al9Si0.5Mg0.75Cu 442.5 364.5 6.0 559.2 6. Al9Si0.35Mg1.25Cu 446.5 342.8 6.5 568.4 7. Al9Si0.45Mg1.25Cu 455.3 375.8 4.0 545.6 8. Al9Si0.55Mg1.25Cu 475.8 385.0 4.8 577.3 9. Al9Si0.35Mg1.75Cu 478.8 386.3 5.0 583.6 10. Al9Si0.35Mg1.75Cu0.5Ag 471.0 389.3 4.5 569.0 *Averaged value from five tensile specimens. The Quality Index, Q = UTS + 150 log(E).

(60) TABLE-US-00006 TABLE 8 Charpy impact test results for some selected alloys Energy (ft-lbs) 155 C./15 hrs 155 C./60 hrs Speci- Speci- Speci- Speci- Alloy men 1 men 3 men 7 men 9 1. Al9Si0.5Mg 6 27 23 27 3. Al9Si0.45Mg0.75Cu4Zn 17 18 10 12 4. Al9Si0.45Mg0.75Cu 32 15 28 13 7. Al9Si0.45Mg1.25Cu 27 12 7 12 9. Al9Si0.35Mg1.75Cu 16 15 8 9

(61) TABLE-US-00007 TABLE 9 S-N fatigue results for some selected alloys aged at 155 C. for 60 hours ( Smooth, Axial; stress ratio = 1) Cycles to Failure Stress 155 C./ 155 C./ Alloy (MPa) 15 hrs 60 hrs 1. Al9Si0.5Mg 100 1680725 1231620 1. Al9Si0.5Mg 100 1302419 272832 1. Al9Si0.5Mg 100 4321029 1077933 1. Al9Si0.5Mg 150 71926 148254 1. Al9Si0.5Mg 150 242833 42791 1. Al9Si0.5Mg 150 153073 56603 1. Al9Si0.5Mg 200 16003 54623 1. Al9Si0.5Mg 200 8654 30708 1. Al9Si0.5Mg 200 36597 39376 3. Al9Si0.45Mg0.75Cu4Zn 100 160572 248032 3. Al9Si0.45Mg0.75Cu4Zn 100 298962 131397 3. Al9Si0.45Mg0.75Cu4Zn 100 120309 394167 3. Al9Si0.45Mg0.75Cu4Zn 150 120212 12183 3. Al9Si0.45Mg0.75Cu4Zn 150 70152 42074 3. Al9Si0.45Mg0.75Cu4Zn 150 190200 31334 3. Al9Si0.45Mg0.75Cu4Zn 200 38369 18744 3. Al9Si0.45Mg0.75Cu4Zn 200 29686 14822 3. Al9Si0.45Mg0.75Cu4Zn 200 39366 11676 4. Al9Si0.45Mg0.75Cu 100 485035 575446 4. Al9Si0.45Mg0.75Cu 100 4521553 233110 4. Al9Si0.45Mg0.75Cu 100 3287495 940229 4. Al9Si0.45Mg0.75Cu 150 170004 141654 4. Al9Si0.45Mg0.75Cu 150 110500 234640 4. Al9Si0.45Mg0.75Cu 150 688783 238478 4. Al9Si0.45Mg0.75Cu 200 108488 22686 4. Al9Si0.45Mg0.75Cu 200 40007 36390 4. Al9Si0.45Mg0.75Cu 200 51678 20726 7. Al9Si0.45Mg1.25Cu 100 1115772 1650686 7. Al9Si0.45Mg1.25Cu 100 318949 1744140 7. Al9Si0.45Mg1.25Cu 100 468848 484262 7. Al9Si0.45Mg1.25Cu 150 102341 232171 7. Al9Si0.45Mg1.25Cu 150 145766 106741 7. Al9Si0.45Mg1.25Cu 150 63720 226188 7. Al9Si0.45Mg1.25Cu 200 41686 21873 7. Al9Si0.45Mg1.25Cu 200 20709 58819 7. Al9Si0.45Mg1.25Cu 200 52709 4367 9. Al9Si0.35Mg1.75Cu 100 2159782 2288145 9. Al9Si0.35Mg1.75Cu 100 354677 1011473 9. Al9Si0.35Mg1.75Cu 100 4258369 783758 9. Al9Si0.35Mg1.75Cu 150 281867 164554 9. Al9Si0.35Mg1.75Cu 150 135810 188389 9. Al9Si0.35Mg1.75Cu 150 100053 146740 9. Al9Si0.35Mg1.75Cu 200 24014 48506 9. Al9Si0.35Mg1.75Cu 200 30695 8161 9. Al9Si0.35Mg1.75Cu 200 62211 31032
1.4.2 Mechanical Properties at Room Temperature
1.4.2.1 Effect of Aging Temperature on Tensile Properties

(62) The effect of artificial aging temperature on tensile properties was investigated using the baseline alloy 1-Al-9% Si-0.5% Mg. After a minimum 4 hours of natural aging, the tensile bar castings were aged at 155 C. for 15, 30, 60 hours and at 170 C. for 8, 16, 24 hours. Three replicate specimens were used for each aging condition.

(63) FIG. 10 shows the tensile properties of the baseline A359 alloy (Al-9% Si-0.5% Mg) at various aging conditions. Low aging temperature (155 C.) tends to yield higher quality index than the high aging temperature (170 C.). Thus, the low aging temperature at 155 C. was selected, even though the aging time is longer to obtain improved properties.

(64) 1.4.2.2 Effects of Alloy Elements on Tensile Properties

(65) FIG. 11 compares the tensile properties of baseline Al-9% Si-0.5% Mg alloy and Al-9% Si-0.5% Mg-0.75% Cu alloy. The addition of 0.75% Cu to Al-9% Si-0.5% Mg alloy increases the yield strength by 20 MPa and ultimate tensile strength by 40 MPa while maintaining the elongation. The average quality index of the Cu-containing alloy is 560 MPa, which is much higher than the baseline alloy with an average of 520 MPa.

(66) FIG. 12 compares the tensile properties of four cast alloys, 1, 2, 3 and 4. Alloy 1 is the baseline alloy. Alloy 2-4 all contain 0.75% Cu with various amounts of Mg and/or Zn. Alloys 3 and 4 contain 0.45% Mg, while alloy 2 contains 0.35% Mg and alloy 1 contains 0.5% Mg. Alloys 2 and 3 also have 4% Zn. A preliminary assessment of these four alloys indicates that Mg and Zn increase alloy strength without sacrificing ductility. A direct comparison between alloys 3 and 4 indicates that by adding 4% Zn to the Al-9% Si-0.45% Mg-0.75% Cu alloy, both ultimate tensile strength and yield strength are increased while maintaining the elongation. The 4% Zn addition also increases the aging kinetics as indicated in FIG. 12. When aged at 155 C. for 15 hours, yield strength of about 370 MPa can be achieved for the Al-9% Si-0.45% Mg-0.75% Cu-4% Zn alloy, which is about 30 MPa higher than that of the alloy without Zn.

(67) FIG. 13 shows the effect of Mg content (0.35-0.55 wt %) on the tensile properties of the Al-9% Si-1.25% CuMg alloys (Alloys 6-8). The tensile properties of the baseline alloy Al-9% Si-0.5% Mg are also included for comparison. Mg content showed significant influence on the tensile properties. With increasing Mg content, both yield strength and tensile strength were increased, but the elongation was decreased. The decrease of elongation with increasing Mg content could be related to higher amount of -AlFeMgSi phase particles even if all the Q-AlCuMgSi phase particles were dissolved. The impact of Mg content on quality indexes of the Al-9% Si-1.25% CuMg alloys was overall found to be insignificant.

(68) FIG. 14 shows the effect of Ag (0.5 wt %) on the tensile properties of Al-9% Si-0.35% Mg-1.75% Cu alloy. An addition of 0.5 wt % Ag had very limited impact on strength, elongation and quality index of the Al-9% Si-0.35% Mg-1.75% Cu alloy. It should be noted that the quality index of the Al-9% Si-0.35% Mg-1.75% Cu (without Ag) alloy is 60 MPa higher than the baseline alloy, A359 (Alloy 1).

(69) FIGS. 15a-15d show the tensile properties of five promising alloys in accordance with the present disclosure along with the baseline alloy Al-9Si-0.5 Mg (alloy 1). These five alloys achieve the target tensile properties, i.e., 10-15% increase in tensile and maintaining similar elongation as A356/A357 alloy. The alloys are: Al-9% Si-0.45% Mg-0.75% Cu (Alloy 4), Al-9% Si-0.45% Mg-0.75% Cu-4% Zn (Alloy 3), Al-9% Si-0.45% Mg-1.25% Cu (Alloy 7), Al-9% Si-0.35% Mg-1.75% Cu (Alloy 9), and Al-9% Si-0.35% Mg-1.75% Cu-0.5% Ag (Alloy 10).

(70) Based on the data, it is believed that the following tensile properties can be obtained with alloys aged at 155 C. for time ranged from 15 to 60 hrs.

(71) TABLE-US-00008 Ultimate tensile strength: 450-470 MPa Tensile yield strength: 360-390 MPa Elongation: 5-7% Quality index: 560-590 MPa

(72) These properties are much higher than A359 (Alloy 1) and are very similar to A201 (Al4.6Cu0.35Mg0.7Ag) cast alloy (UTS 450 MPa, TYS 380 MPa, Elongation 8%, and Q 585 MPa) ASM Handbook Volume 15, Casting, ASM International, December 2008. On the other hand, the castability of these Al-9% SiMgCu alloys is much better than A201 alloy. The A201 alloy has a poor castability due to its high tendency of hot cracking and Cu macro-segregation. Additionally, the material cost of A201 with 0.7 wt % Ag is also much higher than those embodiments in accordance with the present disclosure that are Ag-free.

(73) Based on the tensile property results, four alloys without Ag (Alloys 3, 4, 7 and 9) with promising tensile properties along with baseline alloy, A359 (Alloy 1) were selected for further investigation. Charpy impact, S-N fatigue and general corrosion tests were conducted on these five alloys aged at 155 C. for 15 hours and 60 hours.

(74) 1.4.4 Charpy Impact Tests

(75) FIG. 16 shows the results of the individual tests by plotting Charpy impact energy vs. tensile yield strength. The filled symbols are for specimens aged at 155 C. for 15 hours and open symbols are for specimens aged at 155 C. for 60 hours. Tensile yield strength increases as the aging time increases, while the Charpy impact energy decreases with increasing aging time. The results indicate that most alloys/aging conditions follow the expected strength/toughness relationship. However, the results indeed show a slight degradation of the strength/toughness relationship with higher Cu content such as 1.25 and 1.75 wt %.

(76) 1.4.5 S-N Fatigue Tests

(77) Aluminum castings are often used in engineered components subject to cycles of applied stress. Over their commercial lifetime millions of stress cycles can occur, so it is important to characterize their fatigue life. This is especially true for safety critical applications, such as automotive suspension components.

(78) FIGS. 17 and 18 show the S-N fatigue test results of five selected alloys aged at 155 C. for 15 and 60 hours, respectively. During these tests a constant amplitude stress (R=1) was applied to the test specimens. Three different stress levels, 100 MPa, 150 MPa and 200 MPa were applied. The total number of cycles to failure was recorded.

(79) When aged at 155 C. for 15 hours, all the Cu-containing alloys showed better fatigue performance (higher number of cycles to failure) than the baseline A359 alloy at higher stress levels (>150 MPa). At lower stress levels (<125 MPa), the fatigue lives of the Al-9Si-0.45Mg-0.75Cu and Al-9Si-0.35Mg-1.75Cu alloys are very similar to the A359 alloy, while the fatigue life of the Al-9Si-0.45Cu-0.75Cu-4Zn alloy (alloy 3) was lower than the A359 alloy. The lower fatigue life of this alloy could result from the higher hydrogen content of the casting, as stated previously.

(80) Increasing aging time (higher tensile strength) tended to decrease the number of cycles to failure. For example, as the aging time increased from 15 hours to 60 hours, the average number of cycles to failure at 150 MPa stress level decreased from 323,000 to 205,000 for the Al-9% Si-0.45% Mg-0.75% Cu alloy and from 155,900 to 82,500 for the A359 alloy. The result could be a general trend of the strength/fatigue relationship of AlSiMg(Cu) casting alloys. Again, alloy 3 showed a lower fatigue performance than others.

(81) 1.4.6 Corrosion TestsASTM G110

(82) FIGS. 19 to 23 show optical micrographs of the cross-sectional views after 6-hour ASTM G110 tests for five selected alloys of both the as-cast surfaces and machined surfaces. The mode of corrosion attack was predominantly interdendritic corrosion. The number of corrosion sites was generally higher in the four Cu-containing compositions than in the Cu-free baseline alloy.

(83) More particularly, FIGS. 19a-d show optical micrographs of cross-sections of Al-9% Si-0.5% Mg after a 6-hour ASTM G110 test: a) of the alloy as cast and aged 15 hours at 155 C.; b) of the alloy as cast and aged 60 hours at 155 C.; c) of the alloy with a machined surface and aged 15 hours at 155 C.; and d) of the alloy with a machined surface and aged 60 hours at 155 C.

(84) FIGS. 20a-d show optical micrographs of cross-sections of Al-9% Si-0.35% Mg-0.75% Cu-4% Zn after a 6-hour ASTM G110 test: a) of the alloy as cast and aged 15 hours at 155 C.; b) of the alloy as cast and aged 60 hours at 155 C.; c) of the alloy with a machined surface and aged 15 hours at 155 C.; and d) of the alloy with a machined surface and aged 60 hours at 155 C.

(85) FIGS. 21a-d show optical micrographs of cross-sections of Al-9% Si-0.45% Mg-0.75% Cu after a 6-hour ASTM G110 test: a) of the alloy as cast and aged 15 hours at 155 C.; b) of the alloy as cast and aged 60 hours at 155 C.; c) of the alloy with a machined surface and aged 15 hours at 155 C.; and d) of the alloy with a machined surface and aged 60 hours at 155 C.

(86) FIGS. 22a-d show optical micrographs of cross-sections of Al-9% Si-0.45% Mg-1.25% Cu after a 6-hour ASTM G110 test: a) of the alloy as cast and aged 15 hours at 155 C.; b) of the alloy as cast and aged 60 hours at 155 C.; c) of the alloy with a machined surface and aged 15 hours at 155 C.; and d) of the alloy with a machined surface and aged 60 hours at 155 C.

(87) FIGS. 23a-d show optical micrographs of cross-sections of Al-9% Si-0.35% Mg-1.75% Cu after a 6-hour ASTM G110 test: a) of the alloy as cast and aged 15 hours at 155 C.; b) of the alloy as cast and aged 60 hours at 155 C.; c) of the alloy with a machined surface and aged 15 hours at 155 C.; and d) of the alloy with a machined surface and aged 60 hours at 155 C.

(88) FIG. 24 shows the depth of attack after the 6-hour ASTM G110 test. There is no clear difference or trend among the alloys. Aging time did not show obvious impact on the depth of attack either, while some differences were found between the as-cast surfaces and the machined surfaces. In general, the corrosion attack was slightly deeper on the machined surface than the as-cast surface of the same sample.

(89) Overall, the additions of Cu or Cu+Zn do not change the corrosion mode nor increase the depth-of-attack of the alloys. It is believed that all the alloys evaluated have similar corrosion resistance as the baseline alloy, A359.

(90) The present disclosure has described AlSiCuMg alloys that can achieve high strength without sacrificing ductility. Tensile properties including 450-470 MPa ultimate tensile strength, 360-390 MPa yield strength, 5-7% elongation, and 560-590 MPa Quality Index were obtained. These properties exceed conventional 3xx alloys and are very similar to that of the A201 (2xx+Ag) Alloy, while the castabilities of the new Al-9SiMgCu alloys are much better than that of the A201 alloy. The new alloys showed better S-N fatigue resistance than A359 (Al-9Si-0.5 Mg) alloys. Alloys in accordance with the present disclosure have adequate fracture toughness and general corrosion resistance.

EXAMPLE 2

Cast Alloys for Applications at Elevated Temperatures

(91) Because alloys such as those described in the present disclosure may be utilized in applications wherein they are exposed to high temperatures, such as in engines in the form of engine blocks, cylinder heads, pistons, etc., it is of interest to assess how such alloys behave when exposed to high temperatures. FIG. 26 shows a graph of tensile properties of an alloy in accordance with the present disclosure, namely, Al-9Si-0.35Mg-1.75Cu (previously referred to as alloy 9, e.g., in FIG. 15) after exposure to various temperatures. As noted, for each test generating data in the graph, the exposure time of the alloys was 500 hours at the indicated temperature. The samples were also tested at the temperature indicated. As shown in the graph, the yield strength of the alloy diminished significantly at temperatures above 150 C. In accordance with the present disclosure, the metal was analyzed to ascertain features associated with the loss in strength due to exposure to increased temperatures.

(92) FIGS. 27a and 27b show scanning electron microscope (SEM) micrographs of a cross-section of a sample of alloy 9 prior to exposure to high temperatures, with 27b being an enlarged view of the portion of the micrograph of 31a indicated as Al. As shown in FIG. 27a, the grain boundaries are visible, as well as, Si and AlFeSi particles. The predominately Al portion shown in FIG. 27b shows no visible precipitate at 20,000 magnification.

(93) FIGS. 28a-e show a series of scanning electron microscope (SEM) micrographs of a cross-section of alloy C00 (previously referred to as alloy 9, e.g., in FIG. 15) of the same scale as the micrograph shown in FIG. 27b after exposure to increasing temperatures as shown by the correlation of the micrographs to the data points on the tensile property graph G of alloy 9. The tensile characteristics of A356 alloy in the given temperature range are also shown in graph G for comparison. As can be appreciated from the sequence of micrographs, exposure of alloy 9 to increasing temperatures results in continuously increasing prominence of precipitate particles, which are larger, and which exhibit divergent geometries.

(94) The inventors of the present disclosure recognized that certain alloying elements, viz., Ti, V, Zr, Mn, Ni, Hf, and Fe could be introduced to the C00 alloy (previously referred to as alloy 9, e.g., in FIG. 15) of the present disclosure in small amounts to produce an alloy that resists strength degradation at elevated temperatures.

(95) The following table (Table 10) show 18 alloys utilizing additive elements in small quantities to the C00 alloy (previously referred to as alloy 9, e.g., in FIG. 15) for the purpose of developing improved strength at elevated temperatures.

(96) TABLE-US-00009 TABLE 10 Alloy Compositions (all values in weight percent) Alloy Fe Si Mn Cu Mg Sr Ti B V Zr Ni Hf C00 0.08 9.29 0 1.83 0.37 0.0125 0.05 0 0 0 0 C01 0.15 9.3 0.002 1.82 0.002 0.008 0.11 0.0047 0.012 0.002 0 0 C02 0.15 9.35 0.002 1.82 0.39 0.008 0.11 0.0043 0.012 0.002 0 0 C03 0.15 9.05 0.002 1.77 0.37 0.007 0.11 0.0051 0.13 0.002 0 0 C04 0.16 8.95 0.002 1.77 0.36 0.006 0.1 0.0026 0.1 0.091 0 0 C05 0.16 8.86 0.002 1.76 0.36 0.005 0.1 0.0016 0.13 0.15 0 0 C06 0.16 8.54 0.002 1.72 0.35 0.004 0.1 0.005 0.13 0.18 0 0 C07 0.16 9.31 0.15 1.8 0.34 0.004 0.11 0.0044 0.025 0.016 0 0 C08 0.16 9.32 0.16 1.84 0.34 0.004 0.11 0.0051 0.025 0.017 0 0 C09 0.17 9.1 0.28 1.8 0.33 0.003 0.11 0.005 0.025 0.016 0 0 C10 0.32 9.26 0.3 1.83 0.34 0.003 0.11 0.0045 0.024 0.017 0 0 C11 0.49 8.96 0.3 1.78 0.32 0.003 0.12 0.0055 0.11 0.016 0 0 C12 0.56 8.97 0.3 1.79 0.32 0.002 0.1 0.0039 0.11 0.12 0 0 C13 0.15 9.28 0.003 1.82 0.33 0.0125 0.1 0.005 0.001 0.002 0.28 0 C14 0.2 9.28 0.004 1.81 0.33 0.004 0.1 0.0026 0.012 0.002 0.28 0 C15 0.31 9.27 0.03 1.82 0.33 0.004 0.1 0.0032 0.012 0.002 0.28 0 C16 0.32 9.14 0.1 1.79 0.32 0.003 0.1 0.0032 0.012 0.003 0.27 0.1 C17 0.32 8.88 0.12 1.75 0.3 0.003 0.1 0.0031 0.11 0.013 0.26 0.1 C18 0.32 8.89 0.14 1.76 0.3 0.003 0.1 0.003 0.11 0.036 0.27 0.1

(97) Table 11 shows the mechanical properties of the foregoing alloys, viz., ultimate tensile strength (UTS), total yield strength (TYS) and Elongation % at 300 C., 175 C. and room temperature (RT).

(98) TABLE-US-00010 TABLE 11 Mechanical Properties at Various Temperatures 300 C. Alloy UTS (ksi) TYS (ksi) Elong. (%) C00 8.2 8.4 8.3 6 6.3 6 49 54 29.5 C01 9.3 9.5 9.6 6.5 6.4 6.7 63 54.5 49.5 C02 10 10.3 9 6.9 7.2 6.5 51.5 40.5 40.5 C03 8.8 10.2 10.6 6.8 7.2 7.5 52 43.5 56.5 C04 10.4 10.3 11.7 7.9 7.4 8 47.5 47 41.5 C05 10.8 10.7 11.1 8.5 8 8.2 47 41.5 36.5 C06 11 9.3 11.2 7.7 7.1 8.5 35 36 42.5 C07 10.5 10.6 10.3 8.1 8 7.7 53 40 43.5 C08 10 9.7 10.6 7.5 6.7 7.9 39 40.5 36.5 C09 10.3 10.8 11.7 7.5 7.8 8.6 35 35 36 C10 10.7 10.7 11.3 8.1 8 8.3 37 40 33 C11 11 11.3 10.5 7.9 8.1 7.7 27.5 30.5 34.5 C12 11.7 10.8 11.4 8.2 7.9 8.2 33 28.5 34.5 C13 10.2 9 9.4 7.5 6.9 7 45.5 53 40 C14 9.3 9.2 9.9 6.6 6.6 6.9 56 44 42.5 C15 10 9.8 10 7.2 7.2 7.2 46.5 32 31.5 C16 10.3 10.3 10.1 7.7 7.5 7.5 44.5 36.5 34.5 C17 10.5 9.4 10 7.5 7.2 7.2 46.5 42.5 29.5 C18 10.1 11.4 11.3 7.5 8.6 8.2 29 28.5 25.5 175 C. Alloy UTS (ksi) TYS (ksi) Elongation (%) C00 34.8 33.7 37.1 28.8 27.8 31 8.5 10.5 10.5 C01 28.1 31 29.4 21.4 23.7 21.8 16.6 24 14.9 C02 43.6 46.2 46.1 38 39.6 40.2 6.9 5.1 5.1 C03 44.9 43.1 45.4 40.6 37.4 39.8 0.6 7.4 4 C04 46.5 46.5 48.3 40.6 41 42.8 6.9 9.1 4.6 C05 40 47.4 47 35.4 40.7 39.9 2.9 5.1 5.1 C06 44.3 43.6 46.6 38.4 37.4 40.9 5.7 8 3.4 C07 48.3 46.7 43 41.6 40.8 38 6.3 2.3 6.9 C08 49.3 41.8 42.6 41.2 36.5 36.6 6.3 2.3 6.9 C09 39 45.2 43.9 33.7 39.2 38.6 3.4 3.4 2.3 C10 35.7 43.6 48.6 30.9 37.3 41.9 2.3 3.4 2.3 C11 42.4 42.5 47.6 36.5 35.8 41.1 1.1 2.3 2.3 C12 37.9 37.3 37.3 35.3 31.7 31.2 1.1 1.7 4 C13 45.3 45.2 41.3 39.2 38.2 35 2.9 6.3 8 C14 34.3 38.6 45.7 32.3 32.4 39 0.6 9.1 5.1 C15 40.1 45.2 44.7 34.2 38.5 37.6 2.9 5.1 3.4 C16 42.3 41.6 41.7 35.4 35.2 35.9 4 5.1 2.3 C17 42.6 38.4 39.5 21.8 38 34.2 14.9 6.9 2.3 C18 37.2 41.4 41.5 35.1 34.6 34.7 1.1 5.1 3.4 Room Temperature Alloy UTS (ksi) TYS (ksi) Elongation (%) C00 58.4 56.5 47.7 52.4 4 4 58.4 56.5 47.7 C01 37.7 38.4 20.1 20.9 9 12 37.7 38.4 20.1 C02 60.2 56.7 46.2 3 3 60.2 56.7 C03 50.5 59.8 48.7 50.3 3 5.5 50.5 59.8 48.7 C04 58.7 57.5 49.7 48.1 3 1 58.7 57.5 49.7 C05 52.4 58.2 51.1 47.7 1 3 52.4 58.2 51.1 C06 57.9 59.1 48.2 48.8 3 4 57.9 59.1 48.2 C07 57 58.3 48.1 3.5 3.5 57 58.3 48.1 C08 58.6 52 46.2 48.2 3.5 3 58.6 52 46.2 C09 52 58.1 47.9 48.5 3 3 52 58.1 47.9 C10 55 55.6 47.7 49.6 3 3 55 55.6 47.7 C11 54.1 52.6 49.3 49.1 3 3 54.1 52.6 49.3 C12 50.2 52.7 48.5 50.6 1 1.5 50.2 52.7 48.5 C13 56.3 58.5 48.1 45.9 2.5 8 56.3 58.5 48.1 C14 61.3 57.1 44.3 44.5 8 4 61.3 57.1 44.3 C15 56.7 55.8 45.9 47.1 4 4 56.7 55.8 45.9 C16 57.4 53.7 46.4 46 4 3 57.4 53.7 46.4 C17 57.2 56.1 47.1 46.9 3 3 57.2 56.1 47.1 C18 48.5 50.6 45.1 46.9 2 2 48.5 50.6 45.1

(99) FIG. 29 shows a graph of yield strength at room temperature for foregoing alloys. A356 is shown for comparison. In addition, a department of energy (DOE) published target for strength improvement is shown for comparison [Predictive Modeling for Automotive Light weighting Applications and Advanced Alloy Development for Automotive and Heavy-Duty Engines, Issue by Department of Energy on Mar. 3, 2012]. As can be appreciated, the C00 alloy is comparable in strength at room temperature to alloys C02-C18, all of which substantially exceed the strength of the A356 alloy and the DOE target properties. Alloy C01-without substantial quantities of Mg, has a far lower yield strength.

(100) FIG. 30 is a graph of yield strength after exposure to 175 C. for 500 hours for the foregoing alloys. The C00, as well as A356 are shown for comparison. As can be appreciated, the C00 alloy substantially exceeds the strength of the A356 alloy. Alloys C02-C18), all show marked improvement over both A356 and C00.

(101) FIG. 31 is a graph of yield strength after exposure to 300 C. for 500 hours for the foregoing alloys. C00, as well as A356 are shown for comparison. FIG. 32 shows is a graph of yield strength after exposure to 300 C. for various alloys. More particularly, adjacent alloys (going in the direction of the arrows) show the result of an additional element or the increase in quantity of an element. The highest result in the graph of FIG. 32 is for C00+0.1T+0.16Fe+0.13V+0.15Zr. The addition of more Zr (to 0.18%) to this combination results in decreased performance.

(102) FIG. 33 is a graph of yield strength after exposure to 300 C. for various alloys for 500 hours. The graphs show improvements due to the addition of Ti, Fe and Mn to the C00 composition, with the maximum performance noted relative to C00+0.11Ti+0.32Fe+0.3Mn. The addition of V to the foregoing reduces performance and the further addition of 0.12 Zr brings performance almost back to the maximum level.

(103) FIG. 34 is a graph of yield strength after exposure to 300 C. for various alloys, i.e., due to the addition of elements to the C00 composition. The optimal performance is noted relative to C00+0.1Ti+0.28Ni+0.32 Fe+0.14Mn+0.1Hf+0.11V+0.04Zr.

EXAMPLE 3

Cast Alloys for Semi-Permanent Mold Cylinder Head Applications

(104) High strength at elevated temperature and very good castability make the C05 alloy (TABLE 10) an excellent candidate for cylinder head applications, e.g., for internal combustion engines. Plant-scale trials for the C05 alloy (TABLE 10) were conducted. Cylinder head castings were made using a gravity semi-permanent mold casting process. The actual compositions are listed in Table 12.

(105) TABLE-US-00011 TABLE 12 Actual Composition of Example 3 Alloys Alloy Si Fe Cu Mn Mg Ti V Zr Sr B D1 8.97 0.12 1.91 0.13 0.38 0.11 0.085 0.085 0.01 0 D2 9.14 0.14 1.98 0.14 0.37 0.11 0.094 0.1 0.011 0.0011

(106) Tensile specimen blocks were cut from the combustion chamber area. They were solution heat treated using following practice:
2-hr log to 940 F. (504.4 C.)+940 F.(504.4 C.)/2 hrs+30 minutes ramp up to 986 F.(530 C.)+986 F.(530 C.)/4 hrs+CWQ

(107) Three artificial aging practices, 190 C./6 hrs, 205 C./6 hrs and 220 C./6 hrs, were evaluated and the mechanical property results are shown in Table 13.

(108) TABLE-US-00012 TABLE 13 Mechanical Properties of Example 3 Alloys Artificial Aging Tensile Yield Ultimate Tensile Elongation Condition Strength (MPa) Strength (MPa) (%) 190 C./6 hrs 332 386 2 190 C./6 hrs 336 387 2 205 C./6 hrs 320 362 2 205 C./6 hrs 326 369 3 220 C./6 hrs 273 322 2 220 C./6 hrs 281 335 3
The foregoing alloy compositions may also be used to form cylinder heads by high pressure die casting (HPDC) methods and using T5 tempering procedures.

EXAMPLE 4

Cast Alloys for HPDC Engine Block Applications

(109) In accordance with another embodiment of the present disclosure, the disclosed aluminum alloys may be used to cast cylinder blocks, e.g., for internal combustion engines. Since the engine block is the main contributor to engine mass, use of the disclosed alloys for the engine block may result in significant weight reduction, e.g., up to 45% weight reduction for gasoline engines, compared to engines made from cast-iron. Engines having lower mass translate into improved performance, better fuel economy and reduced emissions. For mass engine production, high-pressure die-casting (HPDC) process is widely used for high production rates and reduced production costs.

(110) HPDC engine block casting methods frequently employ T5 temper practices. The alloys of the present disclosure may be tempered using T5 practices. Note that this approach does not employ a high-temperature solution heat treatment and quench. In accordance with an embodiment of the present disclosure, six alloys having the compositions shown in Table 14 were prepared, cast into a modified ASTM tensile bar mold.

(111) TABLE-US-00013 TABLE 14 Actual Composition of Example 4 Alloys (weight percent) Alloy Si Cu Mg Fe Mn Ti V Zr Sr B R1 9.32 0.55 0.22 0.13 0.48 0.13 0.13 0.14 0.012 0.002 R2 9.25 0.54 0.42 0.13 0.52 0.13 0.13 0.14 0.012 0.002 R3 9.24 1.02 0.21 0.16 0.53 0.13 0.12 0.10 0.012 0.002 R4 9.41 1.02 0.41 0.17 0.53 0.14 0.12 0.10 0.012 0.002 R5 9.14 1.53 0.22 0.16 0.53 0.11 0.12 0.12 0.012 0.002 R6 9.27 1.52 0.43 0.16 0.53 0.12 0.12 0.12 0.012 0.002 The weight ratio of Fe:Mn for all alloys was from 0.25 to 0.32.

(112) Sixty (60) tensile bar specimens were made for each composition. After the specimens were completely solidified, half were water quenched, and the other half were air cooled. The physical attributes of the resultant specimens were then tested and are also described below. Three different artificial aging practices, 175 C./6 hrs, 190 C./6 hrs and 205 C./6 hrs, were evaluated for both water quenched and air-cooled specimens.

(113) Tables 15, 16 and 17 list average yield strength, ultimate tensile strength and elongation, respectively, for air-cooled specimens aged at different conditions. Table 15 shows the effect of Cu, Mg and aging condition on yield strength of the Al-9Si-0.15Fe-0.55MnCuMg alloys. After being completely solidified, the tensile bar castings were cooled in the air. As shown in Table 15, Mg and Cu content showed significant impact on yield strength. Alloys with 0.4% Mg and 1.0-1.5% Cu showed higher yield strength than other alloys.

(114) Table 16 shows the effect of Cu, Mg and aging condition on ultimate tensile strength of the Al-9Si-0.15Fe-0.55MnCuMg alloys. After being completely solidified, tensile bar castings were cooled in the air. Table 16 shows the effect of Cu, Mg and aging condition on elongation of the Al-9Si-0.15Fe-0.55MnCuMg alloys. After being completely solidified, tensile bar castings were cooled in the air. As shown in Tables 16-17, increasing Mg and Cu will slightly increase UTS, and decrease elongation. For air cooled specimens, the highest achieved yield strength in the T5 condition was about 190 MPa.

(115) TABLE-US-00014 TABLE 15 Yield Strength for R1-R6 Alloys (Air Cool) at Various Artificial Aging Conditions Average Tensile Yield Strength Standard Deviation 190 C./ 205 C./ 190 C./ 205 C./ Alloy 175 C./6 hrs 6 hrs 6 hrs 175 C./6 hrs 6 hrs 6 hrs R1 150 178 172 6.2 9.0 23.4 R3 142 150 149 1.4 3.4 1.4 R5 174 198 179 4.1 4.8 12.4 R2 179 167 185 2.1 13.1 2.1 R4 188 197 194 0.7 2.1 6.9 R6 200 194 195 9.6 6.9 8.3

(116) TABLE-US-00015 TABLE 16 Tensile Strength for R1-R6 Alloys (Air Cool) at Various Artificial Aging Conditions Average Ultimate Tensile Strength Standard Deviation 190 C./ 205 C./ 190 C./ 205 C./ Alloy 175 C./6 hrs 6 hrs 6 hrs 175 C./6 hrs 6 hrs 6 hrs R1 223 248 269 14.5 22.7 22.0 R3 241 240 234 2.1 7.6 17.2 R5 263 251 229 3.4 19.3 33.8 R2 251 249 243 9.0 26.2 4.8 R4 243 234 249 26.2 19.3 9.6 R6 243 269 237 17.9 11.0 29.6

(117) TABLE-US-00016 TABLE 17 Elongation for R1-R6 Alloys (Air Cool) at Various Artificial Aging Conditions Average Elongation Standard Deviation 190 C./ 205 C./ 190 C./ 205 C./ Alloy 175 C./6 hrs 6 hrs 6 hrs 175 C./6 hrs 6 hrs 6 hrs R1 2.50 2.17 3.50 0.50 0.76 1.32 R3 2.83 2.33 2.00 0.29 0.29 0.87 R5 2.50 1.67 1.17 0.00 0.29 0.29 R2 2.17 2.67 1.83 0.58 0.29 0.29 R4 1.83 1.33 1.67 0.58 0.29 0.29 R6 1.33 1.50 1.50 0.29 0.87 0.50

(118) Tables 18, 19 and 20 list average yield strength, ultimate tensile strength and elongation, respectively, for warm water quenched specimens aged at different conditions. Table 18 shows the effect of Cu, Mg and aging condition on yield strength of the Al-9Si-0.15Fe-0.55MnCuMg alloys. After being completely solidified, the tensile bar castings were cooled in warm water. As shown in Table 18, Mg and Cu content showed significant impact on yield strength. Table 19 shows the effect of Cu, Mg and aging condition on ultimate tensile strength of the Al-9Si-0.15Fe-0.55MnCuMg alloys. After being completely solidified, the tensile bar castings were cooled in warm water. Table 20 shows the effect of Cu, Mg and aging condition on elongation of the Al-9Si-0.15Fe-0.55MnCuMg alloys. After being completely solidified, the tensile bar castings were cooled in warm water.

(119) Alloys with 0.4% Mg and 1.0-1.5% Cu showed higher yield strength than other alloys. For warm water quenched specimens, the highest achieved yield strength in the T5 condition was about 260 MPa.

(120) TABLE-US-00017 TABLE 18 Yield Strength for R1-R6 Alloys (Water Cool) at Various Artificial Aging Conditions Average Tensile Yield Strength Standard Deviation 190 C./ 205 C./ 190 C./ 205 C./ Alloy 175 C./6 hrs 6 hrs 6 hrs 175 C./6 hrs 6 hrs 6 hrs R1 194 201 193 2.1 2.8 4.1 R3 195 205 180 16.5 10.3 7.6 R5 246 232 222 17.9 22.0 3.4 R2 227 234 232 6.2 11.7 7.6 R4 256 261 243 6.2 6.2 23.4 R6 239 267 251 5.5 6.9 15.8

(121) TABLE-US-00018 TABLE 19 Tensile Strength for R1-R6 Alloys (Water Cool) at Various Artificial Aging Conditions Average Ultimate Tensile Strength Standard Deviation 190 C./ 205 C./ 190 C./ 205 C./ Alloy 175 C./6 hrs 6 hrs 6 hrs 175 C./6 hrs 6 hrs 6 hrs R1 285 298 274 9.0 19.3 4.8 R3 268 283 235 30.3 18.6 46.9 R5 289 274 247 7.6 18.6 2.1 R2 294 278 278 11.0 28.9 9.6 R4 306 279 291 23.4 1.4 20.7 R6 293 293 291 23.4 4.1 17.2

(122) TABLE-US-00019 TABLE 20 Elongation for R1-R6 Alloys (Water Cool) at Various Artificial Aging Conditions Average Elongation Standard Deviation 190 C./ 205 C./ 190 C./ 205 C./ Alloy 175 C./6 hrs 6 hrs 6 hrs 175 C./6 hrs 6 hrs 6 hrs R1 2.7 3.7 3.0 0.8 1.4 0.5 R3 2.2 2.5 2.2 0.6 0.5 1.6 R5 1.7 1.3 1.3 0.3 0.6 0.6 R2 2.2 2.0 1.7 0.3 0.5 0.3 R4 1.7 0.8 1.5 0.6 0.3 0.0 R6 1.8 0.8 1.5 0.3 0.3 0.0

EXAMPLE 5

Cast Alloys for HPDC Engine Block Applications

(123) Additional high-pressure die-casting (HPDC) tests were completed on two alloys, the compositions of which are shown below in Table 21. The alloys were cast as journal pieces. After casting, various ones of the alloys were quenched in air, while other ones of the alloys were quenched in warm water (60 C.). Various ones of the alloys were aged at various times and temperatures, after which various mechanical properties were tested, the results of which are provided in Tables 22-24, below. Strength and elongation were tested using JIS14B test specimens taken from about 1 mm below the casting surface.

(124) TABLE-US-00020 TABLE 21 Actual Composition of Example 5 Alloys (weight percent) Alloy Si Cu Mg Fe Mn Ti V Zr Sr B R7 9.15 0.52 0.19 0.16 0.57 0.10 0.13 0.11 0.013 0.0018 R8 9.24 1.10 0.41 0.17 0.53 0.11 0.12 0.13 0.014 0.0017 The weight ratio of Fe:Mn for all alloys was from 0.28 to 0.32.

(125) TABLE-US-00021 TABLE 22 T5 properties of Alloys Aged at about 205 C. for about 6 hours (values averages of five specimens; standard deviation shown) Alloy Quench UTS (MPa) TYS (MPa) Elong. (%) R7 Air 248.8 9.2 136.9 11.1 5.6 1.3 R7 Water 278.6 4.0 177.9 1.2 4.4 0.7 R8 Air 249.1 10.3 140.9 15.7 3.8 0.5 R8 Water 295.7 4.1 210.5 1.5 2.7 0.2

(126) TABLE-US-00022 TABLE 23 T5 properties of Alloys Aged at about 205 C. for various times (values averages of five specimens; standard deviation shown; all water quenched) Alloy Aging Time UTS (MPa) TYS (MPa) Elong. (%) R8 2 hours 298.4 9.5 224.0 2.2 2.2 0.4 R8 4 hours 300.3 4.0 220.3 1.3 2.4 0.2 R8 6 hours 295.7 4.1 210.5 1.5 2.7 0.2

(127) TABLE-US-00023 TABLE 24 T5 fatigue Properties of Alloy R8 (water quenched and aged at about 205 C. for 6 hours) Sample Stress amplitude Number of cycles No. .sub.a (MPa) (Nf) Condition 1 110 1.00E+06 Fracture 2 90 1.00E+07 OK 3 93 1.00E+07 Fracture 4 93 3.998E+06 Fracture 5 95 1.82E+06 Fracture 6 120 3.596E+05 Fracture 7 110 7.37E+05 Fracture 8 100 2.206E+06 Fracture 9 90 1.00E+07 OK 10 100 2.915E+06 Fracture
The fatigue properties of alloy R8 were measured at room temperature, at a stress ratio of R=1 (=.sub.min/.sub.max) with a frequency of 1500 rpm, and with a mean stress (.sub.m) of zero (0) MPa. The fatigue was 90 MPa at room temperature.

(128) Fatigue strength (staircase fatigue) at about 150 C. was also measured for alloy R8 in one T5 temper, having been water quenched and artificially aged for about 6 hours at about 205 C. Alloy R8 in this type of T5 temper realized a mean fatigue strength of 81.257.83 MPa at 150 C. The stress amplitude increment was 5.0 MPa and the convergence factor was 0.94.

(129) It will be understood that the embodiments described herein are merely exemplary and that a person skilled in the art may make many variations and modifications without departing from the spirit and scope of the claimed subject matter. For example, use different aging conditions may produce different resultant characteristics. All such variations and modifications are intended to be included within the scope of the appended claims.