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.

Description

FIELD

The present invention relates to aluminum alloys, and more particularly, to aluminum alloys used for making cast products.

BACKGROUND

Aluminum alloys are widely used, e.g., in the automotive and aerospace industries, due to a high performance-to-weight ratio, favorable corrosion resistance and other factors. Various aluminum alloys have been proposed in the past that have characteristic combinations of properties in terms of weight, strength, castability, resistance to corrosion, and cost. AlSiMgCu casting alloys are described in commonly-owned U.S. Patent Application Publication No. 2013/0105045, entitled “High-Performance AlSiMgCu Casting Alloy”, published May 2, 2013.

SUMMARY

The disclosed subject matter relates to improved aluminum casting alloys (also known as foundry alloys) and methods for producing same. More specifically, the present application relates to new aluminum casting alloys having:

• • 8.5-9.5 wt. % silicon;
  • 0.5-2.0 wt. % copper (Cu);
    • wherein 2.5≤(Cu+10Mg)≤5.8;
  • 0.15-0.60 wt. % magnesium (Mg);
  • 0.35 to 0.8 wt. % manganese;
  • up to 5.0 wt. % zinc;
  • up to 1.0 wt. % silver;
  • up to 1.0 wt. % nickel;
  • up to 1.0 wt. % hafnium;
  • up to 1.0 wt. % iron;
  • up to 0.30 wt. % titanium;
  • up to 0.30 wt. % zirconium;
  • up to 0.30 wt. % vanadium;
  • up to 0.10 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.The new aluminum casting alloys may be utilized in a variety of applications, including engine applications (e.g., as a cylinder head, as a cylinder/engine block) and automotive applications (e.g., suspension and structural components, connecting rods), among others.I. Composition

As noted above, the new aluminum casting alloys generally include 8.5-9.5 wt. % Si. In one embodiment, the aluminum alloy includes 8.75-9.5 wt. % Si. In one embodiment, the aluminum alloy includes 8.75-9.25 wt. % Si.

As noted above, the new aluminum casting alloys generally include 0.5-2.0 wt. % copper (Cu). In one approach, the aluminum alloy includes 0.8 to 2.0 wt. % copper. In another approach, the aluminum alloy includes 1.0 to 1.5 wt. % copper. In yet another approach, the aluminum alloy includes 0.7 to 1.3 wt. % copper. In another approach, the aluminum alloy includes 0.8 to 1.2 wt. % copper.

As noted above, the new aluminum casting alloys generally include 0.15-0.60 wt. % Mg. In one approach, the aluminum alloy includes 0.20-0.53 wt. % magnesium (Mg). In one approach the alloy includes ≥0.36 wt. % magnesium (e.g., 0.36-0.53 wt. % Mg). In one approach, the aluminum alloy includes from 0.40 to 0.45 wt. % magnesium. In another approach, the alloy includes ≤0.35 wt. % magnesium (e.g., 0.15-0.35 wt. % Mg). In one another approach, the alloy includes 0.20-0.25 wt. % Mg. Other combinations of magnesium and copper are described below.

The amount of copper plus magnesium may be limited to ensure an appropriate volume fraction of Q phase, as described below. For products to be processed to a T5 temper, and having 0.15-0.35 wt. % Mg (e.g., 0.20-0.25 wt. % Mg), a new aluminum casting alloy may include an amount of copper plus magnesium such that 2.5≤(Cu+10Mg)≤4.5. In one embodiment, a new aluminum casting alloy includes an amount of copper plus magnesium such that 2.5≤(Cu+10Mg)≤4.0. In another embodiment, a new aluminum casting alloy includes an amount of copper plus magnesium such that 2.5≤ (Cu+10Mg)≤3.75. In yet another embodiment, a new aluminum casting alloy includes an amount of copper plus magnesium such that 2.5≤ (Cu+10Mg)≤3.5. In another embodiment, a new aluminum casting alloy includes an amount of copper plus magnesium such that 2.5≤(Cu+10Mg)≤3.25. In yet another embodiment, a new aluminum casting alloy includes an amount of copper plus magnesium such that 2.75≤(Cu+10Mg)≤3.5. In any of the embodiments of this paragraph the magnesium within the aluminum alloy may be limited to 0.15-0.30 wt. % Mg, such as limited to 0.20-0.25 wt. % Mg.

For products to be processed to any of a T5, T6 or T7 temper, a new aluminum casting alloy includes an amount of copper plus magnesium such that 4.7≤(Cu+10Mg)≤5.8. In one embodiment, a new aluminum casting alloy includes an amount of copper plus magnesium such that 4.7≤(Cu+10Mg)≤5.7. In another embodiment, a new aluminum casting alloy includes an amount of copper plus magnesium such that 4.7≤(Cu+10Mg)≤5.6. In yet another embodiment, a new aluminum casting alloy includes an amount of copper plus magnesium such that 4.7≤(Cu+10Mg)≤5.5. In yet another embodiment, a new aluminum casting alloy includes an amount of copper plus magnesium such that 4.8≤(Cu+10Mg)≤5.5. In another embodiment, a new aluminum casting alloy includes an amount of copper plus magnesium such that 4.9≤(Cu+10Mg)≤5.5. In yet another embodiment, a new aluminum casting alloy includes an amount of copper plus magnesium such that 5.0≤(Cu+10Mg)≤5.5. In another embodiment, a new aluminum casting alloy includes an amount of copper plus magnesium such that 5.0≤(Cu+10Mg)≤5.4. In yet another embodiment, a new aluminum casting alloy includes an amount of copper plus magnesium such that 5.1≤(Cu+10Mg)≤5.4. In any of the embodiments of this paragraph, the magnesium within the aluminum alloy may be toward the higher end of the acceptable range, such as from 0.30-0.60 wt. % Mg, or 0.35-0.55 wt. % Mg, or 0.37-0.50 wt. % Mg. or 0.40-0.50 wt. % Mg, or 0.40-0.45 wt. % Mg. In one approach, the aluminum alloy includes about 1.0 wt. % copper (e.g., 0.90-1.10 wt. % Cu, or 0.95-1.05 wt. % Cu) in combination with about 0.4 wt. % magnesium (0.35-0.45 wt. % Mg, or 0.37-0.43 wt. % Mg).

As noted above, the new aluminum casting alloys generally include 0.35 to 0.8 wt. % manganese. In one approach, the aluminum alloy includes 0.45-0.70 wt. % Mn. In another approach, the aluminum alloy includes 0.50-0.65 wt. % Mn. In another approach, the aluminum alloy includes 0.50-0.60 wt. % Mn. In one approach, the weight ratio of iron to manganese (Fe:Mn) in the aluminum alloy is ≤0.50. In another approach, the weight ratio of iron to manganese (Fe:Mn) in the aluminum alloy is ≤0.45. In another approach, the weight ratio of iron to manganese (Fe:Mn) in the aluminum alloy is ≤0.40. In another approach, the weight ratio of iron to manganese (Fe:Mn) in the aluminum alloy is ≤0.35. In another approach, the weight ratio of iron to manganese (Fe:Mn) in the aluminum alloy is ≤0.30.

As noted above, the new aluminum casting alloys may include up to 1.0 wt. % Fe. In one approach, the aluminum alloy includes from 0.01 to 0.5 wt. % Fe. In another approach, the aluminum alloy includes from 0.01 to 0.35 wt. % Fe. In yet approach, the aluminum alloy includes from 0.01 to 0.30 wt. % Fe. In another approach, the aluminum alloy includes from 0.01 to 0.25 wt. % Fe. In yet approach, the aluminum alloy includes from 0.01 to 0.20 wt. % Fe. In another approach, the aluminum alloy includes from 0.01 to 0.15 wt. % Fe. In yet another approach, the aluminum alloy includes from 0.10 to 0.30 wt. % Fe.

As noted above, the new aluminum casting alloys may include up to 5.0 wt. % Zn. In one approach, the alloy includes ≤0.5 wt. % Zn. In another approach, the aluminum alloy includes ≤0.25 wt. % Zn. In yet another approach, the aluminum alloy includes ≤0.15 wt. % Zn. In another approach, the aluminum alloy includes ≤0.05 wt. % Zn. In yet another approach, the aluminum alloy includes ≤0.01 wt. % Zn.

As noted above, the new aluminum casting alloys may include up to 1.0 wt. % Ag. In one embodiment, the aluminum alloy includes ≤0.5 wt. % Ag. In another approach, the aluminum alloy includes ≤0.25 wt. % Ag. In yet another approach, the aluminum alloy includes ≤0.15 wt. % Ag. In another approach, the aluminum alloy includes ≤0.05 wt. % Ag. In yet another approach, the aluminum alloy includes ≤0.01 wt. % Ag.

As noted above, the new aluminum casting alloys may include up to 1.0 wt. % Ni. In one embodiment, the aluminum alloy includes ≤0.5 wt. % Ni. In another approach, the aluminum alloy includes ≤0.25 wt. % Ni. In yet another approach, the aluminum alloy includes ≤0.15 wt. % Ni. In another approach, the aluminum alloy includes ≤0.05 wt. % Ni. In yet another approach, the aluminum alloy includes ≤0.01 wt. % Ni.

As noted above, the new aluminum casting alloys may include up to 1.0 wt. % Hf. In one embodiment, the aluminum alloy includes ≤0.5 wt. % Hf. In another approach, the aluminum alloy includes ≤0.25 wt. % Hf. In yet another approach, the aluminum alloy includes ≤0.15 wt. % Hf. In another approach, the aluminum alloy includes ≤0.05 wt. % Hf. In yet another approach, the aluminum alloy includes ≤0.01 wt. % Hf.

As noted above, the new aluminum casting alloys may include up to 0.30 wt. % each of zirconium and vanadium. For high pressure die casting embodiments, both zirconium and vanadium may be present, and in an amount of at least 0.05 wt. % each, and wherein the total amount of Zr+V does not form primary phase particles (e.g., the total amount of Zr+V is from 0.10 wt. to 0.50 wt. %). In one embodiment, the aluminum alloy includes at least 0.07 wt. % each of zirconium and vanadium, and Zr+V is from 0.14 to 0.40 wt. %. In one embodiment, the aluminum alloy includes at least 0.08 wt. % each of zirconium and vanadium, and Zr+V is from 0.16 to 0.35 wt. %. In one embodiment, the aluminum alloy includes at least 0.09 wt. % each of zirconium and vanadium, and Zr+V is from 0.18 to 0.35 wt. %. In one embodiment, the aluminum alloy includes at least 0.09 wt. % each of zirconium and vanadium, and Zr+V is from 0.20 to 0.30 wt. %. In another approach, the aluminum alloy includes ≤0.03 wt. % each of zirconium and vanadium (e.g., as impurities for non-HPDC applications).

As noted above, the new aluminum casting alloys may include up to 0.30 wt. % titanium. In one embodiment, the aluminum alloy includes from 0.005 to 0.25 wt. % Ti. In another embodiment, the aluminum alloy includes from 0.005 to 0.20 wt. % Ti. In yet another embodiment, the aluminum alloy includes from 0.005 to 0.15 wt. % Ti. In another embodiment, the aluminum alloy includes from 0.01 to 0.15 wt. % Ti. In yet another embodiment, the aluminum alloy includes from 0.03 to 0.15 wt. % Ti. In another embodiment, the aluminum alloy includes from 0.05 to 0.15 wt. % Ti. When both zirconium and titanium are used in the new aluminum alloy, the aluminum alloy generally includes at least 0.005 wt. % Ti, such as any of the amounts of titanium described above. In one embodiment, the aluminum alloy includes at least 0.09 wt. % each of zirconium and vanadium, and Zr+V is from 0.18 to 0.35 wt. % and from 0.05 to 0.15 wt. % Ti.

As noted above, the new aluminum casting alloys may include up to 0.10 wt. % of one or more of strontium, sodium and antimony. In one approach, the aluminum alloy includes ≤0.05 wt. % strontium. In one approach, the aluminum alloy includes ≤0.03 wt. % sodium. In one approach, the aluminum alloy includes ≤0.03 wt. % antimony. In one embodiment, the aluminum alloy includes strontium, and from 50-300 ppm of strontium. In one embodiment, the aluminum alloy is free of sodium and antimony, and includes these elements as impurities only.

As noted above, the new aluminum casting alloys generally include other elements being ≤0.04 wt. % each and ≤0.12 wt. % in total, the balance being aluminum. In one embodiment, the new aluminum casting alloys generally include other elements being ≤0.03 wt. % each and ≤0.10 wt. % in total, the balance being aluminum

In one embodiment, the new aluminum casting alloy includes 9.14-9.41 wt. % Si, 0.54-1.53 wt. % Cu, 0.21-0.48 wt. % Mg, 0.48-0.53 wt. % Mn, 0.13-0.17 wt. % Fe, 0.11-0.30 wt. % Ti, 0.10-0.14 wt. % Zr, 0.12-0.13 wt. % V, ≤0.05 wt. % Zn, ≤0.05 wt. % Ag, ≤0.05 wt. % Ni, ≤0.05 wt. % Hf, up to 0.012 wt. % Sr, other elements being ≤0.04 wt. % each and ≤0.12 wt. % in total, the balance being aluminum. For alloys to be processed to the T5 temper, this alloy may include 0.20-0.25 wt. % Mg, and with Cu+10Mg being from 2.5 to 4.0. For alloys to be processed to any of a T5, T6 or T7 temper, this alloy may include 0.40-0.48 wt. % Mg, and with Cu+10Mg being from 4.7 to 5.8.

II. Processing

The new aluminum casting alloy may be shape cast in any suitable form or article. In one approach, the new aluminum alloy is shape cast in the form of an automotive component or engine component (e.g., a cylinder head or cylinder/engine block).

In one approach, a method of producing a shape cast article includes the steps of:

• • (a) obtaining the above-described aluminum alloy by melting the appropriate amounts of the above-described elements in an appropriate melting apparatus;
  • (b) introducing the molten aluminum alloy into a mold; and
  • (c) removing a defect-free shape cast article from the mold.After the removing step, the method may optionally include:
  • (d) tempering the shape cast article (e.g., tempering to a T5, T6 or T7 temper).Defect-free means that the shape-cast article can be used for its intended purpose.

Regarding the introducing step (b), the mold may be any suitable mold compatible with the new aluminum casting alloy, such as a high pressure die casting (HPDC) mold.

Prior to the removing step (c), the method may include allowing the casting to solidify, and then cooling the casting. In one embodiment, the cooling step includes contacting the shape casting with water after the solidifying step. In another embodiment, the cooling step includes contacting the shape casting with air and/or water after the solidifying step. After the removing step (c), the method may include tempering the shape cast article.

In one embodiment, the tempering is tempering to a T5 temper. As defined by ANSI H35.1 (2009), the T5 temper is where an aluminum alloy is “cooled from an elevated temperature shaping process and then artificially aged. Applies to products that are not cold worked after cooling from an elevated temperature shaping process, or in which the effect of cold work in flattening or straightening may not be recognized in mechanical property limits.” When tempering to a T5 temper, the tempering step may include, after the removing step, artificially aging the shape cast article. The artificially aging may be accomplished as described below. Due to the shape casting process (e.g., HPDC), the T5 temper does not require a separate solution heat treatment and quench (i.e., is free of a separate solution heat treatment and quenching step, as are required by the T6 and T7 temper.

In another embodiment, the tempering is tempering to a T6 temper. As defined by ANSI H35.1 (2009), the T6 is where an aluminum alloy is “solution heat-treated and then artificially aged. Applies to products that are not cold worked after solution heat-treatment, or in which the effect of cold work in flattening or straightening may not be recognized in mechanical property limits.” When tempering to a T6 temper, the tempering step (d) may include (i) solutionizing of the shape cast article and subsequent (ii) quenching of the shape cast article. After the quenching step (ii), the method may include (iii) artificial aging of the shape cast article.

In yet another embodiment, the tempering is tempering to a T7 temper. As defined by ANSI H35.1 (2009), the T7 is where an aluminum alloy is “solution heat-treated and overaged/stabilized. Applies to cast products that are artificially aged after solution heat-treatment to provide dimensional and strength stability.” When tempering to a T7 temper, the tempering step (d) may include (i) solutionizing of the shape cast article and subsequent (ii) quenching of the shape cast article. After the quenching step (ii), the method may include (iii) artificially aging of the shape cast article to an overaged/stabilized condition.

In one approach, a method includes solution heat treating and quenching the aluminum alloy. In one embodiment, the solution heat treating comprises the steps of:

• • (a) heating the aluminum alloy to a first temperature (e.g., subjecting the alloy to a 2 hour±15 minutes heat-up from ambient temperature up to 504.4° C.±5.0° C.);
  • (b) first maintaining the first temperature (e.g., for at least 0.5-8 hours, such as for about 2 hours);
  • (c) ramping the temperature to a second higher temperature (e.g., ramping to 530° C.±5.0° C. and over a period of 5-60 minutes, such as ramping to the second temperature in about 30 minutes);
  • (d) second maintaining the second temperature at 530° C. (e.g., for 2-8 hours, such as holding for about 4 hours).

After the second maintaining step (d), the aluminum alloy may be quenching (e.g., in water and/or air).

As noted above, the tempering step may include artificially aging the aluminum alloy. In one embodiment, the artificially aging comprises holding the alloy at a temperature of from 190° C. to 220° C. for 1-10 hours (e.g., for about 6 hours). In another embodiment, the artificial aging is conducted at a temperature of from 175° C. to 205° C. for 1-10 hours (e.g., for about 6 hours).

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a graph of phase equilibria involving (Al) and liquid in an Al—Cu—Mg—Si system.

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.

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.

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

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

FIG. 6 is a graph of the effect of Mg and Cu content on the equilibrium solidus temperature (T_S) and Q-phase formation temperature (T_Q) of Al-9% Si—Mg—Cu alloys.

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

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

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

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

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

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

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

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.

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

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

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.

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.

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.

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.

FIG. 25 is a graph of Mg and Cu content correlated to strength and ductility for Al-9Si—Mg—Cu alloys.

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

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

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.

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

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

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

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

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

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

EXAMPLE 1

High Performance AlSiCuMg Cast Alloys

1.1 Alloy Development Methods Based on Computational Thermodynamics

To improve the performances of Al—Si—Mg—Cu cast alloys, a novel alloy design method was used and is described as follows:

In Al—Si—Mg—Cu casting alloys, increasing Cu content can increase the strength due to higher amount of θ′-Al₂Cu 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 Al—Cu—Mg—Si quaternary system, as shown in X. Yan, Thermodynamic and solidification modeling coupled with experimental investigation of the multicomponent aluminum alloys. University of Wisconsin—Madison, 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 Al—Si—Mg 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.

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.

The inventors of the present disclosure recognize that adding Cu to Al—Si—Mg 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 θ—Al₂Cu phase formed at ˜510° C. The volume fraction of each constituent phase and their formation temperatures are also influenced by the Cu content.

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 θ-Al₂Cu and Q-AlCuMgSi increases while the amount of Mg₂Si and π-AlFeMgSi decreases. In alloys with more than 0.7% Cu, Mg₂Si 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%.

The Q-AlCuMgSi phase formation temperature (T_Q) in Al-9% Si—Mg—Cu 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.

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_H) needs to be controlled above the formation temperature of the Q-AlCuMgSi phase, i.e., T_H>T_Q. The upper limit of the solution heat treatment temperature is the equilibrium solidus temperature (T_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_S−10° C.>T_H>T_Q  (1)

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% Si—Cu—Mg 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_S−10° 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_Q<T_S−10° C. Projection of the curve A-B-C to the Cu—Mg 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_S−15° 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_S−5° 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.

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

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

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 Al—Cu—Mg—Si space where the formation temperature of all dissolvable constituent phases is at least 10° C. below the solidus temperature. The Al—Cu—Mg—Si 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., Al—Cu—Mg—Si, 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.

1.2 Composition Selection for Tensile Bar Casting

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 Al—Si—Mg—(Cu) alloys can increase both ductility and strength of the alloy. As shown in FIG. 7, zinc can also increase the fluidity of Al—Si—Mg 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.

TABLE 3
Target Compositions (all values in weight percent)
Alloy	Si	Cu	Mg	Zn	Ag	Fe	Sr*	Ti	B
1	Al—9Si—0.5Mg	9	0	0.5	0	0	<0.1	0.0125	0.04	0.003
2	Al—9Si—0.35Mg—0.75Cu—4Zn	9	0.75	0.35	4	0	<0.1	0.0125	0.04	0.003
3	Al—9Si—0.45Mg—0.75Cu—4Zn	9	0.75	0.45	4	0	<0.1	0.0125	0.04	0.003
4	Al—9Si—0.45Mg—0.75Cu	9	0.75	0.45	0	0	<0.1	0.0125	0.04	0.003
5	Al—9Si—0.5Mg—0.75Cu	9	0.75	0.5	0	0	<0.1	0.0125	0.04	0.003
6	Al—9Si—0.35Mg—1.25Cu	9	1.25	0.35	0	0	<0.1	0.0125	0.04	0.003
7	Al—9Si—0.45Mg—1.25Cu	9	1.25	0.45	0	0	<0.1	0.0125	0.04	0.003
8	Al—9Si—0.55Mg—1.25Cu	9	1.25	0.55	0	0	<0.1	0.0125	0.04	0.003
9	Al—9Si—0.35Mg—1.75Cu	9	1.75	0.35	0	0	<0.1	0.0125	0.04	0.003
10	Al—9Si—0.35Mg—1.75Cu—0.5Ag	9	1.75	0.35	0	0.5	<0.1	0.0125	0.04	0.003

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.

TABLE 4
Actual Compositions (all values in weight percent)
Alloy	Si	Cu	Mg	Zn	Ag	Fe	Sr*	Ti	B
1	Al—9Si—0.5Mg	8.87	0.021	0.48	0	0	0.079	0.0125	0.05	0.003
2	Al—9Si—0.35Mg—0.75Cu—4Zn	9.01	0.75	0.37	4.03	0	0.077	0.0125	0.031	0.003
3	Al—9Si—0.45Mg—0.75Cu—4Zn	9.09	0.75	0.46	4.02	0	0.081	0.0125	0.04	0.003
4	Al—9Si—0.45Mg—0.75Cu	9.18	0.76	0.45	0	0	0.083	0.0125	0.042	0.003
5	Al—9Si—0.5Mg—0.75Cu	9.02	0.77	0.49	0	0	0.081	0.0125	0.013	0.003
6	Al—9Si—0.35Mg—1.25Cu	9.02	1.25	0.34	0	0	0.088	0.0125	0.03	0.003
7	Al—9Si—0.45Mg—1.25Cu	9.11	1.28	0.44	0	0	0.082	0.0125	0.04	0.003
8	Al—9Si—0.55Mg—1.25Cu	8.99	1.27	0.53	0	0	0.1	0.0125	0.04	0.003
9	Al—9Si—0.35Mg—1.75Cu	9.29	1.83	0.37	0	0	0.08	0.0125	0.048	0.003
10	Al—9Si—0.35Mg—1.75Cu—0.5Ag	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.

TABLE 5
Hydrogen Content of the Castings
Alloy	H Content (ppm)
1	Al—9Si—0.5Mg	0.14
2	Al—9Si—0.35Mg—0.75Cu—4Zn	0.11
3	Al—9Si—0.45Mg—0.75Cu—4Zn	0.19
4	Al—9Si—0.45Mg—0.75Cu	0.11
5	Al—9Si—0.5Mg—0.75Cu	0.14
6	Al—9Si—0.35Mg—1.25Cu	0.15
7	Al—9Si—0.45Mg—1.25Cu	0.13
8	Al—9Si—0.55Mg—1.25Cu	0.16
9	Al—9Si—0.35Mg—1.75Cu	0.13
10	Al—9Si—0.35Mg—1.75Cu—0.5Ag	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

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.

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	Al—9Si—0.5Mg	560	—	563
2	Al—9Si—0.35Mg—0.75Cu—4Zn	470	518	540
3	Al—9Si—0.45Mg—0.75Cu—4Zn	470	518	543
4	Al—9Si—0.45Mg—0.75Cu	510	541	554
5	Al—9Si—0.5Mg—0.75Cu	510	541	553
6	Al—9Si—0.35Mg—1.25Cu	510	533	552
7	Al—9Si—0.45Mg—1.25Cu	510	536	548
8	Al—9Si—0.55Mg—1.25Cu	510	538	545
9	Al—9Si—0.35Mg—1.75Cu	510	528	543
10	Al—9Si—0.35Mg—1.75Cu—0.5Ag	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.

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_H
  • 6 hour soak at T_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_H
  • 6 hour soak at T_H
  • CWQ (Cold Water Quench)The final step solution heat treatment temperature T_H was determined from following equation based on Mg and Cu content:T_H(° C.)=570−10.48*Cu−71.6*Mg−1.3319*Cu*Mg−0.72*Cu*Cu+72.95*Mg*Mg,  (2)where, Mg and Cu are magnesium and copper contents, in wt. %. A lower limit for T_H is defined by:T_Q=533.6−20.98*Cu+88.037*Mg+33.43*Cu*Mg−0.7763*Cu*Cu−126.267*Mg*Mg  (3)An upper limit for T_H is defined by:T_S=579.2−10.48*Cu−71.6*Mg−1.3319*Cu*Mg−0.72*Cu*Cu+72.95*Mg*Mg  (4)

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 β-AlFeSi, π-AlFeMgSi and Al₇Cu₂Fe phases. The morphologies of these un-dissolved phases are shown in FIG. 9 at higher magnification.

1.4 Experimental Results

1.4.1 Property Characterization

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 mm×10 mm×55 mm machined from the tensile-bar casting. Two specimens were measured for each alloy.

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 10⁷ cycles. Smooth fatigue round specimens were obtained by slightly machining the gauge portion of the tensile bar casting.

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.

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.

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. Al—9Si—0.5Mg	405.8	323.3	8.3	543.2	398.5	326.5	6.5	520.4
2. Al—9Si—0.35Mg—0.75Cu—4Zn	431.5	342.0	5.5	542.6	433.5	358.0	4.5	531.5
3. Al—9Si—0.45Mg—0.75Cu—4Zn	460.5	370.5	5.5	571.6	469.0	378.5	7.0	595.8
4. Al—9Si—0.45Mg—0.75Cu	451.5	339.0	6.5	573.4	450.5	354.8	5.0	555.3
5. Al—9Si—0.5Mg—0.75Cu	426.0	317.3	8.0	561.5	442.8	348.2	6.7	566.4
6. Al—9Si—0.35Mg—1.25Cu	411.2	299.2	7.3	540.2	436.3	326.3	7.0	563.1
7. Al—9Si—0.45Mg—1.25Cu	424.3	328.0	4.8	525.8	453.8	353.0	5.8	567.7
8. Al—9Si—0.55Mg—1.25Cu	444.8	336.5	6.0	561.6	460.3	365.3	4.8	561.8
9. Al—9Si—0.35Mg—1.75Cu	465.7	325.0	9.0	608.8	459.5	355.3	5.5	570.6
10. Al—9Si—0.35Mg—1.75Cu—0.5Ag	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. Al—9Si—0.5Mg	398.7	340.2	5.3	507.7
	2. Al—9Si—0.35Mg—0.75Cu—4Zn	446.8	366.0	6.5	568.7
	3. Al—9Si—0.45Mg—0.75Cu—4Zn	465.3	390.7	5.0	570.2
	4. Al—9Si—0.45Mg—0.75Cu	464.0	373.5	6.5	585.9
	5. Al—9Si—0.5Mg—0.75Cu	442.5	364.5	6.0	559.2
	6. Al—9Si—0.35Mg—1.25Cu	446.5	342.8	6.5	568.4
	7. Al—9Si—0.45Mg—1.25Cu	455.3	375.8	4.0	545.6
	8. Al—9Si—0.55Mg—1.25Cu	475.8	385.0	4.8	577.3
	9. Al—9Si—0.35Mg—1.75Cu	478.8	386.3	5.0	583.6
	10. Al—9Si—0.35Mg—1.75Cu—0.5Ag	471.0	389.3	4.5	569.0
	*Averaged value from five tensile specimens.
	The Quality Index, Q = UTS + 150 log(E).

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. Al—9Si—0.5Mg	6	27	23	27
3. Al—9Si—0.45Mg—0.75Cu—4Zn	17	18	10	12
4. Al—9Si—0.45Mg—0.75Cu	32	15	28	13
7. Al—9Si—0.45Mg—1.25Cu	27	12	7	12
9. Al—9Si—0.35Mg—1.75Cu	16	15	8	9

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. Al—9Si—0.5Mg	100	1680725	1231620
1. Al—9Si—0.5Mg	100	1302419	272832
1. Al—9Si—0.5Mg	100	4321029	1077933
1. Al—9Si—0.5Mg	150	71926	148254
1. Al—9Si—0.5Mg	150	242833	42791
1. Al—9Si—0.5Mg	150	153073	56603
1. Al—9Si—0.5Mg	200	16003	54623
1. Al—9Si—0.5Mg	200	8654	30708
1. Al—9Si—0.5Mg	200	36597	39376
3. Al—9Si—0.45Mg—0.75Cu—4Zn	100	160572	248032
3. Al—9Si—0.45Mg—0.75Cu—4Zn	100	298962	131397
3. Al—9Si—0.45Mg—0.75Cu—4Zn	100	120309	394167
3. Al—9Si—0.45Mg—0.75Cu—4Zn	150	120212	12183
3. Al—9Si—0.45Mg—0.75Cu—4Zn	150	70152	42074
3. Al—9Si—0.45Mg—0.75Cu—4Zn	150	190200	31334
3. Al—9Si—0.45Mg—0.75Cu—4Zn	200	38369	18744
3. Al—9Si—0.45Mg—0.75Cu—4Zn	200	29686	14822
3. Al—9Si—0.45Mg—0.75Cu—4Zn	200	39366	11676
4. Al—9Si—0.45Mg—0.75Cu	100	485035	575446
4. Al—9Si—0.45Mg—0.75Cu	100	4521553	233110
4. Al—9Si—0.45Mg—0.75Cu	100	3287495	940229
4. Al—9Si—0.45Mg—0.75Cu	150	170004	141654
4. Al—9Si—0.45Mg—0.75Cu	150	110500	234640
4. Al—9Si—0.45Mg—0.75Cu	150	688783	238478
4. Al—9Si—0.45Mg—0.75Cu	200	108488	22686
4. Al—9Si—0.45Mg—0.75Cu	200	40007	36390
4. Al—9Si—0.45Mg—0.75Cu	200	51678	20726
7. Al—9Si—0.45Mg—1.25Cu	100	1115772	1650686
7. Al—9Si—0.45Mg—1.25Cu	100	318949	1744140
7. Al—9Si—0.45Mg—1.25Cu	100	468848	484262
7. Al—9Si—0.45Mg—1.25Cu	150	102341	232171
7. Al—9Si—0.45Mg—1.25Cu	150	145766	106741
7. Al—9Si—0.45Mg—1.25Cu	150	63720	226188
7. Al—9Si—0.45Mg—1.25Cu	200	41686	21873
7. Al—9Si—0.45Mg—1.25Cu	200	20709	58819
7. Al—9Si—0.45Mg—1.25Cu	200	52709	4367
9. Al—9Si—0.35Mg—1.75Cu	100	2159782	2288145
9. Al—9Si—0.35Mg—1.75Cu	100	354677	1011473
9. Al—9Si—0.35Mg—1.75Cu	100	4258369	783758
9. Al—9Si—0.35Mg—1.75Cu	150	281867	164554
9. Al—9Si—0.35Mg—1.75Cu	150	135810	188389
9. Al—9Si—0.35Mg—1.75Cu	150	100053	146740
9. Al—9Si—0.35Mg—1.75Cu	200	24014	48506
9. Al—9Si—0.35Mg—1.75Cu	200	30695	8161
9. Al—9Si—0.35Mg—1.75Cu	200	62211	31032

1.4.2 Mechanical Properties at Room Temperature1.4.2.1 Effect of Aging Temperature on Tensile Properties

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.

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.

1.4.2.2 Effects of Alloy Elements on Tensile Properties

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.

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.

FIG. 13 shows the effect of Mg content (0.35-0.55 wt %) on the tensile properties of the Al-9% Si-1.25% Cu—Mg 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 π-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% Cu—Mg alloys was overall found to be insignificant.

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).

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).

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.

Ultimate tensile strength: 450-470 MPa
Tensile yield strength:    360-390 MPa
Elongation:                5-7%
Quality index:             560-590 MPa

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% Si—Mg—Cu 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.

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.

1.4.4 Charpy Impact Tests

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 %.

1.4.5 S-N Fatigue Tests

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.

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.

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.

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 Al—Si—Mg—(Cu) casting alloys. Again, alloy 3 showed a lower fatigue performance than others.

1.4.6 Corrosion Tests—ASTM G110

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.

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.

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.

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.

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.

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.

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.

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.

The present disclosure has described Al—Si—Cu—Mg 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-9Si—MgCu 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

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.

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.

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.

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.

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.

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

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).

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

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.

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.

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.

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.

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

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.

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

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

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.

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

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.

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.

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.

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.

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-0.55Mn—Cu—Mg 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.

Table 16 shows the effect of Cu, Mg and aging condition on ultimate tensile strength of the Al-9Si-0.15Fe-0.55Mn—Cu—Mg 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-0.55Mn—Cu—Mg 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.

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

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

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

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-0.55Mn—Cu—Mg 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-0.55Mn—Cu—Mg 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-0.55Mn—Cu—Mg alloys. After being completely solidified, the tensile bar castings were cooled in warm water.

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.

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

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

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

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.

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.

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

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

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.	σa (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 (=σ_min/σ_max) with a frequency of 1500 rpm, and with a mean stress (σ_m) of zero (0) MPa. The fatigue was 90 MPa at room temperature.

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 81.25±7.83 MPa at 150° C. The stress amplitude increment was 5.0 MPa and the convergence factor was 0.94.

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.

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 0.14≤Zr+V≤0.40up 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.