Methods for producing forged products and other worked products

1. A method comprising:

(a) using additive manufacturing to produce a metal shaped-preform, wherein the metal shaped-preform comprises a titanium alloy; and

(b) after the using step (a), forging the metal shaped-preform, in a single die forging step, into a final forged product;

wherein the single die forging step is using a single blocker die to die forge the metal-shaped preform into the final forged product; and

wherein the single die forging step comprises non-uniformly applying strain to the metal shaped-preform.

2. The method of claim 1 , wherein the final forged product is a jet engine blade for a jet engine.

3. The method of claim 1 , wherein the titanium alloy includes at least 50 wt. % Ti and at least one titanium aluminide phase, wherein the at least one titanium aluminide phase is selected from the group consisting of Ti 3 Al, TiAl and combinations thereof.

4. The method of claim 1 , wherein the titanium alloy includes 5-30 wt. % aluminum, and the titanium alloy comprises at least some Ti 3 Al.

5. The method of claim 1 , wherein the titanium alloy is a Ti-6Al-4V alloy.

6. The method of claim 1 , wherein the forging step comprises:

heating the metal shaped-preform to a stock temperature; and

contacting the metal shaped-preform with a forging die, wherein, when the contacting step is initiated, the forging die is a temperature that is at least 10° F. lower than the stock temperature.

7. The method of claim 1 , comprising:

after the forging step (b), annealing the final forged product.

8. The method of claim 7 , wherein the annealing step comprises heating the final forged product to a temperature of from 670° C. to 750° C.

9. A method comprising:

(a) using additive manufacturing to produce a titanium alloy preform for a jet engine, wherein the titanium alloy preform comprises a titanium alloy; and

(b) after the using step (a), forging the titanium alloy preform, in a single die forging step, into a jet engine blade for a jet engine;

wherein the single die forging step is using a single blocker die to die forge the titanium alloy preform into the jet engine blade; and

wherein the single die forging step comprises non-uniformly applying strain to the metal shaped-preform.

10. The method of claim 9 , wherein the titanium alloy includes at least 50 wt. % Ti and at least one titanium aluminide phase, wherein the at least one titanium aluminide phase is selected from the group consisting of Ti 3 Al, TiAl and combinations thereof.

11. The method of claim 9 , wherein the titanium alloy includes 5-30 wt. % aluminum, and the titanium alloy comprises at least some Ti 3 Al.

12. The method of claim 9 , wherein the titanium alloy is a Ti-6Al-4V alloy.

13. The method of claim 9 , wherein the forging step comprises:

heating the titanium alloy preform to a stock temperature; and

contacting the titanium alloy preform with a forging die, wherein, when the contacting step is initiated, the forging die is a temperature that is at least 10° F. lower than the stock temperature.

14. The method of claim 9 comprising,

after the forging step (b), annealing the jet engine blade.

15. The method of claim 14 , wherein the annealing step comprises heating the jet engine blade to a temperature of from 670° C. to 750° C.

16. A method comprising:

(a) using additive manufacturing to produce a ring-shaped metal preform;

(i) wherein the ring-shaped metal preform comprises one of a titanium alloy, an aluminum alloy, a nickel alloy, a steel, a stainless steel, and a metal matrix composite;

(ii) wherein the using step comprises adding metal, via the additive manufacturing, to a building substrate thereby producing the ring-shaved preform;

(iii) wherein the building substrate is a first ring of a first metal material, wherein the additive manufacturing comprises adding a second metal material to the first ring thereby forming a second ring integral with the first ring, wherein the ring-shaped metal preform comprises the first ring and the second ring; and

(b) after the using step (a), working the ring-shaped preform into a final worked ring-shaped product via at least one of ring rolling and ring forging.

17. The method of claim 16 , wherein the first metal material is the same as the second metal material.

18. The method of claim 16 , wherein the first metal material is different than the second metal material.

19. The method of claim 18 , comprising:

first selecting a high toughness material as the first metal material;

second selecting a high strength material as the second metal material;

after the first selecting step and after the second selecting step, completing the using step (a) and the working step (b).

20. The method of claim 19 , comprising:

after the working step (b), using the final worked ring-shaped product as an engine containment ring in an aerospace engine.