Method and system for die casting a hybrid component

Patent metadata

Field	Value
Publication number	US-9925584-B2
Application number	US-201113248338-A
Country	US
Kind code	B2
Filing date	Sep 29, 2011
Priority date	Sep 29, 2011
Publication date	Mar 27, 2018
Grant date	Mar 27, 2018

Abstract

A method for die casting a hybrid component includes defining a cavity within a die element of a die and inserting a spar into the cavity. Molten metal is injected into the die element. The molten metal is solidified within the cavity to cast the hybrid component. The spar establishes an internal structure of the hybrid component. The spar includes a high melting temperature material that defines a first melting temperature greater than a second melting temperature of the molten metal.

First claim

What is claimed is:

1. A method for die casting a hybrid component, comprising the steps of:
defining a cavity within a die element of a die;
inserting a spar into the cavity;
injecting molten metal into the die element;
solidifying the molten metal within the cavity to form the hybrid component that is made from at least two different materials, wherein the spar establishes an internal structure of the hybrid component, and wherein the spar includes a high melting temperature material that defines a first melting temperature greater than a second melting temperature of the molten metal, wherein the hybrid component is a gas turbine engine component.

2. The method as recited in claim 1 , comprising the step of:
applying vacuum to the die.

3. The method as recited in claim 1 , wherein the spar includes a refractory metal.

4. The method as recited in claim 1 , wherein the spar includes a ceramic material.

5. The method as recited in claim 1 , wherein the spar includes a ceramic matrix composite.

6. The method as recited in claim 1 , wherein the molten metal includes one of cobalt, a nickel based alloy and titanium.

7. The method as recited in claim 1 , wherein an outer structure of the hybrid component is an equiaxed structure and the internal structure is a non-equiaxed structure.

8. The method as recited in claim 1 , wherein the spar includes a hollow portion.

9. The method as recited in claim 1 , wherein the spar is completely hollow between its outer walls.

10. The method as recited in claim 1 , comprising a coating that protects an outer surface of the spar.

11. The method as recited in claim 1 , wherein the step of inserting the spar includes positioning the spar to extend across a split line of the die.

12. The method as recited in claim 1 , wherein the spar is generally T-shaped.

13. The method as recited in claim 1 , comprising at least one locking feature that captures the spar within the die element.

14. The method as recited in claim 1 , wherein the spar and the die element are made from the same material.

15. The method as recited in claim 1 , wherein a portion of the internal structure of the hybrid component extends beyond an outer structure of the hybrid component after the step of solidifying.

16. The method as recited in claim 1 , wherein the hybrid component is a turbine blade of a gas turbine engine.

17. A method of manufacturing a hybrid gas turbine engine component, comprising:
die casting the hybrid gas turbine engine component in a die casting process such that the hybrid gas turbine engine component includes an internal structure and an outer structure that surrounds the internal structure, the internal structure comprised of a different material from the outer structure.

18. A method, comprising:
defining a cavity within a die element of a die casting system that includes a die that defines the die element, a shot tube in fluid communication with the die element, and a shot tube plunger moveable within the shot tube;
positioning a spar into the cavity;
injecting molten metal into the die element using the die casting system; and
solidifying the molten metal within the cavity to form a hybrid gas turbine engine component that is made from at least two different materials, wherein the spar establishes an internal structure of the hybrid gas turbine engine component and is comprised of a different material than the molten metal.

Assignees

• Bullied Steven J
• Marcin John Joseph
• Verner Carl R
• United Technologies Corp

Inventors

• Bullied Steven J
• Marcin John Joseph
• Verner Carl R

Classifications

• B22D21/025

  Casting heavy metals with high melting point, i.e. 1000 - 1600 degrees C, e.g. Co 1490 degrees C, Ni 1450 degrees C, Mn 1240 degrees C, Cu 1083 degrees C · CPC title

• B22D21/002

  Castings of light metals · CPC title

• B22D17/10

  with horizontal press motion · CPC title

• B22D17/24 Primary

  Accessories for locating and holding cores or inserts · CPC title

• B22D27/045

  Directionally solidified castings · CPC title