Composite, internal reinforced ceramic cores and related methods

• US 5,947,181 A
• Filed: 07/10/1996
• Issued: 09/07/1999
• Est. Priority Date: 07/10/1996
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Davis, Richard Mallory
• Primary Examiner(s): Achutamurthy, Ponnathapura
• Assistant Examiner(s): PONNALURI, PADMASHRI
• Application Number:
  US08/677,997
• Time in Patent Office: 1,154 Days
• Field of Search: 428/34.4, 164/132, 164/398, 164/399, 164/131, 164/47, 29/889.721
• US Class Current: 164/132
• CPC Class Codes: B22C 21/14 for reinforcing or securing moulding materials or cores, e.g. gaggers, chaplets, pins, bars
• CPC Class Codes: B22C 9/106 Vented or reinforced cores
• CPC Class Codes: Y10T 428/131 Glass, ceramic, or sintered, fused, fired, or calcined metal oxide or metal carbide containing [e.g., porcelain, brick, cement, etc.]

Abstract

A method of improving structural stability of a ceramic core used in the casting of turbine components includes the steps of a) providing a die having a predetermined geometry which gives the ceramic core a shape corresponding to interior spaces in the turbine component; b) inserting elongated strengthening members into interior or more areas of the die corresponding to one or more of the interior spaces; c) injecting a ceramic slurry into the die so as to substantially enclose the strengthening members; and d) firing the ceramic slurry to form a hardened ceramic core. A ceramic core used in a high temperature gas turbine component casting process includes a ceramic body having a geometry corresponding to internal passages of a gas turbine component; and at least one elongated rod or tube incorporated in the ceramic body, the rod or tube comprised of a material which retains structural stability at temperatures in excess of about 2600° F. In a method of casting a gas turbine component having interior passages, and including inserting a ceramic core in a casting die wherein the ceramic core is shaped to correspond to the interior passages, pouring molten metal into the die, and solidifying the molten metal and extracting the ceramic core, an improvement is disclosed which includes incorporating at least one strengthening member in the ceramic core to improve structural stability of the core during pouring and solidifying the molten metal.

Claims

1. A method of improving structural stability of a ceramic core used in the casting of hollow components comprising the steps of:

a) providing a die having a geometry which gives the ceramic core a shape corresponding to interior spaces in the component;

b) inserting elongated strengthening members into one or more interior areas of said die corresponding to said interior spaces, said strengthening members having a length substantially equal to a corresponding length of said interior passages and said strengthening members being made of a material selected from the group consisting of alumina, quartz, molybdenum, tungsten and tungsten carbide;

c) injecting a ceramic slurry into said die so as to completely enclose said strengthening members; and

d) firing the ceramic slurry to form a hardened ceramic core.

2. The method of claim 1 wherein said strengthening members are made of alumina.

3. The method of claim 1 wherein said strengthening members are solid alumina rods.

4. The method of claim 1 wherein said strengthening members are hollow alumina tubes.

5. The method of claim 4 wherein said hollow alumina tubes are filled with another ceramic material of different composition.

6. The method of claim 1 wherein said die is configured to give the ceramic core a shape corresponding to internal coolant passages in a gas turbine bucket or nozzle.

7. The method of claim 1 wherein said strengthening members are made of material having structural stability at temperatures in excess of 2600°

F.

8. The method of claim 1 wherein said strengthening members have a round cross-section.

9. The method of claim 1 wherein said strengthening members have a rectangular cross-section.

10. A ceramic core used in a high temperature hollow component casting process, comprising:

a ceramic body having a geometry corresponding to internal passages of a hollow component; and

a strengthening member comprising at least one elongated rod or tube completely enclosed within said ceramic body, said rod or tube made of a material which retains structural stability at temperatures in excess of about 2600°

F.

11. The ceramic core of claim 10 wherein said ceramic body has a geometry corresponding to internal coolant passages in a turbine bucket or nozzle.

12. The ceramic core of claim 11 wherein a pair of elongated rods are located in each of said internal coolant passages.

13. The ceramic core of claim 10 wherein said at least one rod or tube is composed of alumina.

14. The ceramic core of claim 10 including a plurality of elongated rods or tubes.

19. The ceramic core of claim 10 including one or more wax extensions on one or both ends of said elongated rod or tube to permit said rod or tube to axially expand under molten metal pouring temperatures.

15. In a method of casting a gas turbine component having interior passages, and including inserting a ceramic core into a casting die wherein the ceramic core is shaped to correspond to said interior passages, pouring molten metal into said die, solidifying said molten metal and extracting said ceramic core, an improvement comprising incorporating at least one strengthening member in said ceramic core to improve structural stability of said core during pouring and solidifying said molten metal, said strengthening member consisting of a solid rod completely enclosed within said core and having a length substantially equal to a corresponding length of said interior passages, and wherein said strengthening member is made of a material selected from the group consisting of alumina, quartz, molybdenum, tungsten and tungsten carbide.

16. The method of claim 15, and further including the step of removing said ceramic core and then extracting said at least one strengthening member through openings in the gas turbine component.

17. The method of claim 15 and further including the step of removing said ceramic core and said strengthening member by leaching.

18. The method of claim 16 wherein the ceramic core is removed by leaching.