DETECTION OF BLOCKAGE IN INTERNAL PASSAGES OF GAS TURBINE ENGINE COMPONENTS

• US 20180214941A1
• Filed: 02/01/2017
• Published: 08/02/2018
• Est. Priority Date: 02/01/2017
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Castle, Lea Kennard, Gautschi, Steven Bruce, Auxier, James Tilsley
• Granted Patent: US 10,456,831 B2
• Time in Patent Office: Days
• CPC Class Codes: B22C 9/04 Use of lost patterns
• CPC Class Codes: B22C 9/10 Cores; Manufacture or installation of cores breaker cores B22C9/084
• CPC Class Codes: B22C 9/24 for hollow articles
• CPC Class Codes: B22D 25/02 by its peculiarity of shape; of works of art cylinders, pistons B22D15/02
• CPC Class Codes: B22D 29/002 by leaching, washing or dissolving
• CPC Class Codes: B22D 46/00 Controlling, supervising, not restricted to casting covered by a single main group, e.g. for safety reasons controlling or regulating in general G05
• CPC Class Codes: G01N 23/04 and forming images of the material
• CPC Class Codes: G01N 23/18 Investigating the presence of flaws defects or foreign matter

Abstract

A method of forming a component includes the steps of placing a core into a mold and pouring a component material around the core. The component material is allowed to solidify. The core is then removed from within the material, leaving a component having at least a first and a second cavity formed by the core. A first filler material is moved into the first cavity, and a second filler material is moved into the second cavity. The component is inspected for the presence of an apparent residual core within the first cavity and the second cavity. The location is identified of the apparent residual core from the core based upon an identification of whether the location of the apparent residual core is in the first or second filler materials. A method of inspecting a component formed by investment casting is also disclosed.

Claims

1. A method of forming a component comprising:

placing a core into a mold and pouring a component material around the core;

allowing the component material to solidify, and then removing the core from within said material, leaving a component having at least a first and a second cavity formed by said core;

moving a first filler material into the first cavity, and moving a second filler material into the second cavity; and

inspecting said component for the presence of an apparent residual core within said first cavity and said second cavity, and identifying the location of the apparent residual core from said core based upon an identification of whether the location of the apparent residual core is in the first or second filler materials.

2. The method as set forth in claim 1, wherein the location of said second cavity at least partially overlaps the location of said first cavity when viewed from a side of said component.

3. The method as set forth in claim 2, wherein said inspecting step creates an image of said first and second cavity with said second cavity superimposed over said first cavity.

4. The method as set forth in claim 2, wherein said first filler material has a different atomic weight than said second filler material, and wherein said different atomic weights are both greater than an atomic weight of the component material.

5. The method as set forth in claim 2, wherein said first cavity is a central cavity and said second cavity extends between said central cavity and an outer surface of the component.

6. The method as set forth in claim 5, wherein said component includes an airfoil and said central cavity extends along a radial length of said component and wherein there are a plurality of said second cavities on both of two sides of said central cavity.

7. The method as set forth in claim 2, wherein if a residual core material is identified, then a leaching process is repeated.

8. The method as set forth in claim 7, wherein if apparent residual core material is identified, then a step is taken prior to the repeated leaching process to ensure the first and second filler materials completely fill the first and second cavities to ensure that the apparent residual core is not a void in the filler materials.

9. The method as set forth in claim 8, wherein the inspection is through radiation.

10. The method as set forth in claim 1, wherein said component is a gas turbine engine component, and said first and second cavities are first and second passages.

11. The method as set forth in claim 10, wherein said first passage is a central cavity and said second passage extends between said central cavity and an outer surface of the component.

12. The method as set forth in claim 11, wherein said component includes an airfoil and said central cavity extends along a radial length of said component and wherein there are a plurality of said second passages on both of two sides of said central cavity.

13. The method as set forth in claim 12, wherein if a residual core is identified, then a leaching process is repeated.

14. The method as set forth in claim 13, wherein if apparent residual core material is identified, then a step is taken prior to the repeated leaching process to ensure the first and second filler materials completely fill the first and second passages to ensure that the apparent residual core is not a void in the filler materials.

15. The method as set forth in claim 14, wherein the inspection is through radiation.

16. The method as set forth in claim 1, wherein if a residual core material is identified, then a leaching process is repeated.

17. The method as set forth in claim 16, wherein if an apparent residual core material is identified, then a step is taken prior to the repeated leaching process to ensure the first and second filler materials completely fill the first and second passages to ensure that the apparent residual core is not a void in the filler materials.

18. The method as set forth in claim 1, wherein the inspection is through radiation.

19. The method as set forth in claim 18, wherein the inspection is through x-ray radiation.

20. The method as set forth in claim 1, wherein said first filler material has a different atomic weight than said second filler material, and wherein said different atomic weights are both greater than an atomic weight of the component material.

21. A method of inspecting an article formed by investment casting using a ceramic inner core, comprising the steps of:

receiving the article with the ceramic inner core removed, the article having a first and a second passage formed by the ceramic inner core;

moving a first filler material into the first passage, and moving a second filler material into the second passage; and

inspecting the article for the presence of an apparent residual core within said first passage and said second passage, and identifying the location of the apparent residual core from said core based upon an identification of whether the location of the apparent residual core is in the first or second filler materials.