MASK SYSTEM FOR GAS TURBINE ENGINE COMPONENT

• US 20140157595A1
• Filed: 12/06/2012
• Published: 06/12/2014
• Est. Priority Date: 12/06/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Trzcinski, Frank J., Brown, Chelsea, Castonguay, Kevin
• Granted Patent: US 9,249,490 B2
• Time in Patent Office: Days
• US Class Current: 29/888
• CPC Class Codes: B05B 12/20 Masking elements, i.e. elements defining uncoated areas on an object to be coated
• CPC Class Codes: C23C 4/01 Selective coating, e.g. pattern coating, without pre-treatment of the material to be coated
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: Y10T 29/49229 Prime mover or fluid pump making
• CPC Class Codes: Y10T 29/53 Means to assemble or disassemble

Abstract

A system to install a mask onto a component of a gas turbine engine includes a drive movable along an axis with respect to a movable base.

Claims

1. A system to install a component into a mask of a gas turbine engine comprising:

a movable base; and

a drive movable along an axis with respect to said movable base.

2. The system as recited in claim 1, wherein said drive supports an insertion cup.

3. The system as recited in claim 2, wherein said insertion cup includes a semi-spherical.

4. The system as recited in claim 2, wherein said insertion cup is non-metallic.

5. The system as recited in claim 1, wherein said drive is a linear motor.

6. The system as recited in claim 1, further comprising a lubrication mister directed toward said movable base.

7. The system as recited in claim 1, wherein said movable base is movable in an X-direction and Y-direction, said Z-direction defined along said axis.

8. The system as recited in claim 1, wherein said movable base includes a mask support movable with respect to a housing.

9. The system as recited in claim 1, wherein said movable base includes a mask support spring connected and biased between the housing and the mask support.

10. A method of masking a component of a gas turbine engine comprising:

pressing a component into a mask supported on a movable base.

11. The method as recited in claim 10, further comprising:

permitting rotational movement of the movable bases.

12. The method as recited in claim 10, further comprising:

permitting tilting movement of the movable bases.

13. The method as recited in claim 10, further comprising:

pressing the component in a Z-direction; and

permitting movement of the movable bases in an X-direction and Y-direction.

14. The method as recited in claim 10, further comprising:

spraying the component with a lubricant solution.

15. The method as recited in claim 10, further comprising:

pressing the component with a semi-spherical insertion cup.