Method for repairing an abradable coating of a compressor of a gas turbine

Patent metadata

Field	Value
Publication number	US-9403244-B2
Application number	US-201214368685-A
Country	US
Kind code	B2
Filing date	Dec 27, 2012
Priority date	Dec 28, 2011
Publication date	Aug 2, 2016
Grant date	Aug 2, 2016

Abstract

The present invention relates to a method for repairing an abradable coating of a compressor of a gas turbine, where a worn abradable coating is repaired, where an analysis and/or selection of areas of the abradable coating to be repaired is conducted by means of a boroscope in the non-removed state of the gas turbine, where a tool is passed through at least one boroscope aperture of the gas turbine to the area to be repaired and the worn abradable coating is at least partially removed, where the removed material is extracted, where the area of the abradable coating to be repaired is cleaned and/or prepared for application of a repair medium, where a hardenable aluminum oxide-based repair medium is applied to the area to be repaired by means of a type of airbrush and then hardened, and where the area provided with the repair medium is subsequently mechanically treated.

First claim

What is claimed is:

1. A method for repairing an abradable coating of a compressor of a gas turbine, comprising:
performing at least one chosen from conducting an analysis and selecting an area of the abradable coating to be repaired with a borescope while the gas turbine is still installed in an operating position,
passing a tool through at least one borescope aperture of the gas turbine to the area of the abradable coating to be repaired and at least partially removing the worn abradable coating,
extracting the removed worn abradable coating,
performing at least one chosen from cleaning and preparing the area of the abradable coating to be repaired for application of a repair medium that is hardenable,
providing that the at least one borescope aperture has an aperture central axis and that the at least one borescope aperture engages an exterior surface of the tool to prevent movement of the tool in a direction perpendicular to the aperture central axis while permitting rotation of the tool around the aperture central axis;
applying the repair medium to the area to be repaired with an airbrush including a nozzle having a nozzle center axis fixed at an angle to a longitudinal axis of the tool, the nozzle supplying a jet of air and repair medium along the nozzle center axis at the fixed angle to the longitudinal axis such that a direction of the jet with respect to the gas turbine is selectively altered and controlled by rotating the tool around the longitudinal axis, thereby increasing an area covered by the jet with respect to the gas turbine by the rotating the tool around the longitudinal axis;
providing that the area of the abradable coating to be repaired is on a rotor of the gas turbine and rotating the rotor of the gas turbine to generate a relative circumferential movement between the tool and the area of the abradable coating to be repaired to apply the repair medium;
hardening the repair medium;
wherein the repair medium is a mixture of aluminum oxide and a thinner.

2. The method of claim 1 , and further comprising applying the repair medium in a plurality of layers.

3. The method of claim 1 , and further comprising using a self-hardening or heat curable repair medium.

4. The method of claim 1 , and further comprising conducting the method under visual control.

5. The method of claim 1 , and further comprising cleaning the area of the abradable coating to be repaired by applying a cleaning fluid and subsequently drying the area of the abradable coating to be repaired.

6. The method of claim 1 , and further comprising rotating the rotor to position the area of the abradable coating to be repaired at a top portion of the rotor when an engine axis of the gas turbine is arranged horizontally.

7. The method of claim 1 , and further comprising removing the worn abradable coating with a micro-cutter and an extraction device.

8. The method of claim 1 , wherein the at least one borescope aperture includes a guide bushing attached to the gas turbine, the guide bushing including an interior surface engaging the exterior surface of the tool to prevent movement of the tool in a direction perpendicular to the aperture central axis while permitting rotation of the tool around the aperture central axis.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Rautenberg Joachim
• Duprè Juergen
• Uhlmann Eckart
• Van Duikeren Bart

Classifications

• B05B13/06

  specially designed for treating the inside of hollow bodies (spray heads B05B1/00 - B05B7/00; {devices for covering leaks in pipes or hoses, e.g. hose-menders, from inside the pipe F16L55/162; sprayed layers of rubber or plastics for internal protection of pipes or pipe fittings against corrosion or incrustation F16L58/1027}) · CPC title

• F05D2230/80

  Repairing, retrofitting or upgrading methods · CPC title

• F05B2230/90

  Coating; Surface treatment · CPC title

• F01D21/003

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title