METHOD OF LASER PROCESSING A COMPONENT WITHIN AN ASSEMBLED APPARATUS USING A BOROSCOPE

• US 20170326685A1
• Filed: 07/20/2017
• Published: 11/16/2017
• Est. Priority Date: 09/19/2012
• Status: Active Grant

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: KELL, James, GRAFTON-REED, Clive, AXINTE, Dragos
• Granted Patent: US 10,207,367 B2
• Time in Patent Office: Days
• CPC Class Codes: B08B 7/0042 by laser
• CPC Class Codes: B23K 2101/001 Turbines
• CPC Class Codes: B23K 2101/34 Coated articles , e.g. plated or painted; Surface treated articles
• CPC Class Codes: B23K 2103/02 Iron or ferrous alloys
• CPC Class Codes: B23K 2103/08 Non-ferrous metals or alloys
• CPC Class Codes: B23K 2103/26 Alloys of Nickel and Cobalt and Chromium
• CPC Class Codes: B23K 26/0006 taking account of the properties of the material involved B23K26/32, B23K26/40 take precedence
• CPC Class Codes: B23K 26/0096 Portable laser equipment, e.g. hand-held laser apparatus surgical laser instruments A61B18/20, Dental Lasers A61C1/0046, Hand-held laser dental apparatus for curing resins A61C19/004
• CPC Class Codes: B23K 26/064 by means of optical elements, e.g. lenses, mirrors or prisms
• CPC Class Codes: B23K 26/08 Devices involving relative movement between laser beam and workpiece
• CPC Class Codes: B23K 26/211 with interposition of special material to facilitate connection of the parts
• CPC Class Codes: B23K 26/32 taking account of the properties of the material involved
• CPC Class Codes: B23K 26/342 Build-up welding
• CPC Class Codes: B23K 26/352 for surface treatment
• CPC Class Codes: B23K 35/0244 Powders, particles or spheres; Preforms made therefrom
• CPC Class Codes: B23K 35/3033 Ni as the principal constituent
• CPC Class Codes: B23K 35/3046 Co as the principal constituent
• CPC Class Codes: B23K 35/3053 Fe as the principal constituent
• CPC Class Codes: B23K 35/365 Selection of non-metallic compositions of coating materials either alone or conjoint with selection of soldering or welding materials
• CPC Class Codes: B23P 6/002 Repairing turbine components, e.g. moving or stationary blades, rotors, B23P6/045 takes precedence
• CPC Class Codes: G02B 23/2423 : of the distal end
• CPC Class Codes: G02B 26/101 : with both horizontal and vertical deflecting means, e.g. raster or XY scanners colour television using laser beams scanning a display screen H04N9/3129

Abstract

A method of laser processing a component within an assembled apparatus using a boroscope, which includes a working head having first and second ends. A first optical fibre extends through the boroscope to a position between the first and second ends. A second optical fibre extends through the boroscope to the second end. A laser optical fibre extends through the boroscope. At least one lens is arranged between the first and second ends of the working head and a mirror is gimballed to the second end. The laser optical fibre directs laser light transmitted through the laser optical fibre onto the lens and then onto the mirror. A first LED is arranged at a position between the first and second ends of the working head and a second LED is arranged at the second end and an actuator device adjust the position of the mirror.

Claims

1. A method of laser processing a component within an assembled apparatus, the apparatus comprising a casing enclosing the component, the casing having at least one aperture extending there-through, the method comprising:

a) inserting a boroscope through the aperture, the boroscope comprising a working head, the working head having a first end and a second end, a first optical fiber extending through the boroscope to a position between the first end and the second end of the working head, a second optical fiber extending through the boroscope to the second end of the working head, a laser optical fiber extending through the boroscope, a mirror adjustably mounted on the working head, the laser optical fiber being arranged to direct laser light transmitted through the laser optical fiber onto the mirror on the working head, a first light source arranged at a position between the first end and the second end of the working head, a second light source arranged at the second end of the working head and an actuator device to adjust the position of the mirror,

b) viewing the assembled apparatus within the casing using the second optical fiber,

c) viewing the assembled apparatus within the casing using the second optical fiber while moving the working head of the boroscope to the component,

d) transmitting a laser beam through the laser optical fiber to the mirror,

e) reflecting the laser beam off the mirror onto a surface of the component to process the surface of the component, and

f) viewing the surface of the component and the laser beam with the first optical fiber to monitor the processing of the surface of the component.

2. The method as claimed in claim 1 wherein step e) comprises adjusting the position of the mirror to move the laser beam over the surface of the component.

3. The method as claimed in claim 1 wherein step e) comprises cleaning the surface of the component.

4. The method as claimed in claim 1 wherein the boroscope comprises a pipe extending through the boroscope to a position between the first and second ends of the working head and a device is arranged to supply powder material through the pipe, and step e) comprises supplying a powder material through the pipe onto the surface of the component and melting the powder material with the laser beam.

5. The method as claimed in claim 4 wherein step e) comprises supplying a welding material to weld the component, to repair a crack in the component, to weld the component to another component or to build up a worn portion of the component.

6. The method as claimed in claim 4 wherein step e) comprises supplying a coating material to provide a coating on the component or to repair a coating on the component.

7. The method as claimed in claim 1 wherein the assembled apparatus comprises a gas turbine engine.

8. The method as claimed in claim 7 wherein the component is selected from the group consisting of a compressor blade, a compressor vane, a turbine blade and a turbine vane.