# US 9,039,490 B2 · Method of shaping an edge of an aerofoil > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 9,039,490 B2 - Document ID: US9039490B2 - Status: Granted - Kind: B2 - Application number: 13/479,881 - Filed: 2012-05-24 - Published: 2012-12-06 - Granted: 2015-05-26 - Earliest claimed: 2011-06-03 - Assignees: ROLLS-ROYCE plc - Applicants: John R. Kelly; Adam S. Ramsay; Satyaswaroop Nanda; Fiona M. Halliday - Inventors: John R. Kelly; Adam S. Ramsay; Satyaswaroop Nanda; Fiona M. Halliday - Web page: https://patentgrep.com/patent/US9039490B2 ## CPC - F01D 5/005: {Repairing methods or devices} - B24B 19/14: for grinding turbine blades, propeller blades or the like (using grinding belts B24B21/16) - F05D 2230/80: Repairing, retrofitting or upgrading methods - Y10T 29/49318: Repairing or disassembling - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - B24B: MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING (grinding of gear teeth B23F, of screw-threads B23G1/36; by electro-erosion B23H; abrasive or related blasting B24C; tools for grinding, buffing or sharpening B24D; polishing compositions C09G1/00; abrasives C09K3/14; electrolytic etching or polishing C25F3/00; grinding arrangements for use on assembled railway tracks E01B31/17); DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract An apparatus for shaping an edge of an aerofoil, the apparatus having first and second brushes and each brush having a plurality of bristles. A first motor rotates the first brush about a first axis and a second motor rotates the second brush about a second axis. The axes are arranged substantially parallel to the bristles of the respective brush. A support structure holds the first brush such that the first axis intersects a first surface of the edge of the aerofoil and holds the second brush such that the second axis intersects a second surface of the edge of the aerofoil. There are means to produce relative movement the first and second brushes and the aerofoil such that the first and second brushes move longitudinally along the edge of the aerofoil to shape the edge of the aerofoil. ## Claims ### Claim 1 A method of shaping an edge of an aerofoil, the method comprising:— a) providing a first brush and a second brush, each brush comprising a plurality of bristles extending substantially parallel to each other, b) rotating the first brush about a first axis and rotating the second brush about a second axis, the first axis being arranged substantially parallel to the bristles of the first brush and the second axis being arranged substantially parallel to the bristles of the second brush, c) arranging the first axis to intersect a first surface of an edge of an aerofoil and arranging the second axis to intersect a second surface of the edge of the aerofoil, d) moving the first brush such that the first brush contacts the first surface of the edge and moving the second brush such that the second brush contacts the second surface of the edge, e) producing relative movement between the first brush and the second brush and the aerofoil such that the first brush and the second brush move longitudinally along the edge of the aerofoil to shape the edge of the aerofoil. ### Claim 2 (depends on 1) A method as claimed in claim 1 comprising arranging the first axis and the second axis to intersect the first and second surfaces respectively at angle in the range of 30° to 75°. ### Claim 3 (depends on 2) A method as claimed in claim 2 comprising arranging the first axis and the second axis to intersect the first and second surfaces respectively at angle in the range of 55° to 75°. ### Claim 4 (depends on 3) A method as claimed in claim 3 comprising arranging the first axis and the second axis to intersect the first and second surfaces respectively at angle of 60°. ### Claim 5 (depends on 1) A method as claimed in claim 1 comprising varying the angle at which the first axis and the second axis intersects the first and second surfaces respectively. ### Claim 6 (depends on 1) A method as claimed in claim 1 wherein the bristles are selected from the group comprising alumina bristles and silicon carbide bristles. ### Claim 7 (depends on 1) A method as claimed in claim 1 comprising arranging the first axis and the second axis in a plane. ### Claim 8 (depends on 1) A method as claimed in claim 1 comprising arranging the first axis and the second axis in two parallel planes. ### Claim 9 (depends on 1) A method as claimed in claim 1 wherein the edge of the aerofoil is a leading edge. ### Claim 10 (depends on 1) A method as claimed in claim 1 wherein the aerofoil is worn, and the method further comprising reshaping the edge. ### Claim 11 (depends on 1) A method as claimed in claim 1 wherein the aerofoil is a gas turbine engine aeroloil. ### Claim 12 (depends on 11) A method as claimed in claim 11 wherein the gas turbine engine aerofoil is selected from the group comprising a fan blade, a fan outlet guide vane, a compressor blade and a compressor vane. ### Claim 13 (depends on 11) A method as claimed in claim 11 wherein the aerofoil is selected from the group comprising a blade on an integrally bladed disc, a blade mounted in a slot in the periphery of a rotor disc and a blade mounted in a slot in the periphery of a rotor drum.