# US 6,568,079 B2 · Methods for replacing combustor liner panels > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 6,568,079 B2 - Document ID: US6568079B2 - Status: Granted - Kind: B2 - Application number: 09/878,848 - Filed: 2001-06-11 - Published: 2002-12-12 - Granted: 2003-05-27 - Earliest claimed: 2001-06-11 - Assignees: General Electric Company - Inventors: Gilbert Farmer; David Bruce Patterson; Steven Allen Stiverson; James Michael Caldwell; Edward John Emilianowicz; Jeffrey Michael Martini - Web page: https://patentgrep.com/patent/US6568079B2 ## CPC - B23P 6/005: {using only replacement pieces of a particular form} - F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)} - F23R 3/08: between annular flame tube sections, e.g. flame tubes with telescopic sections - B23P 2700/13: Parts of turbine combustion chambers - F23R 2900/00005: Preventing fatigue failures or reducing mechanical stress in gas turbine components - F23R 2900/00016: Retrofitting in general, e.g. to respect new regulations on pollution - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - Y10T 29/49318: Repairing or disassembling - Y10T 29/49346: Rocket or jet device making - Y10T 29/49721: with disassembling - Y10T 29/4973: Replacing of defective part - Y10T 29/49737: Metallurgically attaching preform - B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q) - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION - Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION ## Abstract A replacement method facilitates replacing of a portion of a combustor liner within a gas turbine engine combustor in a cost-effective and reliable manner. The combustor includes a combustion zone that is defined by an inner and an outer liner. The inner and outer liners each include a series of panels and a plurality of nuggets formed by adjacent panels. The method includes the steps of cutting between an outer surface and an inner surface of at least one liner panel, removing at least one panel that is adjacent the area of the liner that was cut, and installing a replacement panel into the combustor for each panel that was removed from the combustor. ## Claims ### Claim 1 A method for replacing a gas turbine engine combustor liner panel, the combustor having a combustion zone formed by inner and outer liners, the inner and outer liners each including a series of panels and a plurality of cooling features, the cooling features formed by overhanging portions of the inner and outer liner panels, the cooling featuress between adjacent panels, said method comprising the steps of: removing at least one panel from the combustor; and installing at least one replacement panel into the combustor such that the series of panels are arranged in steps relative to one another. ### Claim 2 (depends on 1) A method in accordance with claim 1 wherein each panel includes an upstream end, a downstream end, and a body extending therebetween, said step of removing at least one panel further comprising the step of cutting radially through at least one panel body from an outer surface of the panel to an inner surface of the panel. ### Claim 3 (depends on 1) A method in accordance with claim 1 wherein said step of installing at least one replacement panel further comprises the step of welding a body of each replacement panel to a panel body secured within the combustor. ### Claim 4 (depends on 3) A method in accordance with claim 3 wherein said step of welding a body further comprises the step of using at least one of an EB welding process and a TIG welding process to secure the replacement panel within the combustor. ### Claim 5 (depends on 1) A method in accordance with claim 1 wherein each panel includes an inner surface and an outer surface, said method further comprising the step of applying thermal barrier coating material to the inner surface of each replacement panel attached within the combustor. ### Claim 6 A method for replacing a portion of a combustor liner within a gas turbine engine combustor, the combustor having a combustion zone formed by an inner and outer liner, the inner and outer liners each including a series of panels and a plurality of nuggets, the nuggets formed by adjacent panels, said method comprising the steps of: cutting between an outer surface and an inner surface of at least one liner panel; removing at least one panel adjacent an area of the liner cut; and installing a replacement panel into the combustor to replace each panel removed from the combustor. ### Claim 7 (depends on 6) A method in accordance with claim 6 wherein said step of cutting between an outer surface and an inner surface further comprises the step of cutting through a panel downstream from a nugget. ### Claim 8 (depends on 6) A method in accordance with claim 6 wherein said step of cutting between an outer surface and an inner surface further comprises the step of cutting through a panel body. ### Claim 9 (depends on 8) A method in accordance with claim 8 wherein said step of installing a replacement panel further comprises the step of welding each replacement panel to respective existing panels secured within the combustor. ### Claim 10 (depends on 9) A method in accordance with claim 9 wherein said step of welding each replacement panel further comprises the step of welding a body of each replacement panel to respective panel bodies of existing panels secured within the combustor. ### Claim 11 (depends on 6) A method in accordance with claim 6 further comprising the step of applying thermal barrier coating material to the inner surface of each replacement panel attached within the combustor. ### Claim 12 A method for replacing at least one deteriorated combustor liner panel within a gas turbine engine combustor including an annular liner including a multinugget region, a mulithole region, and an inner surface, the multihole region extending downstream from the multinugget region, said method comprising the steps of: cutting through at least one of the liner multinugget region and the liner multihole region downstream from the at least one deteriorated combustor liner panel to be replaced; removing the at least one deteriorated combustor liner panel from the combustor; and welding at least one replacement panel to at least one existing panel within the combustor for each deteriorated combustor liner panel removed. ### Claim 13 (depends on 12) A method in accordance with claim 12 wherein said step of welding at least one replacement liner further comprises the step of using at least one of an EB welding process and a TIG welding process to secure each replacement panel to each respective existing panel within the combustor. ### Claim 14 (depends on 13) A method in accordance with claim 13 wherein each panel includes an upstream end, a downstream end, and a body extending therebetween, said step of cutting through at least one of the liner multinugget region and the liner multihole region further comprises the step of cutting through a panel body within the liner multinugget region. ### Claim 15 (depends on 14) A method in accordance with claim 14 wherein each panel includes an upstream end, a downstream end, and a body extending therebetween, said step of cutting through at least one of the liner multinugget region and the liner multihole region further comprises the step of cutting through a panel body within the liner multihole region. ### Claim 16 (depends on 14) A method in accordance with claim 14 further comprising the step of applying thermal barrier material to the inner surface of each replacement panel welded into the combustor.