# US 2020/0400037 A1 · Methods of cleaning a component within a turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2020/0400037 A1 - Document ID: US20200400037A1 - Status: Published application - Kind: A1 - Application number: 17/010,309 - Filed: 2020-09-02 - Published: 2020-12-24 - Earliest claimed: 2017-04-26 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Michael Robert Millhaem; Nicole Jessica Tibbetts; Byron Andrew Pritchard, JR.; Bernard Patrick Bewlay; Keith Anthony Lauria; Ambarish Jayant Kulkarni; Mark Rosenzweig; Martin Matthew Morra; Timothy Mark Sambor; Andrew Jenkins - Web page: https://patentgrep.com/patent/US20200400037A1 ## CPC - F01D 25/002: {Cleaning of turbomachines} - B08B 3/003: {Cleaning involving contact with foam} - B08B 3/08: the liquid having chemical or dissolving effect - B08B 3/14: Removing waste, e.g. labels, from cleaning liquid - B08B 9/00: Cleaning hollow articles by methods or apparatus specially adapted thereto - B08B 9/0326: {Using pulsations} - F01D 25/32: Collecting of condensation water; Drainage {; Removing solid particles} - F02C 7/222: {Fuel flow conduits, e.g. manifolds} - F23R 3/28: characterised by the fuel supply (burners F23D) - B64F 5/30: Cleaning aircraft - F05D 2220/32: in gas turbines - F05D 2220/36: specially adapted for the fan of turbofan engines - F05D 2230/70: Disassembly methods - F05D 2230/72: Maintenance - F23R 2900/00019: Repairing or maintaining combustion chamber liners or subparts - Y02P 70/50: Manufacturing or production processes characterised by the final manufactured product - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - B08B: CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - 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) - B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02P: CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS ## Abstract A method of cleaning a component within a turbine that includes disassembling the turbine engine to provide a flow path to an interior passageway of the component from an access point. The component has coked hydrocarbons formed thereon. The method further includes discharging a flow of cleaning solution towards the interior passageway from the access point, wherein the cleaning solution is configured to remove the coked hydrocarbons from the component. ## Claims ### Claim at position 1 -9. (canceled) ### Claim 10 A method of cleaning a component within a turbine engine, said method comprising: disassembling the turbine engine to provide a flow path to an interior passageway of the component from an access point in the turbine engine, wherein the component has coked hydrocarbons formed thereon; filling a volume of the interior passageway with an amount of cleaning solution, wherein the cleaning solution is configured to remove the coked hydrocarbons from the component; and holding the amount of cleaning solution within the interior passageway for a predetermined residence time. ### Claim 11 (depends on 10) The method in accordance with claim 10, wherein disassembling the turbine engine comprises disassembling a fan assembly of the turbine engine to define a first open end of a fan midshaft of the turbine engine, wherein the first open end defines the access point. ### Claim 12 (depends on 11) The method in accordance with claim 11, wherein the fan midshaft includes a second open end, said method further comprising sealing the second open end prior to discharging the flow of cleaning solution towards the interior passageway. ### Claim 13 (depends on 12) The method in accordance with claim 12, wherein sealing the second open end comprises: positioning a plug within the interior passageway of the component proximate the second open end, wherein the plug is insertable through the first open end of the fan midshaft when in a first operational mode; and actuating the plug into a second operational mode from the first operational mode, wherein the plug is configured to seal the second open end when in the second operational mode. ### Claim 14 (depends on 10) The method in accordance with claim 10, wherein filling a volume of the interior passageway comprises filling the volume with the cleaning solution including a foaming agent. ### Claim 15 (depends on 10) The method in accordance with claim 10, wherein holding the amount of cleaning solution comprises holding the amount of cleaning solution for the predetermined residence time defined within a range between about 30 minutes and about 8 hours. ### Claim 16 A method of cleaning a component within a turbine engine, said method comprising: disassembling the turbine engine to define an access point to the component, wherein the component has coked hydrocarbons formed thereon; and discharging a flow of cleaning solution towards the component from the access point, wherein the cleaning solution is configured to remove the coked hydrocarbons from the component, and wherein the cleaning solution includes at least one of citric acid or glycolic acid. ### Claim 17 (depends on 16) The method in accordance with claim 16, wherein disassembling the turbine engine comprises disassembling the turbine engine when the turbine engine is coupled to an airframe. ### Claim 18 (depends on 16) The method in accordance with claim 16, wherein disassembling the turbine engine comprises disassembling the turbine engine to provide access to a fuel nozzle of the turbine engine. ### Claim 19 (depends on 16) The method in accordance with claim 16, wherein discharging a flow of cleaning solution comprises discharging the flow of cleaning solution that further includes a foaming agent. ### Claim 20 (depends on 16) The method in accordance with claim 16 further comprising: disassembling a fuel manifold to define an inlet port within the fuel manifold, wherein the inlet port defines the access point; and discharging the flow of cleaning solution through the inlet port and towards the component.