# US 2023/0053554 A1 · Ice reduction mechanism for turbofan engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2023/0053554 A1 - Document ID: US20230053554A1 - Status: Published application - Kind: A1 - Application number: 17/408,770 - Filed: 2021-08-23 - Published: 2023-02-23 - Earliest claimed: 2021-08-23 - Assignees: General Electric Company - Applicants: General Electric Company - Inventors: Arthur William Sibbach; Allan George van de Wall; Sean Christopher Binion; Brian Lewis Devendorf; Brandon Wayne Miller - Web page: https://patentgrep.com/patent/US20230053554A1 ## CPC - F02C 7/047: Heating to prevent icing - B64D 33/02: of combustion air intakes - F01D 9/041: {using blades (F01D5/148 takes precedence)} - F01D 25/02: De-icing means for engines having icing phenomena - F02C 7/14: of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)} - F02K 3/06: with front fan - F04D 29/684: {by fluid injection} - B64D 2033/0233: {comprising de-icing means} - F05D 2240/12: Fluid guiding means, e.g. vanes - F05D 2240/121: related to the leading edge of a stator vane - F05D 2260/20: Heat transfer, e.g. cooling - F05D 2260/209: using vortex tubes - F05D 2260/213: by the provision of a heat exchanger within the cooling circuit - F05D 2260/961: by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape - F05D 2260/98: Lubrication - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - 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) - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for reducing ice buildup or ice formation on the inlet pre-swirl feature, the means in communication with the inlet pre-swirl feature. ## Claims ### Claim 1 A turbofan engine comprising: a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and a means for reducing ice buildup or ice formation on the inlet pre-swirl feature, the means in communication with the inlet pre-swirl feature. ### Claim 2 (depends on 1) The turbofan engine of claim 1, wherein the means for reducing ice buildup or ice formation comprises a heat source in thermal communication with the inlet pre-swirl feature. ### Claim 3 (depends on 2) The turbofan engine of claim 2, wherein the heat source is in communication with a leading edge of the inlet pre-swirl feature. ### Claim 4 (depends on 2) The turbofan engine of claim 2, wherein the heat source comprises an engine bleed airflow. ### Claim 5 (depends on 4) The turbofan engine of claim 4, wherein the heat source includes an air supply assembly comprising a supply duct in airflow communication with a high pressure air source and a leading edge of the inlet pre-swirl feature, the supply duct configured to receive and provide the engine bleed airflow to the leading edge of the inlet pre-swirl feature. ### Claim 6 (depends on 5) The turbofan engine of claim 5, wherein the air supply assembly further comprises a return duct in airflow communication with the supply duct and a portion of the turbomachine, the return duct configured to return the engine bleed airflow back to the turbomachine. ### Claim 7 (depends on 6) The turbofan engine of claim 6, wherein the air supply assembly further comprises a valve in communication with the supply duct, the valve transitionable between an open position in which the supply duct receives and provides the engine bleed airflow to the leading edge of the inlet pre-swirl feature, and a closed position in which the supply duct is not in airflow communication with the leading edge of the inlet pre-swirl feature. ### Claim 8 (depends on 6) The turbofan engine of claim 6, wherein the air supply assembly further comprises an intermediate duct in airflow communication with and disposed between the supply duct and the return duct, the intermediate duct in airflow communication with an upstream end of the nacelle and configured to receive and provide the engine bleed airflow to the upstream end of the nacelle. ### Claim 9 (depends on 5) The turbofan engine of claim 5, wherein the high pressure air source is the compressor section of the turbomachine. ### Claim 10 (depends on 2) The turbofan engine of claim 2, wherein the heat source comprises an electrical heating element disposed in thermal communication with a leading edge of the inlet pre-swirl feature. ### Claim 11 (depends on 10) The turbofan engine of claim 10, wherein the electrical heating element comprises a first element adjacent the leading edge of the inlet pre-swirl feature and a second element positioned aft of the first element within the inlet pre-swirl feature. ### Claim 12 (depends on 10) The turbofan engine of claim 10, wherein the heat source includes an electrical supply assembly comprising an electrical supply cable in electrical communication with the electrical heating element. ### Claim 13 (depends on 2) The turbofan engine of claim 2, wherein the heat source comprises an engine oil. ### Claim 14 (depends on 13) The turbofan engine of claim 13, wherein the heat source includes an oil supply assembly comprising an oil supply duct in flow communication with an oil source and a leading edge of the inlet pre-swirl feature, the oil supply duct configured to receive and provide the engine oil to the leading edge of the inlet pre-swirl feature. ### Claim 15 (depends on 14) The turbofan engine of claim 14, wherein the oil supply assembly further comprises an oil return duct in flow communication with the oil supply duct and the oil source, the oil return duct configured to return the engine oil back to the oil source. ### Claim 16 (depends on 15) The turbofan engine of claim 15, wherein the oil supply assembly further comprises a valve in communication with the oil supply duct, the valve transitionable between an open position in which the oil supply duct receives and provides the engine oil to the leading edge of the inlet pre-swirl feature, and a closed position in which the oil supply duct is not in flow communication with the leading edge of the inlet pre-swirl feature. ### Claim 17 (depends on 1) The turbofan engine of claim 1, wherein the means for reducing ice buildup or ice formation comprises a vibration assembly in mechanical communication with the inlet pre-swirl feature. ### Claim 18 (depends on 1) The turbofan engine of claim 1, wherein the means for reducing ice buildup or ice formation on the inlet pre-swirl feature in communication with the inlet pre-swirl feature comprises a piezoelectric transducer that vibrates the inlet pre-swirl feature. ### Claim 19 (depends on 1) The turbofan engine of claim 1, wherein the means for reducing ice buildup or ice formation on the inlet pre-swirl feature in communication with the inlet pre-swirl feature comprises an anti-ice coating covering the inlet pre-swirl feature. ### Claim 20 A turbofan engine comprising: a fan comprising a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine comprising a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan; an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle; and one or more of: a heat source in thermal communication with the inlet pre-swirl feature; a vibration assembly in mechanical communication with the inlet pre-swirl feature; a piezoelectric transducer that vibrates the inlet pre-swirl feature; and an anti-ice coating covering the inlet pre-swirl feature.