{"id":{"repo_id":"mit","oai_identifier":"oai:dspace.mit.edu:1721.1/147320"},"canonical_url":"https://search.dev.ndltd.org/etd/mit/oai:dspace.mit.edu:1721.1/147320","repository":{"repo_id":"mit","name":"MIT","base_url":"https://dspace.mit.edu/oai/request"},"display":{"title":"Trade-Space Analysis of Liquid Hydrogen Propulsion Systems for Electrified Aircraft","abstract":"This thesis assesses the feasibility of turbo-, hybrid-, and fully-electric aircraft propulsion systems to enable more efficient air transport. A modular optimization framework was developed to quantify system performance for single-aisle transport aircraft with a mission similar to a Boeing 737 MAX 8. Various propulsion systems leveraging superconducting motors, boundary layer ingestion, high-temperature PEM fuel cells, and liquid hydrogen fuel were examined. Aviation turbine fuel (ATF) and liquid hydrogen were compared using the payload-fuel energy intensity (PFEI), defined as the fuel energy required per product of range and payload. For a given mission, it was found that a hydrogen-fueled fully-electric configuration required similar fuel energy compared to an ATF-burning turbo-fan propulsion system (PFEI = 5.0). Relative to these systems, a hydrogen-fueled turbo-fan had 14% lower PFEI, an ATF-burning turbo-electric propulsion system had 23% higher PFEI, a hydrogen-fueled turbo-electric propulsion system had 8% lower PFEI, and a hydrogen-fueled hybrid-electric had 3% lower PFEI for the same mission.","abstract_html":"This thesis assesses the feasibility of turbo-, hybrid-, and fully-electric aircraft propulsion systems to enable more efficient air transport. A modular optimization framework was developed to quantify system performance for single-aisle transport aircraft with a mission similar to a Boeing 737 MAX 8. Various propulsion systems leveraging superconducting motors, boundary layer ingestion, high-temperature PEM fuel cells, and liquid hydrogen fuel were examined. Aviation turbine fuel (ATF) and liquid hydrogen were compared using the payload-fuel energy intensity (PFEI), defined as the fuel energy required per product of range and payload. For a given mission, it was found that a hydrogen-fueled fully-electric configuration required similar fuel energy compared to an ATF-burning turbo-fan propulsion system (PFEI = 5.0). Relative to these systems, a hydrogen-fueled turbo-fan had 14% lower PFEI, an ATF-burning turbo-electric propulsion system had 23% higher PFEI, a hydrogen-fueled turbo-electric propulsion system had 8% lower PFEI, and a hydrogen-fueled hybrid-electric had 3% lower PFEI for the same mission.","abstract_has_math":false,"creators":["White, Andrew Scott"],"institution":"Massachusetts Institute of Technology","degree_name":"Master","degree_level":null,"degree_discipline":null,"degree_department":"Massachusetts Institute of Technology. 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A modular optimization framework was developed to quantify system performance for single-aisle transport aircraft with a mission similar to a Boeing 737 MAX 8. Various propulsion systems leveraging superconducting motors, boundary layer ingestion, high-temperature PEM fuel cells, and liquid hydrogen fuel were examined. Aviation turbine fuel (ATF) and liquid hydrogen were compared using the payload-fuel energy intensity (PFEI), defined as the fuel energy required per product of range and payload. For a given mission, it was found that a hydrogen-fueled fully-electric configuration required similar fuel energy compared to an ATF-burning turbo-fan propulsion system (PFEI = 5.0). Relative to these systems, a hydrogen-fueled turbo-fan had 14% lower PFEI, an ATF-burning turbo-electric propulsion system had 23% higher PFEI, a hydrogen-fueled turbo-electric propulsion system had 8% lower PFEI, and a hydrogen-fueled hybrid-electric had 3% lower PFEI for the same mission."]},{"key":"dc:description.degree","label":"Dc Description Degree","values":["S.M."]},{"key":"dc:title","label":"Title","values":["Trade-Space Analysis of Liquid Hydrogen Propulsion Systems for Electrified Aircraft"]}]}],"canonical_facts":{"dc:contributor.advisor":["Greitzer, Edward M."],"dc:contributor.department":["Massachusetts Institute of Technology. Department of Aeronautics and Astronautics"],"dc:creator":["White, Andrew Scott"],"dc:date.accessioned":["2023-01-19T18:45:16Z"],"dc:date.available":["2023-01-19T18:45:16Z"],"dc:date.issued":["2022-09"],"dc:description.abstract":["This thesis assesses the feasibility of turbo-, hybrid-, and fully-electric aircraft propulsion systems to enable more efficient air transport. A modular optimization framework was developed to quantify system performance for single-aisle transport aircraft with a mission similar to a Boeing 737 MAX 8. Various propulsion systems leveraging superconducting motors, boundary layer ingestion, high-temperature PEM fuel cells, and liquid hydrogen fuel were examined. Aviation turbine fuel (ATF) and liquid hydrogen were compared using the payload-fuel energy intensity (PFEI), defined as the fuel energy required per product of range and payload. For a given mission, it was found that a hydrogen-fueled fully-electric configuration required similar fuel energy compared to an ATF-burning turbo-fan propulsion system (PFEI = 5.0). Relative to these systems, a hydrogen-fueled turbo-fan had 14% lower PFEI, an ATF-burning turbo-electric propulsion system had 23% higher PFEI, a hydrogen-fueled turbo-electric propulsion system had 8% lower PFEI, and a hydrogen-fueled hybrid-electric had 3% lower PFEI for the same mission."],"dc:description.degree":["S.M."],"dc:identifier.uri":["https://hdl.handle.net/1721.1/147320"],"dc:publisher":["Massachusetts Institute of Technology"],"dc:rights":["In Copyright - Educational Use Permitted","Copyright MIT"],"dc:rights.uri":["http://rightsstatements.org/page/InC-EDU/1.0/"],"dc:title":["Trade-Space Analysis of Liquid Hydrogen Propulsion Systems for Electrified Aircraft"],"dc:type":["Thesis"],"thesis:degree_name":["Master","Master of Science in Aeronautics and Astronautics"]},"updated_at":"2026-07-22T22:21:27Z"}