{"id":{"repo_id":"mit","oai_identifier":"oai:dspace.mit.edu:1721.1/148615"},"canonical_url":"https://search.dev.ndltd.org/etd/mit/oai:dspace.mit.edu:1721.1/148615","repository":{"repo_id":"mit","name":"MIT","base_url":"https://dspace.mit.edu/oai/request"},"display":{"title":"Design of a High Specific Power Electric Machine for Turboelectric Propulsion","abstract":"The benefits of turboelectric propulsion for aviation, in which a gas generator core electrically drives motor-powered propulsors, are limited by the mass and losses of the electric components introduced into the drivetrain. These propulsion systems are predicted to result in a 15\\% fuel savings provided that megawatt-class electrical machines (EMs) and power electronics (PEs) are available with power-to-mass ratios exceeding 13 kW/kg and 16 kW/kg, respectively. This thesis proposes an integrated prime mover concept enabled by the material choices and cooling technology available today. In this concept, an outer rotor, tooth-and-slot Halbach array is integrated with the low pressure compressor of a low fan pressure ratio aeroengine. The specific power of the integrated compressor generator is estimated to be 14.8 kW/kg, exceeding the NASA 2030 goal for aviation applications of 13 kW/kg for a standalone electric machine for aviation applications. Relative to a standalone, optimized electrical machine, co-optimization of the EM, PEs, thermal management system, and turbomachine rim suggests a 38\\% increase in system specific power. Based on these findings and supported by 2D and 3D finite element analysis, a 19.7 kW/kg, megawatt-class, air-cooled tooth-and-slot Halbach array electrical machine demonstrator is conceived. A detailed design study together with risk mitigation experiments of key components are carried out, setting the stage for megawatt-class, high power density, and high efficiency electrical machines for aerospace applications.","abstract_html":"The benefits of turboelectric propulsion for aviation, in which a gas generator core electrically drives motor-powered propulsors, are limited by the mass and losses of the electric components introduced into the drivetrain. These propulsion systems are predicted to result in a 15\\% fuel savings provided that megawatt-class electrical machines (EMs) and power electronics (PEs) are available with power-to-mass ratios exceeding 13 kW/kg and 16 kW/kg, respectively. This thesis proposes an integrated prime mover concept enabled by the material choices and cooling technology available today. In this concept, an outer rotor, tooth-and-slot Halbach array is integrated with the low pressure compressor of a low fan pressure ratio aeroengine. The specific power of the integrated compressor generator is estimated to be 14.8 kW/kg, exceeding the NASA 2030 goal for aviation applications of 13 kW/kg for a standalone electric machine for aviation applications. Relative to a standalone, optimized electrical machine, co-optimization of the EM, PEs, thermal management system, and turbomachine rim suggests a 38\\% increase in system specific power. Based on these findings and supported by 2D and 3D finite element analysis, a 19.7 kW/kg, megawatt-class, air-cooled tooth-and-slot Halbach array electrical machine demonstrator is conceived. A detailed design study together with risk mitigation experiments of key components are carried out, setting the stage for megawatt-class, high power density, and high efficiency electrical machines for aerospace applications.","abstract_has_math":false,"creators":["Dowdle, Aidan Patrick"],"institution":"Massachusetts Institute of Technology","degree_name":"Doctoral","degree_level":null,"degree_discipline":null,"degree_department":"Massachusetts Institute of Technology. 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These propulsion systems are predicted to result in a 15\\% fuel savings provided that megawatt-class electrical machines (EMs) and power electronics (PEs) are available with power-to-mass ratios exceeding 13 kW/kg and 16 kW/kg, respectively. This thesis proposes an integrated prime mover concept enabled by the material choices and cooling technology available today. In this concept, an outer rotor, tooth-and-slot Halbach array is integrated with the low pressure compressor of a low fan pressure ratio aeroengine. The specific power of the integrated compressor generator is estimated to be 14.8 kW/kg, exceeding the NASA 2030 goal for aviation applications of 13 kW/kg for a standalone electric machine for aviation applications. Relative to a standalone, optimized electrical machine, co-optimization of the EM, PEs, thermal management system, and turbomachine rim suggests a 38\\% increase in system specific power. Based on these findings and supported by 2D and 3D finite element analysis, a 19.7 kW/kg, megawatt-class, air-cooled tooth-and-slot Halbach array electrical machine demonstrator is conceived. A detailed design study together with risk mitigation experiments of key components are carried out, setting the stage for megawatt-class, high power density, and high efficiency electrical machines for aerospace applications."]},{"key":"dc:description.degree","label":"Dc Description Degree","values":["Ph.D."]},{"key":"dc:title","label":"Title","values":["Design of a High Specific Power Electric Machine for Turboelectric Propulsion"]}]}],"canonical_facts":{"dc:contributor.advisor":["Spakovszky, Zoltán S."],"dc:contributor.department":["Massachusetts Institute of Technology. Department of Electrical Engineering and Computer Science"],"dc:creator":["Dowdle, Aidan Patrick"],"dc:date.accessioned":["2023-03-17T18:14:30Z"],"dc:date.available":["2023-03-17T18:14:30Z"],"dc:date.issued":["2022-05"],"dc:description.abstract":["The benefits of turboelectric propulsion for aviation, in which a gas generator core electrically drives motor-powered propulsors, are limited by the mass and losses of the electric components introduced into the drivetrain. These propulsion systems are predicted to result in a 15\\% fuel savings provided that megawatt-class electrical machines (EMs) and power electronics (PEs) are available with power-to-mass ratios exceeding 13 kW/kg and 16 kW/kg, respectively. This thesis proposes an integrated prime mover concept enabled by the material choices and cooling technology available today. In this concept, an outer rotor, tooth-and-slot Halbach array is integrated with the low pressure compressor of a low fan pressure ratio aeroengine. The specific power of the integrated compressor generator is estimated to be 14.8 kW/kg, exceeding the NASA 2030 goal for aviation applications of 13 kW/kg for a standalone electric machine for aviation applications. Relative to a standalone, optimized electrical machine, co-optimization of the EM, PEs, thermal management system, and turbomachine rim suggests a 38\\% increase in system specific power. Based on these findings and supported by 2D and 3D finite element analysis, a 19.7 kW/kg, megawatt-class, air-cooled tooth-and-slot Halbach array electrical machine demonstrator is conceived. A detailed design study together with risk mitigation experiments of key components are carried out, setting the stage for megawatt-class, high power density, and high efficiency electrical machines for aerospace applications."],"dc:description.degree":["Ph.D."],"dc:identifier.uri":["https://hdl.handle.net/1721.1/148615"],"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":["Design of a High Specific Power Electric Machine for Turboelectric Propulsion"],"dc:type":["Thesis"],"thesis:degree_name":["Doctoral","Doctor of Philosophy"]},"updated_at":"2026-07-22T22:21:08Z"}