2026-09-19T13:48:50Zhttps://dspace.mit.edu/server/oai/requestoai:dspace.mit.edu:1721.1/1486152023-03-18T03:40:03Zcom_1721.1_7582com_1721.1_7581col_1721.1_131022
Spakovszky, Zoltán S.
Dowdle, Aidan Patrick
Massachusetts Institute of Technology. Department of Electrical Engineering and Computer Science
2023-03-17T18:14:30Z
2023-03-17T18:14:30Z
2022-05
2022-06-21T19:15:34.153Z
https://hdl.handle.net/1721.1/148615
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.
Ph.D.
Massachusetts Institute of Technology
In Copyright - Educational Use Permitted
Copyright MIT
http://rightsstatements.org/page/InC-EDU/1.0/
Design of a High Specific Power Electric Machine for Turboelectric Propulsion
Thesis
application/pdf
Doctoral
Doctor of Philosophy
Publication
unknown
unknown
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<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>
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