Design of a High Specific Power Electric Machine for Turboelectric Propulsion
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 pro...
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| Format: | Thesis |
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Massachusetts Institute of Technology
2023
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| Online Access: | https://hdl.handle.net/1721.1/148615 |
| _version_ | 1826194594138685440 |
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| author | Dowdle, Aidan Patrick |
| author2 | Spakovszky, Zoltán S. |
| author_facet | Spakovszky, Zoltán S. Dowdle, Aidan Patrick |
| author_sort | Dowdle, Aidan Patrick |
| collection | MIT |
| description | 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. |
| first_indexed | 2024-09-23T09:58:39Z |
| format | Thesis |
| id | mit-1721.1/148615 |
| institution | Massachusetts Institute of Technology |
| last_indexed | 2024-09-23T09:58:39Z |
| publishDate | 2023 |
| publisher | Massachusetts Institute of Technology |
| record_format | dspace |
| spelling | mit-1721.1/1486152023-03-18T03:40:03Z Design of a High Specific Power Electric Machine for Turboelectric Propulsion Dowdle, Aidan Patrick Spakovszky, Zoltán S. Massachusetts Institute of Technology. Department of Electrical Engineering and Computer Science 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. 2023-03-17T18:14:30Z 2023-03-17T18:14:30Z 2022-05 2022-06-21T19:15:34.153Z Thesis https://hdl.handle.net/1721.1/148615 In Copyright - Educational Use Permitted Copyright MIT http://rightsstatements.org/page/InC-EDU/1.0/ application/pdf Massachusetts Institute of Technology |
| spellingShingle | Dowdle, Aidan Patrick Design of a High Specific Power Electric Machine for Turboelectric Propulsion |
| title | Design of a High Specific Power Electric Machine for Turboelectric Propulsion |
| title_full | Design of a High Specific Power Electric Machine for Turboelectric Propulsion |
| title_fullStr | Design of a High Specific Power Electric Machine for Turboelectric Propulsion |
| title_full_unstemmed | Design of a High Specific Power Electric Machine for Turboelectric Propulsion |
| title_short | Design of a High Specific Power Electric Machine for Turboelectric Propulsion |
| title_sort | design of a high specific power electric machine for turboelectric propulsion |
| url | https://hdl.handle.net/1721.1/148615 |
| work_keys_str_mv | AT dowdleaidanpatrick designofahighspecificpowerelectricmachineforturboelectricpropulsion |