This content is not included in your SAE MOBILUS subscription, or you are not logged in.
More Electric Architecture for Engine and Aircraft Fuel System
Technical Paper
2013-01-2080
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
The authors are currently developing the MEE (More Electric Engine) electric motor-driven fuel pump system for aircraft engines. The electric fuel system will contribute to the reduction of engine power extraction to drive the fuel pump; thus, an improvement in engine efficiency will be expected. In addition, the engine system reliability will be improved by introducing advanced electric architecture, and the reduction of hydraulic components, fuel tubes and fittings is effective to enhance the maintainability of the engine.
Although it is considered that the MEE electric fuel system will realize several benefits, there are technical challenges to introduce such new electric system into aircraft. One of the key technical challenges is to construct a redundant and simplified electric fuel system, because continuous operation of the fuel pump system is crucial for aircraft safety. The authors consider that integration of the aircraft fuel system and engine fuel system will provide a solution for the technical issue, and propose a concept of an integrated electric fuel system in this paper.
Recommended Content
Citation
Morioka, N. and Oyori, H., "More Electric Architecture for Engine and Aircraft Fuel System," SAE Technical Paper 2013-01-2080, 2013, https://doi.org/10.4271/2013-01-2080.Also In
References
- Newman, R., “The More Electric Engine Concept,” SAE Technical Paper 2004-01-3128, 2004, doi:10.4271/2004-01-3128.
- McLoughlin Adam, Rolls-Royce plc, “Engine Powerplant Electrical Systems”, More Electric Aircraft Forum, 2009
- Zähringer Christian, Stastny Karel, Ardey Sabine, MTU Aero Engines GmbH, “Towards the Powerhouse for More Electric Aircraft -Dedicated Engine Concepts”, ISABE-2009-1166
- Morioka N., Oyori H., Kakiuchi D., Ozawa K., “More Electric Engine Architecture for Aircraft Engine Application”, ASME Turbo Expo 2011, Vancouver, Canada, GT2011-46765
- Morioka, N. and Oyori, H., “Fuel Pump System Configuration for the More Electric Engine,” SAE Technical Paper 2011-01-2563, 2011, doi:10.4271/2011-01-2563.
- Morioka N., Oyori H., “Fuel System Design for the More Electric Engine”, ASME Turbo Expo 2012, Copenhagen, Denmark, GT2012-68374
- Oyori, H., Morioka, N., Seta, M., Shimomura, Y. et al., “A Motor Control Design for the More Electric Aero Engine Fuel System,” SAE Technical Paper 2011-01-2619, 2011, doi:10.4271/2011-01-2619.
- Bennett John William, Newcastle University, “Fault Tolerant Electromechanical Actuators for Aircraft”, Nov. 2010
- Atkinson Glynn J., Mecrow Barrie C., Jack Alan G., Atkinson David J., Sangha Parminder, and Benarous Maamar, “The Analysis of Losses in High-Power Fault-Tolerant Machines for Aerospace Applications”, IEEE Transactions on Industry Application, Vol.42, No.5, Sep/Oct 2006
- Chen Xiaoyuan, Deng Zhiquan, Peng Jingjing, Nanjing University of Aeronautics and Astronautics, “Fault Tolerant Switched Reluctance Machine for Fuel Pump Drive in Aircraft”, ICIEA 2009