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Investigation of the Effects on the Engine Drive Shaft to Increased Electrical Power in Aircraft Applications
Technical Paper
2017-01-2033
ISSN: 0148-7191, e-ISSN: 2688-3627
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English
Abstract
The amount of electrical power required for future aircraft is increasing significantly. In this paper, a comprehensive model of a drive shaft with multiple degrees of freedom was developed and integrated to detailed engine and electrical network models to study the impact of higher electrical loads. The overall system model is composed of the engine, shafts, gearbox, and the electric network. The Dynamic Dual Spool High Bypass JT9D engine was chosen for this study. The engine was modeled using NASA’s T-MATS (Toolbox for the Modeling and Analysis of Thermodynamic Systems) software. In the electrical side, one generator was connected to the Low Pressure (LP) shaft and the other to the High Pressure (HP) shaft. A modified model of the shafts between the engine and the accessory gearbox was created. Multiple different loads could be applied to the system through the gearbox, extracting power from the engine as well as accounting for power losses associated with friction between gears and other means. With the developed system model, the impact of high electrical power demand and step loads on the engine, shafts, and electrical network can be studied more thoroughly.
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Citation
Lam, M., Buterhaugh, C., Herrera, L., and Tsao, B., "Investigation of the Effects on the Engine Drive Shaft to Increased Electrical Power in Aircraft Applications," SAE Technical Paper 2017-01-2033, 2017, https://doi.org/10.4271/2017-01-2033.Data Sets - Support Documents
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References
- Ehsani , Mehrdad , Gao Yimin , and Emadi Ali Modern electric, hybrid electric, and fuel cell vehicles: fundamentals, theory, and design CRC press 2009
- Maldonado , Miguel A. et al. Power management and distribution system for a more-electric aircraft (MADMEL)-program status Energy Conversion Engineering Conference, 1996. IECEC 96., Proceedings of the 31st Intersociety 1 IEEE 1996
- Ahumada S., C. , Garvey , S. , Yang , T. , Wheeler , P. et al. Impact of Electric Loads on Engine Shaft Dynamics within More Electric Aircraft SAE Technical Paper 2015-01-2409 2015 10.4271/2015-01-2409
- Stone M. and Kilgore L. A. Transient Torques in Synchronous Machines Transactions of the American Institute of Electrical Engineers 52 4 945 952 Dec. 1933
- Kirschbaum H. S. Transient electrical torques of turbine generators during short circuits and synchronizing Electrical Engineering 64 2 65 70 Feb. 1945
- Ahumada S., C. , Garvey , S. , Yang T. , Wheeler P. , Morvan H. et al. The Importance of Load Pulse Timing in Aircraft Generation 2015 18th International Conference on Electrical Machines and Systems (ICEMS) Pattaya 2015 1339 1345
- Oyori , H. , Morioka , N. , Kakiuchi , D. , Shimomura , Y. et al. System Design for the More Electric Engine Incorporated in the Electrical Power Management for More Electric Aircraft SAE Technical Paper 2012-01-2169 2012 10.4271/2012-01-2169
- Oyori , H. , Morioka , N. , and Fukuda , T. Conceptual Study of Low-Pressure Spool-Generating Architecture for More Electric Aircraft SAE Technical Paper 2015-01-2408 2015 10.4271/2015-01-2408
- Armstrong M. , French M. , Phillips D. Engine Performance Optimization using Multi-Shaft Electric Machines for Intelligent Torque Management 2015 ISABE-2015-21285
- Champman J. , Lavelle T. , Litt J. , Guo T. A Process for the Creation of T-MATS Propulsion System Models from NPSS Data 2014 AIAA
- Rutledge M. Aircraft Gearbox Dynamics Subject to Electromechanical Actuator Regenerative Energy Flow Master Thesis Wright State University 2010
- MIL-Standard-704F Department of Defense Interface Standard. Aircraft Electric Power Characteristics including +/- 270 VDC