Detailed design of a high speed switched reluctance starter/generator for more/all electric aircraft

Abstract The basic concepts and advantages of more/all electric aircraft (M/AEA) are briefly addressed. The combined starter/generator (CS/G) system is introduced as a key technology to enable M/AEA. Some important performance requirements for CS/G system are obtained. Based on these requirements, a high speed switched reluctance machine (SRM) is designed to operate as a starter/generator. The entire design process is mainly divided into two stages: electromagnetic design and thermal design. In electromagnetic design stage, the electromagnetic structure and dimensions of the machine and the number of phase winding turns per pole are obtained; the topology and main technical details of the converter are briefly introduced as well. In thermal design stage, a liquid-cooling system is designed based on the thermal analysis of the machine. In the end, the performances of the designed SRM are basically verified by simulation. To get high performances, the exciting angles are optimized in two different operating modes respectively, and the optimized performances in the motoring mode are given as well.

[1]  大島 耕一編集,et al.  Fundamentals of Heat Transfer in Space , 2006 .

[2]  Timothy J. E. Miller,et al.  Switched Reluctance Motors and Their Control , 1993 .

[3]  D. Howe,et al.  IEE Colloquium on Electrical Machines and Systems for the More Electric Aircraft , 1999 .

[4]  J. Lienhard.  A heat transfer textbook , 1981 .

[5]  A. Chapman.  Fundamentals of heat transfer , 1987 .

[6]  C. Ferreira,et al.  Detailed design of a 30-kW switched reluctance starter/generator system for a gas turbine engine application , 1993, Conference Record of the 1993 IEEE Industry Applications Conference Twenty-Eighth IAS Annual Meeting.

[7]  M. D. Kankam,et al.  Potential starter/generator technologies for future aerospace applications , 1996, NAECON 1996.

[8]  J. A. Weimer.  The role of electric machines and drives in the more electric aircraft , 2003, IEEE International Electric Machines and Drives Conference, 2003. IEMDC'03..

[9]  J. F. Lindsay,et al.  Design Procedure for Switched Reluctance Motors , 1986, 1986 Annual Meeting Industry Applications Society.

[10]  Pragasen Pillay,et al.  THERMAL MODEL FOR A SWITCHED RELUCTANCE MOTOR OF TEFC DESIGN DURING STEADY AND TRANSIENT OPERATION , 1998 .

[11]  Nigel Schofield,et al.  Generator Operation of a Switched Reluctance Starter/Generator at Extended Speeds , 2009, IEEE Transactions on Vehicular Technology.

[12]  R. I. Jones,et al.  The More Electric Aircraft: the past and the future? , 1999 .

[13]  Andrea Cavagnino,et al.  A simplified thermal model for variable speed self cooled industrial induction motor , 2002 .

[14]  M. D. Kankam,et al.  Potential starter/generator technology for future aerospace application , 1996, NAECON 1996.

[15]  A. V. Radun,et al.  Two-channel switched reluctance starter/generator results , 1998 .

[16]  Klaus Hunecke,et al.  Jet Engines: Fundamentals of Theory, Design and Operation , 1997 .

[17]  Cary R. Spitzer.  The all-electric aircraft - In your future? , 1984 .

[18]  W. Pearson.  The more electric/all electric aircraft-a military fast jet perspective , 1998 .

[19]  Uwe Schäfer,et al.  An At-All Operating Points Highly Efficient PMSM for HEV , 2008 .

[20]  A. V. Radun,et al.  Two channel switched reluctance starter/generator results , 1997, Proceedings of APEC 97 - Applied Power Electronics Conference.

[21]  D. R. Turner,et al.  Lumped parameter thermal model for electrical machines of TEFC design , 1991 .

[22]  M.J.J. Cronin,et al.  The all-electric aircraft , 1990 .

[23]  J. Saari.  Thermal analysis of high-speed induction machines , 1998 .

[24]  R.E.J. Quigley.  More Electric Aircraft , 1993, Proceedings Eighth Annual Applied Power Electronics Conference and Exposition,.