This content is not included in your SAE MOBILUS subscription, or you are not logged in.
A Detailed Power Inverter Design for a 250 kW Switched Reluctance Aircraft Engine Starter/Generator
ISSN: 0148-7191, e-ISSN: 2688-3627
Published April 01, 1993 by SAE International in United States
Annotation ability available
The design results for a 250 kW switched reluctance aircraft engine starter/generator system power inverter are presented. The starter/generator employs a single switched reluctance machine and a generating system architecture that produces two separate 270 Vdc buses from that single switched reluctance machine. The machine has six phases with three of the phases connected to one inverter supplying 125 kW to one 270 Vdc bus while the other three phases are connected to a second inverter supplying 125kW to the other 270 Vdc bus. Each bus has its own EM1 filter and control in addition to its own inverter. Two types of inverters have been developed, one type employs MOS Controlled Thyristors (MCTs) for the controlled switches and the other type employs Insulated Gate Bipolar Transistors (IGBTs). High-current 500 A peak turn-off MCT modules were specifically developed for the MCT inverters. Two of these modules are placed in parallel to form the required 1000 A switches. Safe operating area issues and special considerations related to employing the MCT switches are described. The IGBT inverters use two commercial 400 A 600 V IGBT modules for each switch. The link capacitor bank for each inverter employs multilayer ceramic capacitors to meet the starter/generators temperature requirements. These same multilayer ceramic capacitors are also used in the EMI filters. Performance predictions and results for both inverters are presented.
CitationRadun, A. and Richter, E., "A Detailed Power Inverter Design for a 250 kW Switched Reluctance Aircraft Engine Starter/Generator," SAE Technical Paper 931388, 1993, https://doi.org/10.4271/931388.
- Richter, E. Application Considerations for Integral Gas Turbine Starter/Generator Revisited SAE Paper 892252 Aerospace Technology Conference and Exposition Anaheim, CA Sept 1989 and Aerospace Atlantic, Dayton, OH 1990
- Richter, E. Switched Reluctance Machines For High Performance Operation In A Harsh Environment, A Review Paper invited paper at the International Conference on Electrical Machines OCEM) 90 Boston, MA 1990
- Stephens, C. M. Fault Detection And Management System For Fault Tolerant Switched Reluctance Motor Drives Conf. Record IEEE Industry Applications Society Annual Meeting Sept. 1989 574 578
- MaMinn S. R. Jones, W. D. A Very High Speed Switched Reluctance Starter-Generator For Aircraft Engine Applications Proc. NAECON 89 Dayton, OH May 22-26 1989
- MacMinn S. R. Sember, J. W. Control Of A Switched Reluctance Aircraft Engine Starter-Generator Over A Wide Speed Range Proc. IECEC-89 Washington, DC Aug. 6-11 1989
- Radun, A. Rulison, J. Sanza, P. Switched Reluctance StarterIGenerator SAE Aerotech 92 Oct. 1992 Anaheim, CA
- Radun, A. V. High Power Density Switched Reluctance Motor Drive For Aerospace Applications IEEE Trans. In Ind. Appl. 28 1 113 119 Jan./Feb. 1992
- Cameron D.E. Lang, J.H. The Control of High Speed Variable Reluctance Generators In Electric Power Systems Proc. APEC 92 Boston, MA
- Radun, A. V. Jones, D. W. Rulison, J. R. Stephens, C. M. A High Power Density Switched Reluctance Motor Proc. PCIM fall 92 Universal City, CA
- Temple V. Watrous, D Development of P-MCT Module For Air Force PRDA-89-05-PMRS Final Contract Report Dec 18 1992
- Temple V. Watrous, D Harris MOS Controlled Thyristor User’s Guide Harris Application Note 1992
- Radun A.V. Rulison, J.R. An Alternative Low-Cost Current-Sensing Scheme For High-Current Power Electronics Circuits Proc. IAS Annual Meeting Oct 1990