Kurt Rouser: "Practical Challenges with Turboelectric Power Integration in Aircraft Applications"

Speaker Bio: Dr. Kurt Rouser is Associate Professor of Mechanical and Aerospace Engineering at Oklahoma State University (OSU). He holds a B.S. in Aeronautical Engineering from the US Air Force Academy (USAFA), an M.S. in Aviation Science from OSU and an M.S. in Aeronautical Engineering and Ph.D. in Mechanical Engineering from the Air Force Institute of Technology (AFIT). During 21 years on active duty in the Air Force, he served as Aerospace Propulsion Analyst at the National Air Intelligence Center in Ohio, Maintenance Engineer and Executive Officer for the Propulsion Directorate and KC-135 System Program Office at the Oklahoma City Air Logistics Center and Operations Officer for jet engine test and evaluation at Arnold Engineering Development Center in Tennessee. He served eight years on USAFA faculty in the Aeronautics Department and as Deputy Associate Dean for Educational Innovation. While on active duty, he also briefly served as an Adjunct Professor teaching Jet Engine Operation at OSU and Advanced Aircraft Systems at Southeastern OSU. He retired from the Air Force in 2016 and transitioned into his current position at OSU, teaching and researching aerospace propulsion and power. His current research areas include micro turbojets; solid, hybrid and liquid rockets; propellers and rocket-assisted take-off systems for unmanned aircraft, and turboelectric power system integration with manned and unmanned aircraft.

Abstract: This seminar presents a summary of research accomplished to characterize challenges associated with integrating turboelectric power systems in various aircraft applications, including manned and unmanned systems for conventional and vertical take-off and landing (VTOL). The primary motivation for hybrid gas-electric power systems is to optimize energy-dense hydrocarbon combustion with a power-dense electric powertrain; however, there are many practical issues with coupling the two power systems, as well as with propulsion and airframe integration. Experimental studies covered in this seminar include results from bench-testing of small 5-KW to 11-KW turboelectric systems with micro-turbojet engines, flight testing unmanned turboelectric aircraft in conventional and VTOL configurations, and ground testing a Cessna 172 modified with a 180-KW partial-turboelectric power system. Different methodologies are discussed for coupling electrical power generation components with gas turbine engine shaft power output, ranging up to 550-V systems. Observations include lessons in thermal management, level of hybridization, different power system architectures, and transient effects. The impact of these observations provides a basis for safe and effective integration of turboelectric power systems with aircraft. The seminar will also cover future work to reduce overall system weight and volume, as well as the potential to incorporate detonation combustion for improved efficiency.