Development of a Turbocharger for Small Aviation Diesel Engines

Baker Engineering Inc. (BEI) proposes researching and developing a reliable sequential turbocharger system for a typical 2.0l class aviation compression-ignition engine with a maximum power of 180hp at sea level which is capable of providing 108hp at an altitude of 30,000-ft. With emphasis on durability and performance at altitude, research will be conducted on turbocharger construction, bearing systems, turbocharger control and monitoring, and advanced methods for surge prevention. High performance compressor wheel and housing designs and improved materials and designs for center and turbine housings will be applied. Phase I efforts will focus on research, design, analysis and manufacturing feasibility. The Phase I Option will include the manufacturing of a prototype sequential turbocharger system based on the design developed during the Phase I efforts. BEI will perform the majority of these tasks in-house and will subcontract with Bullseye Power to assist in the efforts. BEI extensive turbocharged engine development expertise, previous aviation turbocharger development experience (SBIR Phase III SBIR contract W56HZV-16-C-0213 and Phase II FA8650-16-C-2622), as well as hands-on knowledge of manufacturing prototype UAV turbochargers will assure success for this program.