Abstract
A multi-stage turbocharger system analysis method has been presented for a hydrogen fueled internal combustion engine targeted for High altitude long endurance UAV (HALE UAV), of which cruising altitude is 60000 ft. To utilize an internal combustion engine as a propulsion system of a HALE UAV, proper inlet pressure boost system such as a series of turbochargers should be ready, which makes engine performance less sensitive to flight altitude. In this study, to boost rarefied intake air pressure up to 1.7 bar to avoid early ignition of hydrogen and to produce required power from engine, we used a boost system which consists of three-staged turbocharger accompanied by intercooler to reduce compressed air temperature. To analyze multi-stage turbocharger performance at the cruising altitude, we established an explicit one-dimensional analysis method by matching required power between compressors and turbines. Then adequate turbochargers were searched for from commercially available models based on performance analysis results. One-dimensional analysis was also applied from sea level to the cruising altitude to decide turbocharger operating lines were located within each turbocharger operating ranges.
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Recommended by Associate Editor Kyu Hong Kim
Young Seok Kang is a Senior Researcher at Korea Aerospace Research Institute. He received his Ph.D. from Seoul National University in 2007. His main research interests cover topics from axial compressor and turbine aerodynamic designs and optimizations to their performance assessments by CFD and experimental methods.
Byeung Jun Lim is a Senior Research at Korea Aerospace Research Institute. He received his Ph.D. from Korea Advanced Institute of Science Technology (KAIST) in 2014. His main research interests cover compressor instabilities, turbomachinery experiments, and aero propulsion system.
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Kang, Y.S., Lim, B.J. & Cha, B.J. Multi-stage turbocharger system analysis method for high altitude UAV engine. J Mech Sci Technol 31, 2803–2811 (2017). https://doi.org/10.1007/s12206-017-0523-4
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DOI: https://doi.org/10.1007/s12206-017-0523-4