Multi-stage turbocharger system analysis method for high altitude UAV engine

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.