Energy and exergy analysis at different hybridization factors for hybrid electric propulsion light utility helicopter engine
ENERGY, vol.189, 2019 (SCI-Expanded, Scopus)
- Publication Type: Article / Article
- Volume: 189
- Publication Date: 2019
- Doi Number: 10.1016/j.energy.2019.116105
- Journal Name: ENERGY
- Journal Indexes: Science Citation Index Expanded (SCI-EXPANDED), Scopus
- Keywords: Piston-prop, Helicopter, Aviation, Hybrid propulsion, Hybridization factor, Energy, Exergy, TURBOJET ENGINE, TURBOPROP ENGINE, EXERGOECONOMIC ANALYSIS, FUEL-ECONOMY, AIRCRAFT, SUSTAINABILITY, ASSESSMENTS, PERFORMANCE, VEHICLE, DESIGN
- Anadolu University Affiliated: No
Abstract
In this study, a parallel hybrid system using an electric motor and an internal combustion engine is designed for a light utility helicopter. Energy and exergy analyses were performed and evaluated for take-off phase of a Robinson R22 Beta II Light Utility Helicopter at various altitudes for different hybridization factors. The maximum energy efficiency and exergy efficiency were found to be as 16.03% and 11.86% respectively at sea level and hybridization factor was 0%. The lowest energy efficiency and exergy efficiency were 13.71% and 10.15 respectively while hybridization factor was 6% at 3000 m altitude. The highest loss exergy and exergy destructions were calculated to be 30.30 kW and 552.75 kW respectively where hybridization factor was 0% at sea level. Furthermore, the lowest loss exergy and exergy destruction value was 24.66 kW and 440.89 kW at 3000 m altitude and hybridization factor was 6%, respectively. (C) 2019 Elsevier Ltd. All rights reserved.