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aerospace Article Modeling and Investigation of a Turboprop Hybrid Electric Propulsion System Maria Cristina Cameretti 1,† , Andrea Del Pizzo 2,†, Luigi Pio Di Noia 2,* , Michele Ferrara 2,† and Ciro Pascarella 3,† 1 2 3 * Correspondence: luigipio.dinoia@unina.it † These authors contributed equally to this work. Received: 25 September 2018; Accepted: 17 November 2018; Published: 21 November 2018 Department of Industrial Engineering, University of Naples “Federico II”, Via Claudio 21, 80125 Naples, Italy; mc.cameretti@unina.it Department of Electrical Engineering and Information Technology, University of Naples “Federico II”, Via Claudio 21, 80125 Naples, Italy; andrea.delpizzo@unina.it (A.D.P.); michele.ferrara25@gmail.com (M.F.) Centro Italiano Ricerca Aerospaziale, Via Maiorise, 81043 Capua, Italy; c.pascarella@cira.it Abstract: Hybrid electric propulsion in the aviation field is becoming an effective alternative propulsion technology with potential advantages, including fuel savings, lower pollution, and reduced noise emission. On the one hand, the aeroengine manufacturers are working to improve fuel consumption and reduce pollutant emissions with new combustion systems; on the other hand, much attention is given to reducing the weight of the batteries increasing the energy density. Hybrid electric propulsion systems (HEPS) can take advantage of the synergy between two technologies by utilizing both internal combustion engines (ICEs) and electric motors (EMs) together, each operating at their respective optimum conditions. In the present work, some numerical investigations were carried out by using a zero-dimensional code able to simulate the flight mission of a turboprop aircraft, comparing fuel consumption and pollutant emissions of the original engine with other two smaller gas turbines working in hybrid configuration. An algorithm has been implemented to calculate the weight of the batteries for the different configurations examined, evaluating the feasibility of the hybrid propulsion system in terms of number of non-revenue passengers. Keywords: hybrid propulsion; gas turbine; modeling; propeller engine 1. Introduction The aviation industry is responsible for 12% of the total transportation impact of CO2 while awareness, for decreasing the total carbon footprint, is rising [1]. Both the aerospace and the automotive industry are facing an increasing pressure from society to make the transportation sector more sustainable. The Advisory Council for Aeronautics Research in Europe (ACARE) imposes, in the Vision 2020, an 80% and 50% reduction in NOx and CO2, respectively. The integrated performance is analyzed in terms of potential fuel reduction and vehicular efficiency in comparison to a suitable projected conventional aircraft employing only the turboprop target in year 2035 [2,3]. Therefore, more and more interest is turned toward hybrid propulsion systems in the aviation field too. On the basis of the hybrid electric aircraft configuration considered, thrust can be provided via a combination of turbine and electrical motor, or, only via the electrical motors. The electric engine could be used throughout the entire flight or in specific phases of the flight plan where the power demand is higher, or near urban areas, to reduce pollutant emission. In the present work, a hybrid configuration is studied for a regional aircraft turboprop engine, similar to ATR42-300. A parallel propulsion system, composed of a gas turbine and an electric motor Aerospace 2018, 5, 123; doi:10.3390/aerospace5040123 www.mdpi.com/journal/aerospacePDF Image | Turboprop Hybrid Electric Propulsion System
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