This article introduces a novel full-electric aircraft propulsion designed based on the DEA compressor, named DEAThruster that is supplied by a PEMFC. The thruster designed and modeled in this study is a compact DEAThruster to operate in altitudes up to 15,000 m and in the subsonic/transonic region with a specific thrust around 8300 N s/kg. The results show the thruster can satisfy all expectations, and it can generate up to 8300 N s/kg specific thrust for flight conditions encompassing static condition at sea level up to flight Mach number 0.95 in altitude 15,000 m. The DEAThruster can potentially be a practical alternative for gas turbine propulsions in all aspects when all available options for full-electric propulsions are not competitive for conventional aircraft propulsions in performance, size, and weight.
ZaporozhetsOIsaienkoVSynyloK. Trends on current and forecasted aircraft hybrid electric architectures and their impact on environment. Energy2020; 211(1): 118814.
2.
BreljeBJJoaquimRMartinsRA. Electric, hybrid, and turboelectric fixed-wing aircraft: a review of concepts, models, and design approaches. Prog Aerosp Sci2019; 104: 1–19.
3.
AhmadBWilberforceTRamadanM, et al.Comprehensive investigation on hydrogen and fuel cell technology in the aviation and aerospace sectors. Renew Sustain Energ Rev2019; 106: 31–40.
4.
YeXAlSTsourdosA, et al.Review of hybrid electric powered aircraft, its conceptual design and energy management methodologies. Chin J Aeronautics2020; 1696: 432–450.
5.
WANGMZHANGSJohannesD, et al.Battery package design optimization for small electric aircraft. Chin J Aeronautics2020; 33(11): 2864–2876.
6.
RiboldiCEDGualdoniFTrainelliL. Preliminary weight sizing of light pure-electric and hybrid-electric aircraft. Transportation Res Proced2018; 29: 376–389.
7.
MaSWangSZhangC, et al.A method to improve the efficiency of an electric aircraft propulsion system. Energy2017; 140: 436–443.
8.
Moreno BravoGPraliyevNVeressA. Performance analysis of hybrid electric and distributed propulsion system applied on a light aircraft. Energy2021; 214: 118823.
9.
AryanaB. Preliminary study to raise axial flow compressors up to the context-awareness standards. Aerosp Sci Technol2008; 12: 515–523.
10.
AryanaB. Implementing DEA to create a novel type of compressor. Mater Sci Eng C2010; 30: 42–49.
11.
AryanaB. New version of DEA compressor for a novel hybrid gas turbine cycle: turboDEA. Energy2016; 111: 676–690.
12.
GuidaDMinutilloM. Design methodology for a PEM fuel cell power system in a more electrical aircraft. Appl Energ2017; 192: 446–456.
13.
PanZFAnLWenCY. Recent advances in fuel cells based propulsion systems for unmanned aerial vehicles. Appl Energ2019; 240: 473–485.
14.
González-EspasandínÓLeoTJRasoMA, et al.Direct methanol fuel cell (DMFC) and H2 proton exchange membrane fuel (PEMFC/H2) cell performance under atmospheric flight conditions of unmanned aerial vehicles. Renew Energ2019; 130: 762–773.
15.
ZhangXLiuLXuG. “Energy management strategy of Hybrid PEMFC PV battery propulsion system for low altitude UAVs”. In: 52nd AIAA/SAE/ASEE joint propulsion conference, Salt Lake City, UT, 25–27 July 2016.
16.
BrochuPA. Dielectric Elastomers for Actuation and Energy Harvesting, Los Angeles: PhD Thesis in Materials Science and Engineering. Los Angles: University of California, 2012.
RonPRoyKJosephJ. Richard Heydt, Qibing Pei, Seiki Chiba, “High-field deformation of elastomeric dielectrics for actuators”. Mater Sci Eng C2000; 11: 89–100.
19.
ChavanSLTalangeDB. Modeling and performance evaluation of PEM fuel cell by controlling its input parameters. Energy2017; 138: 437–445.
20.
AbdinZWebbCJGrayEM. PEM fuel cell model and simulation in Matlab-Simulink based on physical parameters. Energy2016; 116: 1131–1144.
21.
KadykTWinnefeldCHanke-RauschenbachR, et al.Analysis and design of fuel cell systems for aviation. Energies2018; 11: 375–411. DOI: 10.3390/en11020375.
22.
O’HayreRChaSWColellaW, et al.Fuel cell fundamentals. New York, NY, USA: JohnWiley & Sons, 2005.
23.
RezazadehASedighizadehMKarimiM. Proton exchange membrane fuel cell control using a predictive control based on neural network. Int J Computer Electr Eng2010; 2(1): 81-85.
24.
GimbaIDAbdulkareemASJimohA, et al.Theoretical energy and exergy analyses of proton exchange membrane fuel cell by computer simulation. J Appl Chem2016; 15: 2684919. DOI: 10.1155/2016/2684919.
25.
San MartínJIZamoraISan MartínJJ, et al.Performance analysis of a PEM fuel cell. RE&PQJ2010; 1(8): 943-951. DOI: 10.24084/repqj08.456.
26.
GambleEDwain TerrellPERichD. "NOZZLE SELECTION AND DESIGN CRITERIA. USA: AIAA, 2004.
27.
StittLE. Exhaust nozzles for propulsion systems with emphasis on supersonic cruise aircraft. USA: NASA Reference Publication, 1990, 1235.
28.
SUTTONGPOSCARB. Rocket propulsion elements. USA: John Wiley & Sons, 2001.
29.
MattinglyJD. Elements of gas turbine propulsion. Tata McGraw Hill Education. 6th reprint 2013.
30.
LiuHYanCZhaoY, et al.Analysis of pressure fluctuation in transonic cavity flows using modal decomposition. Aerosp Sci Technol2018; 77: 819–835.
31.
GuoGGongJZhangM. Numerical investigation on flow characteristics of low-speed flow over a cavity with small aspect ratio. Int J Mech Sci2020; 178: 105632.
32.
XUEXWangTZHANGT, et al.Mechanism of stall and surge in a centrifugal compressor with a variable vaned diffuser. Chin J Aeronautics2018; 31(6): 1222–1231.
33.
ChangzhengLISiqiXUZhiqiHU. Experimental study of surge and rotating stall occurring in highspeed multistage axial compressor. Proced Eng2015; 99: 1548–1560.
34.
RighiMPachidisVKönözsyL, et al.Three-dimensional through-flow modelling of axial flow compressor rotating stall and surge. Aerosp Sci Technol2018; 78: 271–279.
35.
MikhailovAEMikhailovaABAkhmetovYM, et al.Simulation of gas turbine engines considering the rotating stall in a compressor. Proced Eng2017; 176: 207–217.
36.
GnadtARSpethRLSabnisJS, et al.Technical and environmental assessment of all-electric 180-passenger commercial aircraft. Prog Aerosp Sci2019; 105: 1–30.
37.
VaryukhinANGordinMVS ZakharchenkoV, et al.Roadmap for the technological development of hybrid electric and full-electric propulsion systems of aircrafts. In: International conference on electrotechnical complexes and systems (ICOECS), Ufa, Russia, 21–25 Octomber 2019.
