Full-electric, hybrid and turbo-electric technologies for future aircraft propulsion systems

• Autorzy: Łukasik B. , Wiśniowski W.

Identyfikatory

DOI

10.5604/12314005.1217240

• Języki publikacji: EN

Abstrakty

EN

Recently a huge progress in the field of electrical machines makes them more available for aviation. Assuming a big leap forward of electric technology in the near future, many research institutes around the World examine a revolutionary propulsion system which employs electrical machines. This idea can be a perfect response to a drastically growing air traffic and its demands about emission and fuel consumption reduction. There are already manufactured full electric, ultralight airplanes, which show that the technology is promising and future-proof. What is more it seems to be a key enabler for the development of the other technology that will influence the future of aircraft design and will allow introducing completely new airplane architectures. That is why Institute of Aviation in collaboration with The Ohio State University conducts investigation and analysis on feasibility of using such systems for aircraft propulsion. For this task a completely new tool based on Numerical Propulsion System Simulation (NPSS) environment is being developed. It will enable to analyse the electric devices conjugated with turbine engine as a whole propulsion system in the matter of its performance characteristics. The purpose of this paper is to present some of the most promising ideas and already accomplished analysis of different kinds of architectures. The analysis and optimization of the system, as well as cost effectiveness will be presented.

Słowa kluczowe

EN

full electric; turbo-electric; hybrid systems; distributed propulsion systems

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2016
• Tom: Vol. 23, No. 4
• Strony: 305--310
• Opis fizyczny: Bibliogr. 6 poz., rys.

Twórcy

autor

Łukasik B.

• Institute of Aviation Krakowska Avenue 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 426, fax: [phone]

autor

Wiśniowski W.

• Institute of Aviation Krakowska Avenue 110/114, 02-256 Warsaw, Poland tel.: [phone] ext. 426, fax: [phone]

Bibliografia

• [1] Choi, B.B., Dever, T.P., Duffy, K.P., Lowe, A.M., Loyselle, P.L., Morrison, C.R., Provenza, A.J., Assessment of Technologies for Noncryogenic Hybrid Electric Propulsion, NASA/TP – 2015 – 216588, January 2015.
• [2] Kim, H.D., Turboelectric Distributed Propulsion, Distributed Propulsion Technology, Nova Science Publishers, Inc., pp. 162-171, 2014.
• [3] Kim, H.D., Felder, J.L., Tong, M.T., Armstrong M., Revolutionary Aeropropulsion Concept for Sustainable Aviation: Turboelectric Distributed Propulsion, 21st International Society for Air Breathing Engines; ISABE 2013 – 1719, Korea 2013.
• [4] Leahy, J., Global Market Forecast 2015-2034, http://www.airbus.com/company/market/.
• [5] Piwek, K. H., Wiśniowski, W., Small air transport aircraft entry requirements evoked by FlightPath 2050, Aircraft Engineering and Aerospace Technology: An International Journal, Vol. 88, Is. 2, pp. 341-347.
• [6] Rostek, P., Hybrid Electric Propulsion, A European Initiative for Technology Development, Electric & Hybrid Aerospace Technology Symposium 2015, Brema 2015.

Uwagi

PL

Opracowanie ze środków MNiSW w ramach umowy 812/P-DUN/2016 na działalność upowszechniającą naukę.