The influence of on-design bypass turbine engine parameters on multipurpose aircraft missions energy-consuming

• Autorzy: Wygonik P.
• Języki publikacji: EN

Abstrakty

EN

In the article there was presented a quality assessment of parameters selection of bypass turbine engine for a multipurpose aircraft. It was assumed that the assessment criterion results from the energy-consumption of a flight. The criteria of energy-consumption range were defined as the relation of sum ofenergy supplied to the aircraft on the driven stages to the distance during a mission. The second criterion of unitary energy-consumption is defined as the relation of the movement energy-consumption to the product of the aircraft mass and the route during the elementary stage of the flight. With the use of the already worked out models of the power unit (bypass turbine engine with jet mixer and afterburner) of an aircraft (already known mass and aerodynamic characteristics) there were determined the ranges of thrust which are indispensable for a flight and available for the engine at each stage of the mission: take off, climb, subsonic and supersonic flight and turn with different overload factor. On the example of three chosen aircraft missions (Lo-Lo-Lo, Hi-Lo-Hi and Hi-Hi-Hi) the models of mission energy-consumption were developed. For the accepted change ranges of the comparative cycle parameters of the turbine engine the run of energy-consumption was tested. It was stated that for the assumed data the most energy-consuming mission is Lo-Lo-Lo, wherefore the increase of the compression and the rate of bypass reduces the energy-consumption of the mission.

Słowa kluczowe

EN

military gas turbine engine; military aircraft mission analysis; multipurpose aircraft; energy consuming

• 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: 2010
• Tom: Vol. 17, No. 1
• Strony: 499--506
• Opis fizyczny: Bibliogr. 8 poz., rys.

Twórcy

autor

Wygonik P.

• Rzeszów University of Technology, Department ofAirplane and Aircraft Engines W. Pola Street 2, 35-959 Rzeszów, Poland tel: [phone],

Bibliografia

• [1] Dzierżanowski, P., Kordziński, W., Łyżwiński, M., Otyś, J., Szczeciński, S., Wiatrek, R., Turbinowe silniki odrzutowe. Seria Napędy Lotnicze, WKiŁ, Warszawa 1993.
• [2] Filippone, A., Flight performance of fixe and rotary wing aircraft; Elsevier Ltd. 1998.
• [3] Orkisz, M. (red), Podstawy doboru turbinowych silników odrzutowych do płatowca, Biblioteka Naukowa Instytutu Lotnictwa, Warszawa 2002.
• [4] Siłka, W., Energochłonność ruchu samochodu, WNT, Warszawa 1997.
• [5] Schaffer, A., Lauer, W., Design of a new fighter engine – the dream in an engine man’s life, RTO-MP-*, AC/323(AVT)TP/9 Design Principles and Methods for Aircraft Gas Turbine Engines, 1999.
• [6] Wygonik, P., Kryteria doboru parametrów silnika turbinowego do samolotu wielozadaniowego, Silniki Spalinowe, Nr 4, 2006.
• [7] Wygonik, P., Masowe kryteria doboru parametrów dwuprzepływowego silnika odrzutowego do samolotu wielozadaniowego, dla wybranych zadań lotniczych, Polskie Towarzystwo Naukowe Silników Spalinowych, Silniki Spalinowe, T. 1, 2007.
• [8] Wygonik, P., Criteria of aircraft engine parameters evaluation for multi-purpose aircraft, Journal of KONES Powertrain and Transport, Vol. 14, No. 2, 2007.