Influence of the gas turbine engine design parameters on the energy consumption of the multirole aircraft missions

• Autorzy: Wygonik P.
• Języki publikacji: EN

Abstrakty

EN

In the article the analysis of the influence of design parameters of the engine on the performed by the multirole aircraft mission was performed. The problem is complex as a result of performing a series of manoeuvres in various conditions of flight. A special feature of multi-role aircraft mission is a sudden (even pulse) weight change and exactly its reduction as a result of the discharge of cargo bomb, rocket or due to the consumption of ammunition during air combat manoeuvring. Reducing the airplane mass by the weight of the fuel consumed (continuously) and the used weapons radically differ the demands on the energy required to overcome gravity and drag forces. The article shows how the reduction of the aircraft mass influences on the change of the thrust load factor. It was built the mathematical model of the system engine-aircraft-air job (taking into account the flight conditions, elements of the mission - subsonic and supersonic flight, flight time, the heat-and-gasdynamic and mass model of the engine). The model enables for the simulation research of the complex flight missions and their evaluation on the basis of the constructed criteria. The model includes a parametric description of physical processes in the turbofan engine, thus provides a direct assessment of the impact of selection of engine parameters on the effectiveness of the mission. The results of calculations according to classical criteria (e.g. kilometre fuel consumption, specific fuel consumption) were presented. The paper presents new criteria, which enable to analyze the energy consumption of the complex mission of the aircraft (e.g. energy consumption: the unit range, the degree of utilization of energy resources and the carried out the mission engine). Criteria were built in by combining the parameters necessary for the flight with disposable ones. On the basis of these parameters there was done an assessment of the "quantitative" adjustment of a power unit to various missions such as subsonic, supersonic and mixed (for different their proportion), for different levels and the plane range. The results were presented in a pictorial way on numerous charts.

Słowa kluczowe

EN

gas turbine engine design; simulation; airplane-engine integration; aircraft mission optimization

• 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: 2012
• Tom: Vol. 19, No. 2
• Strony: 569--576
• Opis fizyczny: Bibliogr. 9 poz., rys.

Twórcy

autor

Wygonik P.

• Rzeszów University of Technology Department of Airplane and Aircraft Engines Powstańców Warszawy Avenue 12, 35-959 Rzeszów, Poland tel.: [phone], fax: [phone],

Bibliografia

• [1] Herteman, J. P., Goutines, M., Design Principles and Methods for Military Turbojet Engines, RTO-MP, AC/323 (AVT) TP/9 Design Principles and Methods for Aircraft Gas Turbine Engines, February 1999.
• [2] Orkisz, M., et al., Podstawy doboru turbinowych silników odrzutowych do płatowca, Biblioteka Naukowa Instytutu Lotnictwa, Warszawa 2002.
• [3] Performance Prediction and Simulation of gas Turbine Engine Operations, RTO-TR-044 AC/323 (AVT-018) TP/29, RTO Technical Report 44, RTO/NATO Apri 2002.
• [4] Rumiancev, S. W., Sigilevskij W. A., Sistemnoe projektirovanie awiacionnogo dwigatela,Izidatelstwo MAI, Moskva 1991.
• [5] Siłka W., Energochłonnośc ruchu samochodu, WNT, Warszawa 1997.
• [6] Stricker, J. M., The Gas Turbine Engine Conceptual Design Process – An Integrated Approach, RTO-MP, AC/323 (AVT) TP/9 Design Principles and Methods for Aircraft Gas Turbine Engines, February 1999.
• [7] Ubysz, A., Energochłonność samochodu a zużycie paliwa w złożonych warunkach ruchu, Wydawnictwo Politechniki Śląskiej, Gliwice 2003.
• [8] Wygonik, P., Kryteria doboru parametrów silnika turbinowego do samolotu wielozadaniowego, Silniki Spalinowe, Nr 4, 2006.
• [9] Wygonik, P., Influence of Basic Energetic Parameters of Turbofan Engine on Multipurpose Aircraft Manoeuvres Indexes, PTNSS, 2011.