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Influence of basic turbofan engine parameters on multipurpose aircraft maneuvers indexes

Wygonik P.

Journal of Polish CIMAC

2012

Vol. 7, no 1

285-293

The problem described in the paper concerns the choice strategy of so-called design point of the flow engine in a multi-role aircraft at the initial stage of aircraft and engine design as the aviation system. The design point is defined by the height and speed of flight and engine parameters of heat flow which allows in particular to determine the mass and dimensions of the engine. The following analysis represents an attempt to seek other than the classic (based on a maximum within unitary thrust, specific fuel consumption) criteria for calculation point for the multi-role aircraft. Multipurpose aircraft, during every mission, very often must perform many tasks and at the same time must use the energy source for the maneuvers. The mathematical model of the chosen tasks of an aircraft has been presented, which due to the energetic requirements do not allow to build the uniform optimization criteria. The models of such flight stages have been presented: take off, climbing with the maximum velocity and the maximum angle of climb, horizontal flight both sub-and supersonic, turn determined. In order to make the considerations easier the engine model was reduced to two parameters: non-dimensional loading coefficient and the coefficient of relative engine measure. During the conducted calculations the values of the non-dimensional coefficients were determined allowing to optimize the tasks performed by the aircraft during the mission. By making comparisons of the determined characteristics the acceptable values of the non-dimensional engine coefficients were shown and the assessment criteria of the aircraft manoeuvre properties vital for the realization of the entirety of its mission were presented.

Influence of basic energetic parameters of turbofan engine on multipurpose aircraft maneuvers indexes

Wygodnik P.

Silniki Spalinowe

2011

R. 50, nr 3

Samolot wielozadaniowy, wykonując cały szereg różnorodnych zadań, niejednokrotnie w czasie jednej misji, musi wykorzystywać zasoby energetyczne dla uzyskania wymaganej sytuacją manewrowości. Przedstawiono model matematyczny wybranych zadań samolotu, które z racji wymagań energetycznych i ekonomicznych uniemożliwiają zbudowanie jednolitych kryteriów optymalizacji. Przedstawiono modele takich etapów lotu jak: start, wznoszenie z maksymalna prędkością i maksymalnym katem wznoszenia, lot poziomy pod- i naddźwiękowy, zakręt ustalony. Dla uproszczenia rozważań model silnika sprowadzono do dwóch parametrów: bezwymiarowego współczynnika obciążenia (który zawiera w sobie parametry cyklu roboczego silnika jak temperaturę przed turbiną, spręż całkowity silnika) oraz wskaźnik względnego wymiaru silnika. W trakcie przeprowadzonych obliczeń wyznaczono wartości wskaźników bezwymiarowych pozwalających optymalizować poszczególne zadania wykonywane przez samolot w trakcie misji. Dokonując porównania wyznaczonych charakterystyk wskazano dopuszczalne wartości wskaźników bezwymiarowych silnika i wskazano te kryteria oceny własności manewrowych samolotu, które są istotne dla realizacji całej jego misji.

Multipurpose aircraft, during one mission, very often must perform many tasks and at the same time must use the energy sources for the maneuvers. The mathematical model of the chosen tasks of an aircraft has been presented, which due to the energetic and economical requirements do not allow to build the uniform optimization criteria. The models of such flight stages have been presented: take off, climbing with the maximum velocity and the maximum angle of climb, horizontal flight both sub-and supersonic, turn determined. In order to make the considerations easier the engine model was reduced to two parameters: non-dimensional loading coefficient and the coefficient of relative engine measure. During the conducted calculations the values of the non-dimensional coefficients were determined which allow to optimize the tasks performed by the aircraft during the mission. By making comparisons of the determined characteristics there were shown the acceptable values of the non-dimensional engine coefficients and there were presented the assessment criteria of the aircraft maneuver properties which are important for the realization of the whole its mission.