Abstract
At the stage of a power unit selection for a multi-purpose aircraft the problem of mutual relations between the dimension of an aircraft and an engine should be solved. Starting from the motion equation of an aircraft and the theory of similarity the criteria and performance were determined which connect in a geometrical and power way the engine and the aircraft. The analysis of the influence of flight conditions and the parameters of an engine comparative cycle on the geometrical dimensions was conducted. In the paper it was shown that the fundamental flight stage which determines the relations between the geometrical parameters of the aircraft and the engine is the take-off or supersonic flight on the big altitude. Usually the parameters selection of the turbine engine thermal cycle is done on the basis of the internal characteristics of the engine, such as specific thrust and specific fuel usage. In case of the turbofan engine model with the mixer, afterburner, and the aircraft model (with simplified aerodynamic and mass characteristics) the influence of the cycle parameters on the performance and aerodynamic lift/drag ratio, the agreed range and the theoretical range was described.
Highlights
For the power of contemporary aircrafts turbine engines of different types and constructional schemes are applied
Among them turbojet and turbofan engines are used for the power of multi-purpose aircrafts
The basic indexes of the engine which are taken into consideration as the first ones while aircraft designing are: engine thrust, specific fuel usage, specific mass, overall dimensions, and the functional characteristics such as: relation of the engine thrust and specific fuel usage from the altitude and velocity of an aircraft, work range etc
Summary
For the power of contemporary aircrafts turbine engines of different types and constructional schemes are applied. Wskazuje to na whose flight is mainly at subsonic ranges the turbofan ento, ¿e przy wyborze parametrów silnika w wielu przypad- gines with a jet mixer and afterburner are chosen, for which kach odstêpuje siê od obliczeniowych, optymalnych dla sil- their characteristic feature is their by-pass ratio of about nika wartoœci. „punkt obliczeniowy” dla silnika i jak zadanie lotnicze re- ment for an aircraft is long-lasting flight at small altitudes alizowane przez samolot wielozadaniowy determinuje wy- with the supersonic velocity, it is necessary to use turbofan bór tego punktu? Ruch samolotu poruszaj1cego siê z prêdkoœci V w uk3a- choose “design point” for the engine and what aircraft task dzie wspó3rzêdnych (H, L) opisuj równania [4, 14]: fulfilled by the multi-purpose aircraft determines the choice m dV dt. It enables to decrease the number of variables in the task, and to decrease the dimension of the problem and avoid difficulties connected with recalculating a lot of solutions
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