NUMERICAL INVESTIGATION OF TURBOJET ENGINE THRUST CORRELATED WITH THE COMBUSTION CHAMBER'S PARAMETERS

The purpose of this paper is to highlight the correlation between the thrust as the main performance of a turbojet engine and the parameters of the combustion chamber, e. g. the pressure losses and the influence of the perturbations in the turbine inlet temperature T3T. The performances of the turbojet engine have been predicted by following the numerical simulation of the engine's operation, with an in-house developed code, based on a comprehensive mathematical model of the turbojet engine. The investigation is carried on at the engine's design point, which means 100% rotational speed, at sea level static standard atmosphere conditions. The most significant parameters of the combustion chamber, namely the combustion chamber's pressure losses and the perturbations in the turbine inlet temperature T3T have been chosen such that to match the standpoint of the fighter pilot; the most relevant parameters is the turbine inlet temperature T3T. The numerical results are summarized as graphs and charts, from which one can express new correlations and further, a new command and control law for the turbojet engine's operation can be concluded. The contributions of this study may prove to have practical applications, for being used both for training the pilot students and during flight operation, for contributing to a significant improvement in flight safety, which can be of real help for fighter pilots.