Fabricación e instalación de una toma auxiliar de aire para el carenaje del motor de la Aeronave T-90 CALIMA para obtener un mejor rendimiento del sistema de refrigeración

Abstract

This thesis proposes a solution to the repetitive increase in the temperature of the oil used for the cooling and lubrication of the engine and its components, during the different flight phases recorded by the “Flight Data Recorder” and by the flight reports by the pilots The information obtained by these two sources indicates that during ascents, maneuvers at low speeds and high angle of attack, including traffic for landings and take-offs, the temperature indication is in red arc (+ 235 ° F / + 113 ° C), according to the reports on the cruise flight it gives an indication in green arc (Max. 180 ° F / Max. 82.22 ° C), but this indication is very close yellow arc (+181 ° F / + 83 ° C - 235 ° F / 113 ° C), on land after 25 minutes of operation the temperature indication is in red arc (+ 235 ° F / + 113 ° C). As a first step, an analysis of the position of the radiator and the components of the cooling system (air intakes, hoses and sensors) was carried out, identifying that the main causes of the temperature increase were the position of the radiator behind the cylinders of the engine and the lack of a clean air stream of thermal waste. The solution proposed in this grade project contemplates the manufacture of a series of three supports for changing the position of the radiator and the implementation of an NACA type air intake in the lower fairing of the T-90 Calima aircraft that aims to Radiator cooling and optimization of the aircraft cooling system, thus achieving dissipation of residual heat resulting from combustion produced inside the engine, avoiding excessive overheating of the same and the lubricating oil. Thus achieving a safe operation of the aircraft during the takeoff, flight and landing phases.