In this paperwork we are studying the performance of a combustion process into a jet engine combustion chamber, more specifically the relations between excess of air, overall pressure ratio and inlet turbine temperature for a combustion reaction based on a jet A fuel. The study present a method of calculating the excess of air for a generalized combustion reaction based on Jet A fuel indicated by the general formula , for different temperatures of air, different temperatures of fuel and different inlet turbine temperatures. The result of this study is to achieve diagrams in which are presented the variation of air excess with engine parameters who participate in combustion process and to performed a computing program in which it is calculated the exactly value of excess of air for any outlet compressor temperatures, any inlet turbine temperatures and different fuel temperatures.
This paper proposes a study regarding the use of bioethanol as fuel for turbine engines used in aviation. For this purpose, three blends of 5, 10, and 15% concentrations of bioethanol mixed with Jet A fuel were tested on JET CAT P80 microturbo engine. During the engine testing, the following parameters were monitored: engine speed, generated force, temperature in front of the turbine, fuel volumetric flow rate, and vibration levels measured both on axial and radial direction. The tests were performed by maintaining the microturbo engine for about 1 min at three operating regimes: idle, cruise, and maximum speed. In addition, a comparative analysis between fuels for a test with the microturbo engine from the idle position to maximum position is presented. After the tests were conducted, a jet engine cycle analysis was performed at the max regime and the fuel specific consumption, the efficiency of the combustion chamber, and the thermal efficiency of the engine for each fuel blend were calculated. The tests were made without making any modifications to the engine components or automation system.
The paperwork presents a study to determine the performance parameters of a propeller characterized by the variable diameter in combination with the variable pitch, a technical method of improving the efficiency of the propeller for different power modes. This solution allows varying the load of the propeller by varying the propeller blade diameter in connection with the changing pitch blade at a constant speed mode setting. The solution allows varying the propeller area to control the air flow and to obtain the optimum load at different stage blade angles varying the pitch into the optimum position at a constant speed mode to realize the increase of the air flow through the propeller blades at different power modes. The study is performed only in aerodynamic mode and not in the technical constructive mode.
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