Abstract
Objectives: The study presents the results of modelling and analysis of a micro turbojet engine that can develop thrust in the range of 4 kN, that is sufficient to propel small UAVs and Drones. The modelling and simulation is carried out in Flownex simulation environment which is a powerful one-dimensional tool commercially available to analyze the performance of engine components by establishing network linkages between the components. Methods/Findings: This study also uses the “Turbo power match” module for matching of power produced between the turbine and compressor components in the engine assembly as well as “Adiabatic flame element” module to estimate the combustion parameters in the engine. The results show that the analyzed system produces a thrust of 3.79 kN at an inlet air pressure of 1.01 bar. The burnt gases in the combustor are found to reach a maximum of 556.17 K which permits the use of existing materials in the construction of this engine. The one-dimensional eliminates the time needed for analysis and hence enables quick implementation of design parameters resulting in cost reduction and time delay in manufacturing of engines. Application: This performance analysis provides vital information needed for micro turbine engine manufacturers and drone designers and hence plays a vital role in the future propulsion of UAVs and Drones. Keywords: Adiabatic Flame Temperature, Drone Propulsion, Flownex, Modeling and simulation, Turbojet Engine, Turbo Power Match
Highlights
Modelling and simulation of the dynamic behaviour of aircraft engine to optimize its performance, even manufacturing a prototype for actual testing leads to better results, cost cutting and time saving
Flownex simulation programme has been used for component matching and investigation of the engine
The output thrust of the engine analyzed in this study is found to be 3.79 kN at an inlet air pressure of 1.01 bar at an inlet flow rate of 8.71 kg/s
Summary
Modelling and simulation of the dynamic behaviour of aircraft engine to optimize its performance, even manufacturing a prototype for actual testing leads to better results, cost cutting and time saving. In this process it is essential to consider the complex dynamic behaviour of the interactions between engine stages like and low pressure compressors, turbines, nozzle exit etc.,. This analysis results in obtaining first-hand information on the parameters that affects the optimal working of the engine and enables precise modelling of materials and complex blade shapes. Some of the relevant works carried out by researchers related to the present work is given below
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