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Modern turbofan engine performance is heavily influenced by the thermal efficiency of the high pressure compressor and high pressure turbine. A transient model of the high pressure system of an IAE V2500 is therefore developed. It consists of the high pressure compressor, combustion chamber and high pressure turbine. In this simulation setup, each component is modelled by its respective component map. To achieve the most accurate read-out of the component maps, different approaches for their implementation into the simulation have been examined. To further increase the models accuracy, the gas properties dependency on temperature and chemical composition of the fluid is taken into account. The properties of the gas are calculated for each station along the gas path. Downstream of the combustion chamber, the composition of the fluid varies dependent on the fuel to air ratio. Due to the fact, the chemical reaction in the combustion chamber is included in the simulation setup. The combination of advanced map read-out methods and variable gas properties leads to a model in Simulink which shows the transient behaviour of the high pressure system and converges to a reliable steady state.
Deutscher Luft- und Raumfahrtkongress 2013, Stuttgart
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2013
21,0 x 29,7 cm, 9 Seiten
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