A MATHEMATICAL MODEL OF A SMALL CLASS TURBOPROP ENGINE
Results and process of a development of a mathematical model of a small turboprop engine are presented in this article. The presented model is based on engine characteristics and other necessary input data which came from the EUproject ESPOSA of an engine. This engine is currently under the development and testing by present European manufacturer. The model is derived as generic, dynamic and nonlinear\ There is chosen a conception, where final set of governing equations is based on a connection of submodels governing equations of elementary engine parts, i.e. compressor-, turbine, nozzle. The lumped parameters method is applied to these submodels where their properties are described with characteristics, which are standard in the aircraft industry. 1st and 2nd derived mathematical models are comprised of a dynamic part which respects the rotating mass dynamics only. Result of this assumption is a system of equations, both differential and nondifferential. Dynamic part of 3th derived model respect also gas temperature and pressure dynamics. Its system of equations is fully differential.
Адреса редакції журналу:
Редакція журналу «ВД», Національний університет "Запорізька політехніка",
вул. Жуковського, 64, м. Запоріжжя, 69063, Україна.
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