A MATHEMATICAL MODEL OF A SMALL CLASS TURBOPROP ENGINE

Анотація

Results and process of a development af 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 EU project 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 gcneming 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. 1^st and 2^ndderived 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 3^th derived model respect also gas temperature and pressure dynamics. Its system of equations is fully differential.